copy of apollo 8 flightplan vagc

MET X APOLLO 8 FLIGHTPLAN-003:00:00 LAUNCH - PRE-LAUNCH+000:00:00 LAUNCH - LAUNCH+000:10:06 LAUNCH - INSERTION+000:30:00 FLIGHT DATA - SYSTEMS CHECK+001:00:00 ALIGNMENT - P52 IMU ALIGNMENT+001:50:00 MANEUVER - TRANS-LUNAR INJECTION+003:10:00 SEPARATION+006:00:00 AGC - P23 CISLUNAR NAVIGATION+007:00:00 MANEUVER - INITIATE PTC+009:00:00 SYSTEMS - FUEL CELL O2 PURGE+009:50:00 MANEUVER - TERMINATE PTC+010:00:00 MANEUVER - 1st MIDCOURSE CORRECTION+011:30:00 MANEUVER - INITIATE PTC+012:00:00 FLIGHT DATA - SYSTEMS CHECK+012:30:00 SYSTEMS - INITIATE BATTERY CHARGING+013:00:00 8 HOUR REST PERIOD+021:00:00 SYSTEMS - TERMINATE BATTERY CHARGING+021:00:00 SYSTEMS - INITIATE BATTERY CHARGING+021:30:00 SYSTEMS - FUEL CELL O2 PURGE+024:00:00 FLIGHT DATA - SYSTEMS CHECK+027:30:00 MANEUVER - TERMINATE PTC+028:00:00 AGC - P23 CISLUNAR NAVIGATION+029:00:00 MANEUVER - INITIATE PTC+029:30:00 SYSTEMS - TERMINATE BATTERY CHARGING+035:00:00 SYSTEMS - FUEL CELL O2 PURGE+036:00:00 FLIGHT DATA - SYSTEMS CHECK+036:30:00 ALIGNMENT - P52 IMU ALIGNMENT+037:00:00 8 HOUR REST PERIOD+046:00:00 SYSTEMS - FUEL CELL O2 PURGE+046:30:00 SYSTEMS - FUEL CELL H2 PURGE+050:00:00 FLIGHT DATA - SYSTEMS CHECK+051:30:00 MANEUVER - TERMINATE PTC+052:00:00 AGC - P23 CISLUNAR NAVIGATION+053:00:00 MANEUVER - INITIATE PTC+059:40:00 MANEUVER - TERMINATE PTC+060:00:00 MANEUVER - 2nd MIDCOURSE CORRECTION+061:30:00 MANEUVER - INITIATE PTC+062:00:00 FLIGHT DATA - SYSTEMS CHECK+062:30:00 5 HOUR NAP PERIOD+067:40:00 MANEUVER - TERMINATE PTC+068:10:00 MANEUVER - LUNAR ORBIT INSERTION+070:30:00 SYSTEMS - FUEL CELL O2 PURGE+072:30:00 MANEUVER - LUNAR ORBIT CIRCULARIZATION+075:00:00 SYSTEMS - INITIATE BATTERY CHARGING+076:00:00 FLIGHT DATA - SYSTEMS CHECK+078:30:00 SYSTEMS - TERMINATE BATTERY CHARGING+079:00:00 8 HOUR REST PERIOD+088:20:00 MANEUVER - TRANS-EARTH INJECTION+090:30:00 SYSTEMS - INITIATE BATTERY CHARGING

+091:00:00 FLIGHT DATA - SYSTEMS CHECK+091:30:00 MANEUVER - INITIATE PTC+092:00:00 SYSTEMS - FUEL CELL O2 PURGE+092:30:00 SYSTEMS - FUEL CELL H2 PURGE+096:00:00 SYSTEMS - TERMINATE BATTERY CHARGING+099:40:00 MANEUVER - TERMINATE PTC+100:00:00 AGC - P23 CISLUNAR NAVIGATION+100:30:00 MANEUVER - INITIATE PTC+102:40:00 MANEUVER - TERMINATE PTC+103:00:00 MANEUVER - 3rd MIDCOURSE CORRECTION+104:30:00 MANEUVER - INITIATE PTC+105:00:00 FLIGHT DATA - SYSTEMS CHECK+105:30:00 8 HOUR REST PERIOD+114:00:00 SYSTEMS - FUEL CELL O2 PURGE+119:00:00 FLIGHT DATA - SYSTEMS CHECK+119:30:00 MANEUVER - TERMINATE PTC+120:00:00 AGC - P23 CISLUNAR NAVIGATION+120:30:00 MANEUVER - INITIATE PTC+124:30:00 SYSTEMS - FUEL CELL O2 PURGE+126:30:00 SYSTEMS - ECS REDUNDANCY TEST+127:00:00 8 HOUR REST PERIOD+135:30:00 FLIGHT DATA - SYSTEMS CHECK+144:00:00 MANEUVER - TERMINATE PTC+144:30:00 AGC - STATE VECTOR UPDATE+144:45:00 ALIGNMENT - P52 IMU ALIGNMENT+145:15:00 FLIGHT DATA - SYSTEMS CHECK+145:45:00 ENTRY

APOLLO 8 FLIGHTPLAN

Column 1Option 3

Star 22 (Regulus), far Earth option

Column 2Battery B

Battery BBattery A

Column 3

Star 22 (Regulus), far Earth option

Battery A

Column 4Option 3

Column 5

Star 34 (Atria), far Moon option

Column 6

MANEUVER - LUNAR ORBIT CIRCULARIZATIONBattery BColumn 7Battery B

Battery A

Column 8

Battery A

Column 9

Column 10

Star 23 (Denebola), far Earth option

Column 11

CM State Vectors, Earth SOIOption 2, for Entry REFSMMATColumn 12

MET Panel CONFIGURE DAPPress "F4" to open the menu. Copy the "Mass" field in the Object Info screen into the "kgs" cell below and press "F9" to calulate CSM weight in lbs

kgs28860

DSKY V48ELine 1: 10002Line 2: 01111PROLine 1: xxxxxLine 2: 00000Copy the value in the "CSM Mass" in lbs cell from the conversion cell above and enter into the DSKY the CSM WeightV21E +(CSM Weight in lbs)EPROLine 1: xxxxxLine 2: xxxxxPRO

1 SC CONT - CMC (UP)DSKY V46E

AUTOMATIC SV UPDATEMFD2 Ensure AGC is in idle program, if not, V37E 00E

Open "Project Apollo MFD"Click "TELE"Click "SV"Click "REF" (if necessary)For Earth SOI State Vectors, type "Earth" in the boxFor Moon SOI State Vectors, type "Moon" in the boxClick "SRC" (if necessary)For CM State Vectors, type "AS-503" in the boxFor SIVB State Vectors, type "AS-503-S4BSTG" in the box

2 UPTLM/CM - ACCEPT (UP)3 PCM BIT RATE - HIGH (UP)

VERIFY UP TLM - DATA (UP)Click "SV" again to start the uplinkWhen DSKY is complete uploading uplink, proceed

2 UPTLM/CM - BLOCK (DOWN)3 PCM BIT RATE - LOW (DOWN)

MFD2 Click "BCK"

MANUAL SV UPDATECTRL+P - PAUSE SIMOpen Excel Worksheet "CMC Update"Ensure the "State Vectors" tab in the Worksheet is selectedKey "F4" and select "Custom" in the simulator menuSelect "Scenario Editor" and click "OK"Click "Date"Click "Refresh"Copy the "Modified Julian Day (MJD)" to the "CURR. MJD" cell in the WorksheetClick "Done" in Scenario Editor

Ensure "AS-503" is highlighted for "this vehicle" update. Ensure "AS-503-S4BSTG" is highlighted for "other vehicle" update. Click "Edit"Click "State Vectors"For Earth SOI state vectors, ensure the "Orbit reference" box displays "Earth"For Moon SOI state vectors, ensure the "Orbit reference" box displays "Moon"Copy "x, y, z" fields in Scenario Editor Window into "RPOS" X, Y, Z fields in CMC Update WorksheetCopy "dx/dt, dy/dt, dz/dt" fields in Scenario Editor Window into "RVEL" X, Y, Z fields in CMC Update WorksheetClose the Scenario Editor WindowsCTRL+P - UNPAUSE SIM

DSKY V71ELine 3: xxxxxKey in data for corresponding "UPBUFF" in the CMC Update Worksheet, and hit "ENTR" to proceed to the next UPBUFF Ensure UPBUFF 306 value is 1 for "this vehicle" (CSM) update, and value is 77776 for "other vehicle" (SIVB) updateWhen there are no more UPBUFF values to store, Line 3 will display "330"V33ERepeat if performing SIVB state vector update (if necessary)

P23 CISLUNAR NAVIGATIONKey "F4" to open the menuChoose "Visual helpers..." in the "Main" window Check "Planetarium mode" in the "Visual helpers" windowCheck "Celestial" in the "Markers" box and press the "Config" button nearbyHighlight "Apollo AGC navigation stars" in the "Configure celestial markers" windowClose all of the menu windows

PERFORM - "AGC - CONFIGURE DAP"

V16 N91ELine 1: xxx.xxLine 2: xxx.xx

122 MODE - ZERO (DOWN)Wait for angles in AGC to read 00000MODE - CMC (UP)Roll to 0 degrees and Yaw to 0 degrees

DSKY V37E 23ELine 1: 000xxLine 2: 00000Line 3: xxxxxV25E 000(star code)E 00000E (horizon option)EPROLine 1: 00202

1 CMC MODE - AUTO (UP)DSKY PRO

Line 1: xxx.xxLine 2: xxx.xxLine 3: xxx.xxYou may optionally key ENTR without keying PRO to bypass auto maneuverPROOnce AGC is finished aligning attitude, "V50 N18" will flash on AGC, then proceed with following stepsENTR

122 MODE - MANUAL (CENTER)

1 CMC MODE - FREE (DOWN)SC CONT - SCS (DOWN)NULL ROTATION

SCT Use the W,A,S,D keys in the scanning telescope to locate and center calibration star in the telescope122 SPEED - LO (DOWN)SXT Center the star in the sextant using the W,A,S,D keys

Key "Q" to mark the star ("E" rejects the mark, key "Q" again to re-mark)DSKY Line 2: xx.xxx

PRO122 SPEED - HI (UP)SCT Use the W,A,S,D keys in the telescope to locate the Earth or Moon and center its horizon closest to the calibration star in the telescope122 SPEED - LO (DOWN)SXT Center the sextant on the horizon (curve where Earth or Moon meets space) using the W,A,S,D keys.

Key "Q" to mark the horizon ("E" rejects the mark, key "Q" again to re-mark)Line 1: 00016PROV37E 23ELine 1: 000xxLine 2: xxxxxLine 3: xxxxxPROLine 1: xxx.xxLine 2: xxxx.xValue of 00000 (all balls) for both is goodPRO00E

122 SPEED - HI (UP)

PROGRAMS USED

Prog Description01 Prelaunch initialization02 Prelaunch gyrocompassing03 Prelaunch verification of gyrocompassing05 Guidance, navigation, and control system start-up06 Guidance, navigation, and control system power down11 Earth orbit insertion monitor20 Rendezvous navigation21 Ground track determination22 Orbital navigation23 Cislunar midcourse navigation27 Computer update30 External AV prethrust34 Rendezvous terminal phase iniation35 Terminal phase midcourse40 Service propulsion thrusting41 Reaction control thrusting47 Thrust monitor51 Inertial measurement unit Orientation determination52 Inertial measurement unit realignment53 Backup inertial measurement unit orientation determination54 Backup inertial measurement unit realignment61 Entry maneuver to command module/service module separation attitude62 Entry command module/service module separation and pre-entry maneuver63 Entry initialization64 Entry m post - 0.05g67 Entry --final phase

CONFIGURE DAPPress "F4" to open the menu. Copy the "Mass" field in the Object Info screen into the "kgs" cell below and press "F9" to calulate CSM weight in lbs

lbs63492

value of 00000 deactivates DAPquads used in maneuver

CSM weight in lbsLEM weight in lbs

Copy the value in the "CSM Mass" in lbs cell from the conversion cell above and enter into the DSKY the CSM Weight

pitch gimbal adjustment angleyaw gimbal adjustment angle

starts DAP

AUTOMATIC SV UPDATE

MANUAL SV UPDATE

Copy the "Modified Julian Day (MJD)" to the "CURR. MJD" cell in the Worksheet

Ensure "AS-503" is highlighted for "this vehicle" update. Ensure "AS-503-S4BSTG" is highlighted for "other vehicle" update. Click "Edit"

For Earth SOI state vectors, ensure the "Orbit reference" box displays "Earth"For Moon SOI state vectors, ensure the "Orbit reference" box displays "Moon"Copy "x, y, z" fields in Scenario Editor Window into "RPOS" X, Y, Z fields in CMC Update WorksheetCopy "dx/dt, dy/dt, dz/dt" fields in Scenario Editor Window into "RVEL" X, Y, Z fields in CMC Update Worksheet

upbuff value, initially 304Key in data for corresponding "UPBUFF" in the CMC Update Worksheet, and hit "ENTR" to proceed to the next UPBUFF Ensure UPBUFF 306 value is 1 for "this vehicle" (CSM) update, and value is 77776 for "other vehicle" (SIVB) updateWhen there are no more UPBUFF values to store, Line 3 will display "330"

updates CMC

P23 CISLUNAR NAVIGATION

Check "Celestial" in the "Markers" box and press the "Config" button nearbyHighlight "Apollo AGC navigation stars" in the "Configure celestial markers" window

shaft angle in degreestrunnion angle in degrees

calibration star codelandmark option: 00100 Earth, 00200 Moonhorizon option: 00110 near Earth, 00120 far Earth, 00210 near Moon, 00220 far Moonloads desired calibration star and desired horizon option

auto maneuver preparation code

COMP ACTY will light for a momentroll anglepitch angleyaw angle

You may optionally key ENTR without keying PRO to bypass auto maneuverAGC will automatically align CSM within range to align optics with calibration star

Once AGC is finished aligning attitude, "V50 N18" will flash on AGC, then proceed with following stepsAGC will display flashing V59

Use the W,A,S,D keys in the scanning telescope to locate and center calibration star in the telescope

Key "Q" to mark the star ("E" rejects the mark, key "Q" again to re-mark)trunnion bias calibration angle in degreesAGC will display flashing V51

Use the W,A,S,D keys in the telescope to locate the Earth or Moon and center its horizon closest to the calibration star in the telescope

Center the sextant on the horizon (curve where Earth or Moon meets space) using the W,A,S,D keys.Key "Q" to mark the horizon ("E" rejects the mark, key "Q" again to re-mark)

terminate marking sequence

verify calibration star codeverify landmark optionverify horizon optionCOMP ACTY will light for a momentstate vector poistion change in .01 nmstate vector velocity change in .1 ft/sec

Entry maneuver to command module/service module separation attitudeEntry command module/service module separation and pre-entry maneuver

MET Panel P51 IMU ORIENTATIONEnsure rotation is nulledPress Ctrl+F9 to open the "Visual Helpers" menuCheck "Planetarium mode" in the "Visual helpers" windowCheck "Celestial" in the "Markers" box and press the "Config" button nearbyHighlight "Apollo AGC navigation stars" in the "Configure celestial markers" windowClose all of the menu windows

1 VERIFY BMAG MODE - 3 RATE 2 (ALL UP)122 VERIFY MODE - MANUAL (CENTER)

VERIFY CONTROLLER/SPEED - HI (UP)DSKY V16 N91E

Line 1: xx.xxxLine 2: xx.xxx

122 MODE - ZERO (DOWN)Wait for angles in AGC to read 00000MODE - MANUAL (CENTER)

DSKY V37E 51ELine 1: 00015If realigning IMU after Gimbal Lock or loss of IMU, key "ENTR" to center the FDAI to 0, 0, 0, then proceedPROUse the W,A,S,D keys to orient the Scanning Telescope over any starCONTROLLER/SPEED - LO (DOWN)Use the W,A,S,D keys to orient the Sextant over the starKey "Q" to mark the star ("E" rejects the mark, key "Q" again to re-mark)Line 1: 00016PROLine 1: 000xxEnter the first marked star code into the DSKYV21E 000(star code)EPROUse the W,A,S,D keys to orient the Scanning Telescope over a different starCONTROLLER/SPEED - LO (DOWN)Use the W,A,S,D keys to orient the Sextant over the starKey "Q" to mark the star ("E" rejects the mark, key "Q" again to re-mark)Line 1: 00016PROLine 1: 000xxEnter the second marked star code into the DSKYV21E 000(star code)EPROLine 1: xxx.xxPRO

122 CONTROLLER/SPEED - HI (UP)

PERFORM "ALIGNMENT - P52 IMU ALIGNMENT" (OPTION 3)

P52 IMU ALIGNMENTEnsure rotation is nulled and FDAI ball is centered at close to 0 roll, 0 pitch, and 0 yawPress Ctrl+F9 to open the "Visual Helpers" menuCheck "Planetarium mode" in the "Visual helpers" window

Check "Celestial" in the "Markers" box and press the "Config" button nearbyHighlight "Apollo AGC navigation stars" in the "Configure celestial markers" windowClose all of the menu windows

1 VERIFY BMAG MODE - 3 RATE 2 (ALL UP)122 VERIFY MODE - MANUAL (CENTER)

VERIFY CONTROLLER/SPEED - HI (UP)DSKY V16 N91E


122 MODE - ZERO (DOWN)Wait for angles in AGC to read 00000MODE - CMC (UP)

DSKY V37E 52ELine 1: 00001Line 2: 0000xEnter number of desired align optionV22E 0000(option)EPROIf option 2 is selected for Entry REFSMMAT, follow these steps:Line 1: 00xxxLine 2: 000xxLine 3: 0xx.xxInput the GET of Entry Interface (ReT GET) indicated in the IMFD Map ProgramV25E +00XXXE +000XXE +0XXXXEPROIf align option 1 or 2 are selected, IMU R,P,Y angles will be displayed. Key "PRO" to proceed. "NO ATT" will light briefly. FDAI 1 aligns R,P,YLine 1: 00015PROIf the AGC fails to select two suitable stars, a PROG alarm occurs and the DSKY shows "F 05 09" with error code "00405" in R1In this case press "RSET", roll the CSM 90 degrees, and key in "V32E" to return to Star selection and try again.Line 1: 000xxPROAGC moves the Scanning Telescope and Sextant to the area of the first star

122 MODE - MANUAL (CENTER)CONTROLLER/SPEED - LO (DOWN)

SXT Center the star in the sextant using the W,A,S,D keysKey "Q" to mark the star ("E" rejects the mark, key "Q" again to re-mark)

DSKY PROLine 1: 000xxPROLine 2: 000xx

122 MODE - CMC (UP)VERIFY CONTROLLER/SPEED - HI (UP)

DSKY PROAGC moves the Scanning Telescope and Sextant to the area of the first starMODE - MANUAL (CENTER)CONTROLLER/SPEED - LO (DOWN)Center the star in the sextant using the W,A,S,D keysKey "Q" to mark the star ("E" rejects the mark, key "Q" again to re-mark)PRO

Line 1: 000xxPROLine 1: xxx.xxPROLine 1: xx.xxxLine 2: xx.xxxLine 3: xx.xxx

1 VERIFY CMC MODE - FREE (DOWN)DSKY PRO

Line 1: 00014ENTR00E

122 CONTROLLER/SPEED - HI (UP)

PERFORM "ALIGNMENT - GDC ALIGNMENT"

P53 BACKUP IMU ORIENTATIONEnsure rotation is nulledPress Ctrl+F9 to open the "Visual Helpers" menuCheck "Planetarium mode" in the "Visual helpers" windowCheck "Celestial" in the "Markers" box and press the "Config" button nearbyHighlight "Apollo AGC navigation stars" in the "Configure celestial markers" windowClose all of the menu windows

DSKY V37E 53ELine 1: 00015ENTRLine 1: 00015PROLine 1: xxx.xxLine 2: xxx.xxV24E +00000E +57476EPRO

DOCK Use rotational RCS thrust to orient COAS crosshairs directly over any star, use "Z" or "X" keys to zoom in/out for better accuracyDSKY ENTR

Line 1: 00016PROLine 1: 000xxEnter first aligned star code into AGCV21E 000(star code)EPROLine 1: xx.xxxLine 2: xx.xxxPRO

DOCK Use rotational RCS thrust to orient COAS crosshairs directly over a different star, use "Z" or "X" keys to zoom in/out for better accuracyDSKY ENTR

Line 1: 00016PROLine 1: 000xxEnter second aligned star code into AGCV21E 000(star code)E

PROLine 1: xxx.xxIf star angle difference higher than 000.70 degrees, key V32E to restart star marking sequence, if not, proceedPRO

PERFORM "ALIGNMENT - P54 BACKUP IMU ALIGNMENT" (OPTION 3)

P54 BACKUP IMU ALIGNMENT

Ensure rotation is nulled and FDAI ball is centered at close to 0 roll, 0 pitch, and 0 yawEnsure rotation is nulledPress Ctrl+F9 to open the "Visual Helpers" menuCheck "Celestial" in the "Markers" box and press the "Config" button nearbyHighlight "Apollo AGC navigation stars" in the "Configure celestial markers" windowClose all of the menu windows

DSKY V37E 54ELine 1: 00001Line 2: 0000xEnter number of desired align optionV22E 0000(option)EPROLine 1: 00015ENTRLine 1: 000xxV21E 00040EPROLine 1: xxx.xxLine 2: xxx.xxV24E +00000E +57476EPRO

DOCK Use rotational RCS thrust to orient COAS crosshairs directly over Altair, use "Z" or "X" keys to zoom in/out for better accuracyDSKY ENTR

Line 1: 00016PROLine 1: 00040PROLine 1: 00040V21E 00044ELine 1: 00000Line 2: 00000PRO

DOCK Use rotational RCS thrust to orient COAS crosshairs directly over Enif, use "Z" or "X" keys to zoom in/out for better accuracyDSKY ENTR

Line 1: 00016PROLine 1: 00044PROLine 1: xxx.xxIf star angle difference higher than 000.70 degrees, key V32E to restart star marking sequence, if not, proceedLine 1: xx.xxx


1 VERIFY CMC MODE - FREE (DOWN)DSKY PRO

Line 1: 00014ENTR00E

PERFORM "ALIGNMENT - GDC ALIGNMENT"

GDC ALIGNMENTEnsure rotation is nulled

DSKY V16 N20ELine 1: xxx.xxLine 2: xxx.xxLine 3: xxx.xx

1 ATTITUDE SET/ROLL - SETATTITUDE SET/PITCH - SETATTITUDE SET/YAW - SETVERIFY ATT SET - GDC (DOWN)GDC ALIGN - PUSHV37E 00E

P51 IMU ORIENTATION



If realigning IMU after Gimbal Lock or loss of IMU, key "ENTR" to center the FDAI to 0, 0, 0, then proceed

Use the W,A,S,D keys to orient the Scanning Telescope over any star

Key "Q" to mark the star ("E" rejects the mark, key "Q" again to re-mark)star marked

first star code

Use the W,A,S,D keys to orient the Scanning Telescope over a different star

Key "Q" to mark the star ("E" rejects the mark, key "Q" again to re-mark)star marked

second star code

star angle difference in degrees (a value less than 000.10 is good)

PERFORM "ALIGNMENT - P52 IMU ALIGNMENT" (OPTION 3)

P52 IMU ALIGNMENTEnsure rotation is nulled and FDAI ball is centered at close to 0 roll, 0 pitch, and 0 yaw



option code IDalign option

displays current IMU anglesIf option 2 is selected for Entry REFSMMAT, follow these steps:

GET of alignment in hoursGET of alignment in minutesGET of alignment in seconds

Input the GET of Entry Interface (ReT GET) indicated in the IMFD Map Program

If align option 1 or 2 are selected, IMU R,P,Y angles will be displayed. Key "PRO" to proceed. "NO ATT" will light briefly. FDAI 1 aligns R,P,Yready to select star pair

If the AGC fails to select two suitable stars, a PROG alarm occurs and the DSKY shows "F 05 09" with error code "00405" in R1In this case press "RSET", roll the CSM 90 degrees, and key in "V32E" to return to Star selection and try again.

star code 1

AGC moves the Scanning Telescope and Sextant to the area of the first star

Key "Q" to mark the star ("E" rejects the mark, key "Q" again to re-mark)

selected star code

star code 2

AGC moves the Scanning Telescope and Sextant to the area of the first star

Key "Q" to mark the star ("E" rejects the mark, key "Q" again to re-mark)

selected star code

star angle difference in degrees (a value less than 000.03 is good)

outer gimbal torquing angle in degreesinner gimbal torquing angle in degreesmiddle gimbal torquing angle in degrees

ready to align IMU

P53 BACKUP IMU ORIENTATION


FDAI 1 centers to R:0, P:0, Y:0

shaft angle in degreestrunnion angle in degreesspecifies COAS orientation angle

Use rotational RCS thrust to orient COAS crosshairs directly over any star, use "Z" or "X" keys to zoom in/out for better accuracymarks first starstar marked

first star code


Use rotational RCS thrust to orient COAS crosshairs directly over a different star, use "Z" or "X" keys to zoom in/out for better accuracymarks second starstar marked

second star code

star angle difference in degrees (a value less than 000.70 is good)If star angle difference higher than 000.70 degrees, key V32E to restart star marking sequence, if not, proceed

PERFORM "ALIGNMENT - P54 BACKUP IMU ALIGNMENT" (OPTION 3)

P54 BACKUP IMU ALIGNMENT

Ensure rotation is nulled and FDAI ball is centered at close to 0 roll, 0 pitch, and 0 yaw


option code IDalign option

ready to select star pair

first star codeloads star 40, Altair

shaft angle in degreestrunnion angle in degreesspecifies COAS orientation angle

Use rotational RCS thrust to orient COAS crosshairs directly over Altair, use "Z" or "X" keys to zoom in/out for better accuracymarks Altairstar marked

confirm first star code

second star codeloads star 44, Enifshaft angle in degreestrunnion angle in degrees

Use rotational RCS thrust to orient COAS crosshairs directly over Enif, use "Z" or "X" keys to zoom in/out for better accuracymarks Enifstar marked

confirm second star code

star angle difference in degrees (a value less than 000.70 is good)If star angle difference higher than 000.70 degrees, key V32E to restart star marking sequence, if not, proceed

outer gimbal torquing angle in degrees

inner gimbal torquing angle in degreesmiddle gimbal torquing angle in degrees

ready to align IMU

GDC ALIGNMENT

IMU roll gimbal angleIMU pitch gimbal angleIMU yaw gimbal angleset to IMU roll gimbal angle on AGCset to IMU pitch gimbal angle on AGCset to IMU yaw gimbal angle on AGC

FDAI 2 will align to specified angles and should closely match FDAI 1

MET Panel PRE-LAUNCHRefer to the "About" tab under "Initial Configuration" to ensure the simulation is properly configured

-003:00:00 2 C/W POWER - 1 (UP)MASTER ALARM - OFF (PUSH)

5 (cb) LM PWR-1 - OPEN (PULL)(cb) LM PWR-2 - OPEN (PULL)(cb) G/N - COMPUTER / MNA - CLOSE (PUSH)(cb) G/N - COMPUTER / MNB - CLOSE (PUSH)

8 (cb) DOCK PROBE - BOTH OPEN (2 PULL)DSKY V16 N65E

Line 1: 0000xLine 2: 000xxLine 3: 000xx

2 C/W - ACK (DOWN)4 ECS GLYCOL PUMPS / 1 - AC1 (TURN)7 DIRECT O2 - OPEN HALFWAY (TURN)

101 SYSTEM TEST - 5B (2 TURN)WASTE H2O DUMP - HTR A (UP)URINE DUMP - HTR A (UP)

100 G/N POWER/OPTICS - ON (UP)G/N POWER/IMU - ON (UP, GUARDED)

122 CONTROLLER/COUPLING - DIRECT (UP)CONTROLLER/SPEED - LO (DOWN)UPTLM - ACCEPT (UP)

8 FLOOD/DIM - 1 (UP)7 FDAI/GPI POWER - BOTH (TURN)

SCS ELECTRONICS POWER - GDC/ECA (TURN)SIG COND/DRIVER BIAS POWER / 1 - AC1 (UP)SIG COND/DRIVER BIAS POWER / 2 - AC2 (DOWN)

1 TRANS CONTR PWR - ON (UP)ROT CONTR PWR/NORMAL - BOTH AC/DC (2 UP)LV/SPS IND - a (UP)

2 UPTLM/IU - BLOCK (DOWN)CM RCS PRPLNT - BOTH ON (2 UP)RCS/TRNFR - SM (DOWN MOMENTARY)

16 DOCKING TARGET - OFF (DOWN)5 G/N PWR - AC1 (UP)

INTERIOR LIGHTS/INTEGRAL - OFF (TURN)INTERIOR LIGHTS/FLOOD - OFF (TURN)INTERIOR LIGHTS/FLOOD/DIM - 1 (UP)(cb) INSTRUMENTS/NONESS - OPEN (PULL)(cb) ENVIRONMENTAL CONTROL SYSTEM/WASTE H2O URINE DUMP HTR - BOTH OPEN (2 PULL)

225 (cb) HIGH GAIN ANTENNA/FLT BUS - OPEN (PULL)(cb) HIGH GAIN ANTENNA/GROUP 2 - OPEN (PULL)

229 (cb) MAIN RELEASE/PYRO A&B - BOTH OPEN (2 PULL)(cb) O2 VAC ION PUMPS - BOTH OPEN (2 PULL)

4 TELCOM/GROUP 1 - AC1 (UP)TELCOM/GROUP 2 - AC2 (DOWN)

3 FUEL CELL INDICATOR - 2 (TURN)

DC INDICATORS - MAIN BUS A (TURN)S BAND NORMAL/PWR AMPL - PRIM (UP)S BAND NORMAL/MODE/VOICE - VOICE (UP)S BAND NORMAL/MODE/PCM - PCM (UP)S BAND NORMAL/MODE/RANGING - RANGING (UP)UP TLM - DATA (UP)UP TLM/CMD - RESET THEN OFF (UP THEN DOWN)S BAND ANTENNA - OMNI (UP)TAPE RECORDER - PCM/ANLG (UP)TAPE RECORDER - RECORD (UP)TAPE RECORDER/FWD - REWIND (DOWN)TAPE RECORDER/FWD - OFF (CENTER)POWER/SCE - NORM (UP)POWER/PMP - NORM (UP)PCM BIT RATE - HIGH (UP)

2 CABIN TEMP - SET TO 2 (SET)CABIN TEMP - AUTO (UP)HIGH GAIN ANT/POWER - OFF (DOWN)HIGH GAIN ANTENNA/TRACK - AUTO (UP)HIGH GAIN ANTENNA/BEAM - WIDE (UP)HIGH GAIN ANTENNA/PITCH POSITION - 0 (TURN)HIGH GAIN ANTENNA/YAW POSITION - 180 (TURN)HIGH GAIN ANT/SERVO ELEC - PRIM (UP)

325 CABIN PRESSURE RELIEF (LOWER HANDLE) - CLOSE (MOVE)3 VHF ANTENNA - SM LEFT (TURN)

VHF AM/B - DUPLEX (UP)6 MODE - INTERCOM/PTT (UP)

PAD COMM - T/R (UP)PAD COMM/VOLUME - 5 (SET)MASTER VOLUME - 5 (SET)INTERCOM - T/R (UP)INTERCOM/VOLUME - 5 (SET)VHF AM - T/R (UP)VHF AM/VOLUME - 5 (SET)S BAND - T/R (UP)S BAND/VOLUME - 5 (SET)AUDIO CONTROL - NORM (UP)

9 MODE - INTERCOM/PTT (UP)PAD COMM - T/R (UP)PAD COMM/VOLUME - 5 (SET)MASTER VOLUME - 5 (SET)INTERCOM - T/R (UP)INTERCOM/VOLUME - 5 (SET)VHF AM - T/R (UP)VHF AM/VOLUME - 5 (SET)S BAND - T/R (UP)S BAND/VOLUME - 5 (SET)AUDIO CONTROL - NORM (UP)

10 MODE - INTERCOM/PTT (UP)PAD COMM - T/R (UP)

PAD COMM/VOLUME - 5 (SET)MASTER VOLUME - 5 (SET)INTERCOM - T/R (UP)INTERCOM/VOLUME - 5 (SET)VHF AM - T/R (UP)VHF AM/VOLUME - 5 (SET)S BAND - T/R (UP)S BAND/VOLUME - 5 (SET)AUDIO CONTROL - NORM (UP)

2 C/W - NORMAL (UP)3 S BAND NORMAL/XPNDR - PRIM (UP)7 DIRECT O2 - INCREASE 1 CLICK FURTHER (TURN)4 SUIT COMPRESSOR / 1 - AC1 (UP)

300 SUIT FLOW - FULL (MOVE)301 SUIT FLOW - FULL (MOVE)302 SUIT FLOW - FULL (MOVE)303 SECONDARY CABIN TEMP - MAX (TURN)2 SEC COOLANT LOOP/PUMP - AC1 (UP)9 SUIT POWER - ON (UP)

POWER - AUDIO/TONE (UP)2 CABIN FAN - BOTH ON (2 UP)6 SUIT POWER - ON (UP)

POWER - AUDIO/TONE (UP)10 SUIT POWER - ON (UP)

POWER - AUDIO/TONE (UP)2 C/W - BOOST (CENTER)

SUIT CIRCUIT/H2O ACCUM - AUTO 1 (UP)SUIT CIRCUIT/HEAT EXCH - ON FOR 20 SECONDS, THEN OFF (UP FOR 20 SEC, THEN CENTER)SEC COOLANT LOOP/EVAP - RESET FOR 58 SECONDS, THEN OFF (DOWN FOR 58 SEC, THEN CENTER)UPTLM/CM - BLOCK (DOWN)

351 WATER & GLYCOL TANKS PRESSURE/REGULATOR - BOTH (TURN)WATER & GLYCOL TANKS PRESSURE/RELIEF - BOTH (TURN)EMERGENCY CABIN PRESSURE - OFF (TURN)

375 OXYGEN SURGE TANK PRESSURE RELIEF - OPEN (TURN CLOCKWISE)377 GLYCOL TO RADIATORS SEC - BYPASS (TURN)379 PRIM ACCUM FILL - OFF (TURN)352 WASTE TANK SERVICING - CLOSE (ON)

PRESSURE RELIEF - 2 (TURN)382 SUIT HT EXCH PRIMARY GLYCOL - FLOW (TURN)

SUIT HT EXCH SECONDARY GLYCOL - FLOW (TURN)WATER ACCUMULATION - BOTH RMTE (2 TURN)

-001:40:00 2 CABIN FAN - BOTH OFF (2 DOWN)

-001:10:00 SIDE HATCH CONTROL LEVER - CLOSE (CLICK)7 BMAG PWR - BOTH ON (2 TURN)2 C/W - ACK (DOWN)

DSKY V37E 01E

V16 N65E

Line 1: 0000xLine 2: 000xxLine 3: 000xx

3 FUEL CELL/MAIN BUS A - 1 & 2 ON, 3 OFF (1 & 2 UP, 3 DOWN)FUEL CELL/MAIN BUS B - 1 & 2 OFF, 3 ON (1 & 2 DOWN, 3 UP)

1 LV/SPS IND - SII/SIVB (UP)EMS FUNC - dV (TURN)

2 C/W - BOOST (CENTER)3 UP TLM/CMD - NORM (CENTER)

-000:45:00 7 EDS POWER - ON (UP)1 CM RCS LOGIC - ON (UP)8 (cb) SEQ EVENTS CONT SYS/ARM - BOTH CLOSE (2 PUSH)

(cb) SEQ EVENTS CONT SYS/LOGIC - BOTH CLOSE (2 PUSH)SECS EVENTS CONT SYSTEM/LOGIC - BOTH ON (2 UP)SECS EVENTS CONT SYSTEM/PYRO ARM - BOTH ON (2 UP)

-000:25:00 2 H2 FANS - BOTH OFF (2 CENTER)O2 FANS - BOTH OFF (2 CENTER)SM RCS/HELIUM 1 - 4 OPEN (4 UP)SM RCS/HELIUM 2 - 4 OPEN (4 UP)SM RCS SEC PRPLNT FUEL PRESS - 4 CLOSE (4 DOWN)SM RCS PRIM PRPLNT - 4 OPEN (4 UP)RCS INDICATORS - SM/A (TURN)

-000:20:00 8 AUTO RCS SELECT - B/D ROLL - B1 & B2 - MNA (UP)AUTO RCS SELECT - B/D ROLL - D1 & D2 - MNB (DOWN)AUTO RCS SELECT - PITCH - A3 & C4 - MNB (DOWN)AUTO RCS SELECT - PITCH - C3 & A4 - MNA (UP)AUTO RCS SELECT - YAW - B3 & D4 - MNA (UP)AUTO RCS SELECT - YAW - D3 & B4 - MNB (DOWN)

-000:15:00 1 FDAI/SCALE - 5/5 (CENTER)ROT CONTR PWR/DIRECT - BOTH MNA/MNB (2 UP)BMAG MODE - 3 RATE 1 (3 DOWN)GDC ALIGN - PUSH

2 EDS - AUTO (UP)RCS/CMD - OFF (DOWN MOMENTARY)

7 TVC SERVO POWER 1 - AC1/MNATVC SERVO POWER 2 - AC2/MNB

-000:10:00 2 MSN TIMER - START (UP)3 FC REACS VALVES - LATCH (DOWN)2 SEC COOLANT LOOP/PUMP - OFF (CENTER)

-000:02:00 325 PRIM GLY TO RAD - BYP (PULL)5 MAIN BUS TIE - BOTH ON (2 UP)

6,9,10 PAD COMM - OFF (CENTER)

LAUNCH

+000:00:00 If Abort, perform "Errors and Failures - Abort Mode 1A"DSKY VERIFY P11

Line 1: xxxxxLine 2: xxxxxLine 3: xxxx.x

+000:00:40 If Abort, perform "Errors and Failures - Abort Mode 1B"2 PRPLNT DUMP - RCS CMD (DOWN)

+000:01:50 If Abort, perform "Errors and Failures - Abort Mode 1C"2 EDS - OFF (DOWN)

2 ENG OUT - OFF (DOWN)LV RATES - OFF (DOWN)

+000:02:50 1 LV/SPS IND - Pc (DOWN)MANUAL ATTITUDE/PITCH - RATE CMD (CENTER)

2 GLYCOL EVAP/STEAM PRESS - AUTO (UP)GLYCOL EVAP/H2O FLOW - AUTO (UP)

+000:02:46 If Abort, perform "Errors and Failures - Abort Mode 2"

+000:05:00 1 SPS GIMBAL MOTORS - 4 START (4 UP)

+000:11:52

INSERTIONDSKY V37E 00E

1 SPS GIMBAL MOTORS - 4 OFF (4 DOWN)7 EDS POWER - OFF (DOWN)

TVC SERVO POWER - BOTH OFF (2 CENTER)5 MAIN BUS TIE - BOTH OFF (2 DOWN)8 SECS EVENTS CONT SYSTEM/PYRO ARM - BOTH SAFE (2 DOWN)

SECS EVENTS CONT SYSTEM/LOGIC - BOTH OFF (2 DOWN)(cb) SEQ EVENTS CONT SYS/ARM - BOTH OPEN (2 PULL)(cb) STABILIZATION CONTROL SYSTEM/DIRECT ULL - BOTH OPEN (2 PULL)(cb) ELS - BOTH OPEN (2 PULL)(cb) PL VENT FLT/PL - OPEN (PULL)

1 EMS FUNC - OFF (TURN)TRANS CONTR PWR - OFF (DOWN)ROT CONTR PWR/DIRECT - BOTH OFF (2 CENTER)BMAG MODE - 3 RATE 2 (3 UP)CM RCS LOGIC - OFF (DOWN)ELS - MAN (DOWN)

2 SM RCS HEATERS - 4 PRIM (4 UP)C/W - NORMAL (UP)

3 FC REACS VALVES - NORM (UP)351 EMERGENCY CABIN PRESSURE - BOTH (TURN)325 CABIN PRESSURE RELIEF (BOTH HANDLES) - NORMAL (2 MOVE)326 REPRESS PKG - FILL FOR 10 SECONDS THEN OFF (TURN)7 DIRECT O2 - CLOSE (TURN)

375 SUIT CIRCUIT RETURN VALVE - OPEN (PULL)MFD2 Open Orbit MFD

Click "DST" to display "PeA" and "ApA"Click "FRM" to change the frame to "EQU"Record PeA, ApA, T, Vel, and Inc from Orbit MFD to the Flight Data tab

+000:20:00 326 GLYCOL RESERVOIR/BYPASS - OPEN (TURN)GLYCOL RESERVOIR/OUTLET - CLOSE (TURN)GLYCOL RESERVOIR/INLET - CLOSE (TURN)

379 PRIM ACCUM FILL - ON FOR 35 SECONDS, THEN OFF (TURN)2 ECS RADIATORS/FLOW CONT - PWR (UP)

325 PRIMARY GLYCOL TO RADIATORS - NORMAL (PUSH)2 ECS RADIATORS/HEATER - PRIM 1 (UP)

POT H2O HTR - MNA (UP)GLYCOL EVAP/TEMP IN - AUTO (UP)

5 (cb) ENVIRONMENTAL CONTROL SYSTEM/WASTE H2O URINE DUMP HTR - BOTH CLOSE (2 PUSH)3 PCM BIT RATE - LOW (DOWN)

UP TLM - CMD RESET (UP MOMENTARY)VHF AM/A - SIMPLEX (DOWN)VHF AM/B - OFF (CENTER)

122 CONTROLLER/SPEED - HI (UP)DOCK INSTALL COAS (CLICK)

2 CABIN FAN/1 - ON (UP)

PRE-LAUNCHRefer to the "About" tab under "Initial Configuration" to ensure the simulation is properly configured

Suit Compressor and CMC alarms are normal

hours until launchminutesseconds

(cb) ENVIRONMENTAL CONTROL SYSTEM/WASTE H2O URINE DUMP HTR - BOTH OPEN (2 PULL)

(cb) MAIN RELEASE/PYRO A&B - BOTH OPEN (2 PULL)

CABIN PRESSURE RELIEF (LOWER HANDLE) - CLOSE (MOVE)

"O2 FLOW HI" alarm will sound after a moment, then extinguish after a few more moments

SUIT CIRCUIT/HEAT EXCH - ON FOR 20 SECONDS, THEN OFF (UP FOR 20 SEC, THEN CENTER)SEC COOLANT LOOP/EVAP - RESET FOR 58 SECONDS, THEN OFF (DOWN FOR 58 SEC, THEN CENTER)

WATER & GLYCOL TANKS PRESSURE/REGULATOR - BOTH (TURN)WATER & GLYCOL TANKS PRESSURE/RELIEF - BOTH (TURN)

OXYGEN SURGE TANK PRESSURE RELIEF - OPEN (TURN CLOCKWISE)

closes hatch after ingress

AGC will change to P01, "NO ATT" will light after a few secondsNO ATT dims and AGC changes to P02. FDAI 1 will realign

hours until launchminutesseconds

FUEL CELL/MAIN BUS A - 1 & 2 ON, 3 OFF (1 & 2 UP, 3 DOWN)FUEL CELL/MAIN BUS B - 1 & 2 OFF, 3 ON (1 & 2 DOWN, 3 UP)

(cb) SEQ EVENTS CONT SYS/ARM - BOTH CLOSE (2 PUSH)(cb) SEQ EVENTS CONT SYS/LOGIC - BOTH CLOSE (2 PUSH)SECS EVENTS CONT SYSTEM/LOGIC - BOTH ON (2 UP)SECS EVENTS CONT SYSTEM/PYRO ARM - BOTH ON (2 UP)

SM RCS SEC PRPLNT FUEL PRESS - 4 CLOSE (4 DOWN)

AUTO RCS SELECT - B/D ROLL - D1 & D2 - MNB (DOWN)

LAUNCH

absolute velocity in ft/secvertical velocity in ft/secaltitude in .1 nm

SIVB Cutoff

INSERTIONsends AGC into idle (program 00)

SECS EVENTS CONT SYSTEM/PYRO ARM - BOTH SAFE (2 DOWN)SECS EVENTS CONT SYSTEM/LOGIC - BOTH OFF (2 DOWN)(cb) SEQ EVENTS CONT SYS/ARM - BOTH OPEN (2 PULL)(cb) STABILIZATION CONTROL SYSTEM/DIRECT ULL - BOTH OPEN (2 PULL)

CABIN PRESSURE RELIEF (BOTH HANDLES) - NORMAL (2 MOVE)REPRESS PKG - FILL FOR 10 SECONDS THEN OFF (TURN)

Record PeA, ApA, T, Vel, and Inc from Orbit MFD to the Flight Data tab

PRIM ACCUM FILL - ON FOR 35 SECONDS, THEN OFF (TURN)

PRIMARY GLYCOL TO RADIATORS - NORMAL (PUSH)

(cb) ENVIRONMENTAL CONTROL SYSTEM/WASTE H2O URINE DUMP HTR - BOTH CLOSE (2 PUSH)

MET Panel TRANS-LUNAR INJECTION+001:50:00 MFD1 Open Interplanetary MFD

Click "MNU"Click "MOD" (Configuration)Select "LambertAP Mode" and ensure "Apollo P30" is displayedSelect "P30 Comp. Mode" and ensure "1.000" is displayed

Click "MNU"Click the "Course" buttonEnsure "Target Intercept" is highlighted and click "Set"Click "PRV" until "TEj" is highlightedClick "+" or "-" to change the Tej to "GET 2:50:37" and use "Adj" to change the increments as necessaryClick "NXT" until "TIn" is highlightedClick "+" or "-" to change the TIn to "GET 69:13:58" and use "Adj" to change the increments as necessaryClick "MOD" twiceClick "PRV" until "Offset Disabled" is highlightedClick "+" to select "Vel. Frame"Click "NXT" until "Rad" is highlightedClick "SET" and type "7.828M" into the box to start with. The "M" must be uppercaseClick "NXT" to highlight "Lon." Click "SET" and type "0.00" in the boxClick "NXT" to highlight "Lat." Click "SET" and type "19.20" in the box

MFD2 Open Interplanetary MFDClick "MNU"Click "PG" and type "0" into the box. This shares the right MFD with the data from the left MFDClick the "MAP" buttonClick "MOD" until "Map-config" is displayedClick "NXT" until "Time limit" is displayedClick "SET" and type "600k" into the boxClick "MOD" twice to display GET, PeT, PeV, PeA, etc…Click "PG"Click the "Soi" buttonClick the "Int" buttonClick the "Plan" buttonClick "TGT" and type "moon" in the boxClick "PG"Click the "Cnt" button and type "r-moon" in the boxClick "Z+" or "Z-" to zoom in or out as necessary to more easily view the planned trajectory to the moon

MFD1 Click "+" or "-" to change the TIn until the planned "PeT" in MFD2 is "69:13:58." Adjust Rad and TIn until PeA is around -241.1k and GET 69:13:58

+002:25:00 MFD1 Click "+" or "-" to fine-tune the TIn until the planned "PeT" in MFD2 is "69:13:58." Adjust Rad and TIn until PeA is around -241.1k and GET 69:13:58Complete trajectory fine-tuning by GET +002:34:00

MFD2 Click "SEL" to open ProjectApollo MFDClick "IMFD"Click "SIVB"Click "REQ" PAMFD will request TLI burn data from IMFD and the SIVB IU will orient the spacecraft for TLIRecord GET of Ignition, "dV x", "dV y", "dV z", and Burn Time in the "Flight Data" tab

2 VERIFY LAUNCH VEHICLE/XLUNAR - INJECT (UP)7 EDS POWER - ON (UP)8 (cb) SEQ EVENTS CONT SYS/ARM - BOTH CLOSE (2 PUSH)

SECS EVENTS CONT SYSTEM/PYRO ARM - BOTH ON (2 UP)SECS EVENTS CONT SYSTEM/LOGIC - BOTH ON (2 UP)

1 TRANS CONTR PWR - ON (UP)ROT CONTR PWR/DIRECT - BOTH MNA/MNB (2 UP)

+002:48:00 DSKY V37E 47E do not use time acceleration from this point until after TLI burnLine 1: xxxx.x delta velocity gained in 0.1 ft/secLine 2: xxxx.x y velocity change in 0.1 ft/secLine 3: xxxx.x z velocity change in 0.1 ft/sec

7 TVC SERVO POWER 1 - AC1/MNA

+002:50:37 SIVB IU TLI BURN

SIVB SHUTDOWN

DSKY V37E 00E COMP ACTY will light for a moment2 LAUNCH VEHICLE/XLUNAR - SAFE (DOWN)

MFD1 Click "PWR"MFD2 Click "REQ" PAMFD will discontinue requesting burn data

Click "SEL" and reopen IMFD Map programClick the "Plan" button to disengage map planning mode and note current trajectoryRecord the PeT GET, PeA, PeV, Lon and Lat in the "Flight Data" tab

1st MIDCOURSE CORRECTION3 SPS LINE HTRS - A (DOWN) if "SPS PRPLNT TANK/TEMP INDICATOR" 10-45 degrees

SPS LINE HTRS - A/B (UP) if "SPS PRPLNT TANK/TEMP INDICATOR" below 10 degreesSPS LINE HTRS - OFF (CENTER) if "SPS PRPLNT TANK/TEMP INDICATOR" above 75 degrees

PERFORM "AGC - STATE VECTOR UPDATE" CM State Vectors, Earth SOI


PERFORM - "SYSTEMS - EMS TEST"

MFD1 Open Interplanetary MFDClick "MNU"Click "MOD" (Configuration)Select "LambertAP Mode" and ensure "Apollo P30" is displayedSelect "P30 Comp. Mode" and ensure "1.000" is displayedClick "MNU"Click the "Course" buttonEnsure "Target Intercept" is highlighted and click "Set"Click "PRV" until "TEj" is highlightedClick "+" or "-" to change the Tej to "GET 11:00:00" and use "Adj" to change the increments as necessaryClick "NXT" until "TIn" is highlightedClick "MOD" twiceClick "PRV" until "Offset Disabled" is highlightedClick "+" to select "Vel. Frame"Click "NXT" until "Rad" is highlightedClick "SET" and type "5.723M" into the box. The "M" must be uppercase

Click "NXT" to highlight "Lon." Click "SET" and type "7.90" in the boxClick "NXT" to highlight "Lat." Click "SET" and type "6.10" in the box

MFD2 Open Interplanetary MFD (these settings may have been previously configured)Click "PG" and type "0" into the box. This shares the right MFD with the data from the left MFDClick the "MAP" buttonClick "MOD" until "Map-config" is displayedClick "NXT" until "Time limit" is displayedClick "SET" and type "600k" into the boxClick "MOD" twice to display GET, PeT, PeV, PeA, etc…Click "PG"Click the "Soi" buttonClick the "Int" buttonClick the "Plan" buttonClick "TGT" and type "moon" in the boxClick "PG"Click the "Cnt" button and type "r-moon" in the boxClick "Z+" or "Z-" to zoom in or out as necessary to more easily view the trajectory around the moon

MFD1 Modify "TIn" to change the "PeT" in MFD2. Adjust "Rad" to change the "PeA" in MFD2. Adjust "Lat" and "Lon" to change the Lat and Lon in MFD2Adjust MFD1 to aim for the following values in MFD2: PeT GET: 69:10:39 PeA: 121.9k Lon: 172.00W Lat: 8.60S***Try to make the PeT GET and PeA as close as possible, the Lon and Lat may be off by a few degrees***Continue to adjust the values in MFD1 until the values in MFD2 relate closely to those listed above. Once satisfied, continue

MFD2 Click "SEL" and open Project Apollo MFDClick the "IMFD" buttonClick "REQ" to request burn velocities from MFD1 in ft/sec

DSKY V37E 30ELine 1: 00xxx GET of burn in hoursLine 2: 000xx GET of burn in minutesLine 3: 0xx.xx GET of burn in .01 secondsInput the desired GET of the burn in hours, minutes, then seconds from MFD2V25E +00XXXE +000XXE +0XXXXERecord the GET of the burn (TeJ) from MFD1 to the "Flight Data" tabPROLine 1: xxxx.x dV x in 0.1 ft/secLine 2: xxxx.x dV y in 0.1 ft/secLine 3: xxxx.x dV z in 0.1 ft/secInput the desired velocities of the burn from in ft/sec from MFD2V25E (+ OR -)xxxxxE (+ OR -)xxxxxE (+ OR -)xxxxxE

MFD2 Record "dV x", "dV y", and "dV z" in the "Flight Data" tabPRO COMP ACTY will light for a momentLine 1: 0xxx.x predicted ApA after burn in nmLine 2: 0xxx.x predicted PeA after burn in nmLine 3: xxxx.x total dV in 0.1 ft/secRecord Line 3 in the "Flight Data" tab

1 EMS FUNC - dV SET/VHF RNG (TURN)dV EMS SET - INCR or DECRIncrease until "dV RANGE" indicator displays the dV displayed in Line 3 of the DSKYEMS FUNC - dV (TURN)

DSKY PROLine 1: xx xx mark counterLine 2: xx xx time until ignition in min/sec

Line 3: xxxxx middle gimbal anglePRO40E sets align option flag for P52

PERFORM ALIGNMENT - P52 IMU ALIGNMENT (OPTION 1)

MFD2 Click "REQ" to discontinue burn data acquisition

TIG - 15:00 DSKY V37E 40ELine 1: xxx.xx roll gimbal angleLine 2: xxx.xx pitch gimbal angleLine 3: xxx.xx yaw gimbal angle

1 VERIFY SC CONT - CMC (UP)CMC MODE - AUTO (UP)

DSKY PRO AGC will automatically align CSM for burnOnce AGC is finished aligning attitude, "V50 N18" will flash on DSKY

1 ATT DEADBAND - MIN (DOWN)TRANS CONTR PWR - ON (UP)

8 (cb) DIRECT ULL - BOTH CLOSE (2 PUSH)3 Record SPS Quantity in the "Flight Data" tab

MFD1 Click "PWR"MFD2 Click "SEL" and reopen IMFD Map program

Click the "Plan" button to disengage map planning mode and note current trajectory

TIG - 6:00 3 SPS LINE HTRS - OFF (CENTER) regardless of temperature5 MAIN BUS TIE - BOTH ON (2 UP)7 TVC SERVO POWER 1 - AC1/MNA (1 UP)

TVC SERVO POWER 2 - AC2/MNB (1 DOWN)1 BMAG MODE - ALL ATT1/RATE2 - (3 CENTER)

TIG - 5:00 1 SPS GIMBAL MOTORS - 4 START (4 UP)ROT CONTR PWR/DIRECT - BOTH MNA/MNB (2 UP)

DSKY PRO trims attitude, "V50 N18" will continue to flash on DSKYENTRLine 1: 00204PRO, ENTR TO BYPASS DSKY blanks for a moment, GPI needles will fluctuate while gimbal test is performedLine 1: xx xx time until ignition in min/secLine 2: xxx.xx velocity to be gained in fpsLine 3: xxx.xx velocity gained in fps

TIG - 2:00 1 RATE - HIGH (UP)dV THRUST/A - NORMAL (UP)SWITCH TO TRANSLATIONAL MODE - KEYPAD "/"EMS/MODE - NORMAL (UP)

TIG - 35 sec AGC blanks for 5 seconds 35 seconds prior to ignition

TIG - 1 sec PRO executes SPS burn

DSKY FLASHING V16 N40 burn complete

MFD2 Use keypad "6" or "9" (translational thrust) until the PeA in MFD2 is close to 121.9k1 dV THRUST/A - OFF (DOWN)

SPS GIMBAL MOTORS - 4 OFF (4 DOWN)7 TVC SERVO POWER - BOTH OFF (2 CENTER)5 MAIN BUS TIE - BOTH OFF (2 DOWN)

DSKY PROFLASHING V16 N85 residual velocities

1 ATT DEADBAND - MAX (UP)TRANS CONTR PWR - OFF (DOWN)ROT CONTR PWR/DIRECT - BOTH OFF (2 CENTER)BMAG MODE - ALL RATE2 - (3 UP)

8 (cb) DIRECT ULL - BOTH OPEN (2 PULL)1 EMS/MODE - STBY (CENTER)

EMS FUNC - OFF (TURN)RATE - LOW (DOWN)SC CONT - SCS (DOWN)

DSKY PROCMC MODE - FREE (DOWN)00ESWITCH TO ROTATIONAL MODE - KEYPAD "/"

3 Record SPS Quantity in the "Flight Data" tabMFD2 Record the PeT GET, PeA, PeV, Lon and Lat in the "Flight Data" tab

Null Rotation

2nd MIDCOURSE CORRECTIONPERFORM "AGC - STATE VECTOR UPDATE" CM State Vectors, Moon SOI



MFD1 Open Interplanetary MFDClick "MNU"Click "MOD" (Configuration)Select "LambertAP Mode" and ensure "Apollo P30" is displayedSelect "P30 Comp. Mode" and ensure "1.000" is displayedClick "MNU"Click the "Course" buttonClick "NXT" until "Delta Velocity" is selectedClick "SET"Click "NXT" to highlight "Vel. Frame"Click the "+" button until "P30 LVLH" is displayedClick "PG"Click "REF" and type "Moon" in the boxClick the "Src" button and type "AS-503" in the boxClick "PG"Click "NXT" until "TEj" is highlightedUse the "+" or "-" buttons to change the Tej to 60:59:55

MFD2 Open Interplanetary MFD (these settings may have been previously configured)Click "PG" and type "0" into the box. This shares the right MFD with the data from the left MFD

Click the "MAP" buttonClick "MOD" until "Map-config" is displayedClick "NXT" until "Time limit" is displayedClick "SET" and type "600k" into the boxClick "MOD" twice to display GET, PeT, PeV, PeA, etc…Click "PG"Click the "Soi" buttonClick the "Int" buttonClick the "Plan" buttonClick "TGT" and type "moon" in the boxClick "PG"Click the "Cnt" button and type "r-moon" in the boxClick "Z+" or "Z-" to zoom in or out as necessary to more easily view the trajectory around the moon

MFD1 Modify "dVo" and "dVo" in MFD1 to adjust the PeT GET and PeA in MFD2Adjust MFD1 to aim for the following values in MFD2: PeT GET: 69:10:39 PeA: 121.9k***Try to make the PeT GET and PeA as close as possible***Continue to adjust the values in MFD1 until the values in MFD2 relate closely to those listed above. Once satisfied, continue





DSKY PROLine 1: xx xx mark counterLine 2: xx xx time until ignition in min/secLine 3: xxxxx middle gimbal anglePRO40E sets align option flag for P52



TIG - 15:00 DSKY V37E 41E do not use any time acceleration from this point until after the burnLine 1: xxx.xx roll gimbal angleLine 2: xxx.xx pitch gimbal angleLine 3: xxx.xx yaw gimbal angle


DSKY PRO AGC will automatically align CSM for the burnOnce AGC is finished aligning attitude, "V50 N18" will flash on DSKY

DSKY PRO trims attitude, "V50 N18" will continue to flash on DSKYENTRLine 1: xxxx.x dV x to be gained in ft/secLine 2: xxxx.x dV y to be gained in ft/secLine 3: xxxx.x dV z to be gained in ft/sec

1 ATT DEADBAND - MIN (DOWN)TRANS CONTR PWR - ON (UP)RATE - HIGH (UP)EMS/MODE - NORMAL (UP)

TIG - 6:00 1 BMAG MODE - ALL ATT1/RATE2 - (3 CENTER)ROT CONTR PWR/DIRECT - BOTH MNA/MNB (2 UP)SWITCH TO TRANSLATIONAL MODE - KEYPAD "/"




TIG - 0 sec MFD2 Use translational thrust until the PeA in MFD2 is close to 121.9k

DSKY PRO00E

1 BMAG MODE - ALL RATE2 - (3 UP)ATT DEADBAND - MAX (UP)TRANS CONTR PWR - OFF (DOWN)ROT CONTR PWR/DIRECT - BOTH OFF (2 CENTER)RATE - LOW (DOWN)EMS/MODE - STBY (CENTER)EMS FUNC - OFF (TURN)SC CONT - SCS (DOWN)CMC MODE - FREE (DOWN)SWITCH TO ROTATIONAL MODE - KEYPAD "/"Null Rotation

MFD2 Record the PeT GET, PeA, PeV, Lon and Lat in the "Flight Data" tab

LUNAR ORBIT INSERTION

3 SPS LINE HTRS - A (DOWN) if "SPS PRPLNT TANK/TEMP INDICATOR" 10-45 degreesSPS LINE HTRS - A/B (UP) if "SPS PRPLNT TANK/TEMP INDICATOR" below 10 degreesSPS LINE HTRS - OFF (CENTER) if "SPS PRPLNT TANK/TEMP INDICATOR" above 75 degrees

PERFORM "AGC - STATE VECTOR UPDATE" CM State Vectors, Moon SOI



MFD1 Open Interplanetary MFDClick "MNU"Click "MOD" (Configuration)Select "LambertAP Mode" and ensure "Apollo P30" is displayedSelect "P30 Comp. Mode" and ensure "1.000" is displayedClick "MNU"Click the "Course" buttonClick "NXT" until "Delta Velocity" is selectedClick "SET"Click "NXT" to highlight "TEj"Click "+" or "-" to change the Tej to "GET 69:08:20" and use "Adj" to change the increments as necessaryClick "NXT" to highlight "Vel. Frame"Click the "+" button until "P30 LVLH" is displayedSet the "dVf" to -917.3 to start withSet the "dVo" to 9.8 to start withFine-tune the "dVf" and "dVo" until the ApA in MFD1 is around 312.1k and the PeA is around 111.1k



MFD2 Record "dV x", "dV y", and "dV z" in the "Flight Data" tabPRO COMP ACTY will light for a momentLine 1: 0xxx.x predicted ApA after burn in 0.1 nmLine 2: 0xxx.x predicted PeA after burn in 0.1 nmLine 3: xxxx.x total dV in 0.1 ft/secRecord Line 3 in the "Flight Data" tab

1 EMS FUNC - dV SET/VHF RNG (TURN)

dV EMS SET - INCR or DECRIncrease until "dV RANGE" indicator displays the dV displayed in Line 3 of the DSKYEMS FUNC - dV (TURN)









MFD1 Click "PWR"MFD2 Click "SEL" and open Orbit MFD

Click "DST" to display "PeA" and "ApA"Click "FRM" to change the frame to "EQU"





TIG - 2:00 1 RATE - HIGH (UP)dV THRUST/A&B - BOTH NORMAL (2 UP)SWITCH TO TRANSLATIONAL MODE - KEYPAD "/"

EMS/MODE - NORMAL (UP)



DSKY FLASHING V16 N40 burn completeMFD2 Use keypad "6" or "9" (translational thrust) until dV/RANGE displays 0

1 dV THRUST/A&B - BOTH OFF (2 DOWN)SPS GIMBAL MOTORS - 4 OFF (4 DOWN)

7 TVC SERVO POWER - BOTH OFF (2 CENTER)5 MAIN BUS TIE - BOTH OFF (2 DOWN)






3 Record SPS Quantity in the "Flight Data" tabMFD2 Record PeA, ApA, T, Vel, and Inc from Orbit MFD to the Flight Data tab

Null Rotation

LUNAR ORBIT CIRCULARIZATION3 SPS LINE HTRS - A (DOWN) if "SPS PRPLNT TANK/TEMP INDICATOR" 10-45 degrees





MFD1 Open Interplanetary MFDClick "MNU"Click "MOD" (Configuration)Select "LambertAP Mode" and ensure "Apollo P30" is displayedSelect "P30 Comp. Mode" and ensure "1.000" is displayedClick "NXT" until "Delta Velocity" is selectedClick "SET"Click "NXT" to highlight "TEj"

Click "+" or "-" to change the Tej to match the "PeT" in MFD2 (Orbit MFD). Use "Adj" to change the increments as necessaryClick "NXT" to highlight "Vel. Frame"Click the "+" button until "P30 LVLH" is displayedSet the "dVf" to -40.8 to start withSet the "dVo" to -0.8 to start withFine-tune the "dVf" and "dVo" until the ApA in MFD1 is around 112.4k and the PeA is around 110.6k



MFD2 Record "dV x", "dV y", and "dV z" in the "Flight Data" tabPRO COMP ACTY will light for a momentLine 1: 0xxx.x predicted ApA after burn in 0.1 nmLine 2: 0xxx.x predicted PeA after burn in 0.1 nmLine 3: xxxx.x total dV in 0.1 ft/secRecord Line 3 in the "Flight Data" tab










MFD1 Click "PWR"MFD2 Click "SEL" and open Orbit MFD

Click "DST" to display "PeA" and "ApA"Click "FRM" to change the frame to "EQU"





TIG - 2:00 1 RATE - HIGH (UP)dV THRUST/A&B - BOTH NORMAL (2 UP)SWITCH TO TRANSLATIONAL MODE - KEYPAD "/"EMS/MODE - NORMAL (UP)











3 Record SPS Quantity in the "Flight Data" tabMFD2 Record PeA, ApA, T, Vel, and Inc from Orbit MFD to the Flight Data tab

Null Rotation

TRANS-EARTH INJECTION3 SPS LINE HTRS - A (DOWN) if "SPS PRPLNT TANK/TEMP INDICATOR" 10-45 degrees





Change view to the Lower Equipment Bay (below panel 122) in order to open 4 MFD'sMFD1 Open Interplanetary MFD (1st MFD Slot)

Click "MNU"Click "MOD" (Configuration)Select "LambertAP Mode" and ensure "Apollo P30" is displayedSelect "P30 Comp. Mode" and ensure "1.000" is displayedClick "MNU"

MFD2 Open Interplanetary MFD (2nd MFD Slot)Click "MNU"

MFD3 Open Interplanetary MFD (3rd MFD Slot)Click "MNU"

MFD4 Open Project Apollo MFDMFD2 Click the "BaseApproach" button, ensure "Approach for" reads "Re-Entry"

Click "PG"Click the "Src" button and type "Moon" in the boxClick "PG"Click "NXT" until "TEj" is highlightedUse the "+" or "-" buttons to change the Tej to 89:19:17Click "NXT" until "Lon" is highlightedClick "SET" and key "-179.9" in the boxClick "NXT" to highlight "Lat"Click "SET" and key "20.8" in the boxClick "NXT" to highlight "Alt" Click "SET" and key "1.3M" in the box to start withClick "NXT" to highlight "REA"Click "SET" and key "6.1" in the boxClick "NXT" to highlight "Ant" Click "SET" and key "9.89" in the box to start with

Click "NXT" to highlight "HINT" Click "+" to raise the HINT as long as the ReT GET is closest to +146:46:12Click "PRV" to highlight "Ant"Click "+" or "-" to adjust the "Ant" until the ReT GET is +146:46:12

MFD1 Click "PG" and type "2" into the box. This shares MFD1 with the data from MFD2Click the "Orbit-Eject" buttonClick "NXT" until "Higher Orbit" is highlightedClick "+" until "BaseApproach" is selectedClick "NXT" to highlight "Realtime"Click "+" to select "Off-Axis"Click "PRV" until "TEj" is highlightedClick "+" or "-" to modify the Tej until the "Enroute dV" is minimal

MFD2 Change the "TEj" until it matches the "TEj" in MFD1MFD3 Click "PG" and type "0" into the box. This shares MFD3 with the data from MFD1

Click the "MAP" buttonClick "MOD" until "Map-config" is displayedClick "NXT" until "Time limit" is displayedClick "SET" and type "300k" into the boxClick "MOD" until "ReEntry Display" is shownClick "PG"Click the "Soi" buttonClick the "Int" buttonClick the "Plan" buttonClick "REF" and type "earth" in the boxClick "PG"Click "+" or "-" to zoom in or out as necessary to more easily view your planned trajectory towards Earth

MFD2 Click "NXT" until "Alt" is highlightedClick "+" or "-" to change the Alt until the planned "ReA" in MFD3 displays around "6.1." Use "Adj" to change the increments as necessaryAdjust the "Ant" and "Alt" values until the GET in MFD3 is around +146:46:12 and the ReA is 6.1Switch back to the main panel to view the Orbit Eject MFD and Project Apollo MFD

MFD2 Click the "IMFD" buttonClick "REQ" to request burn velocities from MFD1 in ft/sec


MFD2 Record "dV x", "dV y", and "dV z" in the "Flight Data" tabPRO COMP ACTY will light for a momentLine 1: 0xxx.x predicted ApA after burn in 0.1 nmLine 2: 0xxx.x predicted PeA after burn in 0.1 nm

Line 3: xxxx.x total dV in 0.1 ft/secRecord Line 3 in the "Flight Data" tab










MFD1 Click "PWR"MFD2 Open Interplanetary MFD

Click "PG" and type "0" into the box. This shares the center MFD with the data from MFD1Click the "MAP" buttonClick "MOD" until "Map-config" is displayedClick "NXT" until "Time limit" is displayedClick "SET" and type "300k" into the boxClick "MOD" until "ReEntry Display" is shownClick "PG"Click the "Soi" buttonClick the "Int" buttonClick the "Plan" buttonClick "REF" and type "earth" in the boxClick "PG"Click "+" or "-" to zoom in or out as necessary to more easily view your planned trajectory towards Earth





TIG - 2:00 1 RATE - HIGH (UP)dV THRUST/A&B - BOTH NORMAL (2 UP)SWITCH TO TRANSLATIONAL MODE - KEYPAD "/"EMS/MODE - NORMAL (UP)











MFD2 Click the "Plan" button to disengage map planning mode and note current trajectoryRecord the ReT GET, ReV, ReA, Lon and Lat in the "Flight Data" tabNull Rotation

3rd MIDCOURSE CORRECTIONPERFORM "AGC - STATE VECTOR UPDATE" CM State Vectors, Earth SOI



MFD1 Open Interplanetary MFDClick "MNU"Click "MOD" (Configuration)Select "LambertAP Mode" and ensure "Apollo P30" is displayedSelect "P30 Comp. Mode" and ensure "1.000" is displayedClick "MNU"Click the "Course" buttonClick "NXT" until "Delta Velocity" is selectedClick "SET"Click "NXT" to highlight "Vel. Frame"Click the "+" button until "P30 LVLH" is displayedClick "PG"Click "REF" and type "Moon" in the boxClick the "Src" button and type "AS-503" in the boxClick "PG"Click "NXT" until "TEj" is highlightedUse the "+" or "-" buttons to change the Tej to 103:59:54

MFD2 Open Interplanetary MFD (these settings may have been previously configured)Click "PG" and type "0" into the box. This shares the right MFD with the data from the left MFDClick the "MAP" buttonClick "MOD" until "Map-config" is displayedClick "NXT" until "Time limit" is displayedClick "SET" and type "200k" into the boxClick "MOD" twice to display GET, PeT, PeV, PeA, etc…Click "PG"Click the "Soi" buttonClick the "Int" buttonClick the "Plan" buttonClick "TGT" and type "moon" in the boxClick "PG"Click the "Cnt" button and type "r-moon" in the boxClick "Z+" or "Z-" to zoom in or out as necessary to more easily view the trajectory around the moon

MFD1 Modify "dVo" and "dVo" in MFD1 to adjust the ReT GET and ReA in MFD2Adjust MFD1 to aim for the following values in MFD2: ReT GET: 146:46:12 ReA: 6.40***Try to make the ReT GET and ReA as close as possible***Continue to adjust the values in MFD1 until the values in MFD2 relate closely to those listed above. Once satisfied, continue


DSKY V37E 30ELine 1: 00xxx GET of burn in hoursLine 2: 000xx GET of burn in minutesLine 3: 0xx.xx GET of burn in .01 secondsInput the desired GET of the burn in hours, minutes, then seconds from MFD2V25E +00XXXE +000XXE +0XXXXERecord the GET of the burn (TeJ) from MFD1 to the "Flight Data" tabPRO

Line 1: xxxx.x dV x in 0.1 ft/secLine 2: xxxx.x dV y in 0.1 ft/secLine 3: xxxx.x dV z in 0.1 ft/secInput the desired velocities of the burn from in ft/sec from MFD2V25E (+ OR -)xxxxxE (+ OR -)xxxxxE (+ OR -)xxxxxE






TIG - 15:00 DSKY V37E 41E do not use any time acceleration from this point until after the burnLine 1: xxx.xx roll gimbal angleLine 2: xxx.xx pitch gimbal angleLine 3: xxx.xx yaw gimbal angle


DSKY PRO AGC will automatically align CSM for the burnOnce AGC is finished aligning attitude, "V50 N18" will flash on DSKY

DSKY PRO trims attitude, "V50 N18" will continue to flash on DSKYENTRLine 1: xxxx.x dV x to be gained in ft/secLine 2: xxxx.x dV y to be gained in ft/secLine 3: xxxx.x dV z to be gained in ft/sec

1 ATT DEADBAND - MIN (DOWN)TRANS CONTR PWR - ON (UP)RATE - HIGH (UP)EMS/MODE - NORMAL (UP)

TIG - 6:00 1 BMAG MODE - ALL ATT1/RATE2 - (3 CENTER)ROT CONTR PWR/DIRECT - BOTH MNA/MNB (2 UP)SWITCH TO TRANSLATIONAL MODE - KEYPAD "/"




TIG - 0 sec MFD2 Use translational thrust until the ReA in MFD2 is close to 6.40

DSKY PRO00E

1 BMAG MODE - ALL RATE2 - (3 UP)ATT DEADBAND - MAX (UP)TRANS CONTR PWR - OFF (DOWN)ROT CONTR PWR/DIRECT - BOTH OFF (2 CENTER)RATE - LOW (DOWN)EMS/MODE - STBY (CENTER)EMS FUNC - OFF (TURN)SC CONT - SCS (DOWN)CMC MODE - FREE (DOWN)SWITCH TO ROTATIONAL MODE - KEYPAD "/"

MFD2 Record the ReT GET, ReV, ReA, Lon and Lat in the "Flight Data" tabNull Rotation

INITIATE PTCPERFORM - "AGC - CONFIGURE DAP"

Null Rotation Euler AnglesObtain PTC Attitude: alpha -81.678Key "F4" and select "Custom" in the simulator menu beta -12.968Select "Scenario Editor" and click "OK" gamma 31.797Click "Orientation" and copy the Euler angles (alpha, beta, gamma) to the Euler Angles table aboveClose the Scenario Editor Windows

DSKY V16 N20ELine 1: xxx.xx IMU roll gimbal angleLine 2: xxx.xx IMU pitch gimbal angleLine 3: xxx.xx IMU yaw gimbal angleEnter the IMU roll, pitch, and yaw gimbal angles to the IMU Gimbal Angles table above

DSKY V49ELine 1: xxx.xx PTC roll angleLine 2: xxx.xx PTC pitch angleLine 3: xxx.xx PTC yaw angleKey in the DSKY the PTC roll, pitch, and yaw angles from the PTC Angles table aboveV25E +xxxxxE +xxxxxE +xxxxxE


DSKY PRO AGC will automatically align CSM to PTC attitudeOnce AGC is finished aligning attitude, "V50 N18" will flash on AGC, then proceed with following stepsENTR

8 AUTO RCS SELECT - A/C ROLL - ALL OFF (CENTER)AUTO RCS SELECT - B/D ROLL - ALL OFF (CENTER)

1 MANUAL ATTITUDE/ROLL - MIN IMP (DOWN)ROT CONTR PWR/DIRECT - BOTH MNA/MNB (2 UP)

Tap keypad "6" to initiate slow 0.1 degree per second roll rateLIMIT CYCLE - ON (UP)RATE - HIGH (UP)BMAG MODE - ALL ATT1/RATE2 (3 CENTER)

Wait roughly 20 minutes to allow pitch and yaw rates to damp, then proceed

1 SC CONT - SCS (DOWN)BMAG MODE - ALL RATE2 (3 UP)

8 AUTO RCS SELECT - ALL OFF (16 CENTER)

TERMINATE PTC1 ROT CONTR PWR/DIRECT - BOTH OFF (2 CENTER)

RATE - LOW (DOWN)LIMIT CYCLE - OFF (DOWN)MANUAL ATTITUDE/ROLL - RATE CMD (CENTER)

8 AUTO RCS SELECT - A/C ROLL - A1 & A2 - MNB (DOWN)AUTO RCS SELECT - A/C ROLL - C1 & C2 - MNA (UP)AUTO RCS SELECT - B/D ROLL - B1 & B2 - MNA (UP)AUTO RCS SELECT - B/D ROLL - D1 & D2 - MNB (DOWN)AUTO RCS SELECT - PITCH - A3 & C4 - MNB (DOWN)AUTO RCS SELECT - PITCH - C3 & A4 - MNA (UP)AUTO RCS SELECT - YAW - B3 & D4 - MNA (UP)AUTO RCS SELECT - YAW - D3 & B4 - MNB (DOWN)

1 CMC MODE - FREE (DOWN)Null Rotation

TRANS-LUNAR INJECTION

Click "+" or "-" to change the Tej to "GET 2:50:37" and use "Adj" to change the increments as necessary

Click "+" or "-" to change the TIn to "GET 69:13:58" and use "Adj" to change the increments as necessary

Click "PG" and type "0" into the box. This shares the right MFD with the data from the left MFD

Click "Z+" or "Z-" to zoom in or out as necessary to more easily view the planned trajectory to the moonClick "+" or "-" to change the TIn until the planned "PeT" in MFD2 is "69:13:58." Adjust Rad and TIn until PeA is around -241.1k and GET 69:13:58

Click "+" or "-" to fine-tune the TIn until the planned "PeT" in MFD2 is "69:13:58." Adjust Rad and TIn until PeA is around -241.1k and GET 69:13:58

PAMFD will request TLI burn data from IMFD and the SIVB IU will orient the spacecraft for TLI

do not use time acceleration from this point until after TLI burndelta velocity gained in 0.1 ft/secy velocity change in 0.1 ft/secz velocity change in 0.1 ft/sec

COMP ACTY will light for a moment

PAMFD will discontinue requesting burn data

1st MIDCOURSE CORRECTIONif "SPS PRPLNT TANK/TEMP INDICATOR" 10-45 degreesif "SPS PRPLNT TANK/TEMP INDICATOR" below 10 degreesif "SPS PRPLNT TANK/TEMP INDICATOR" above 75 degrees

CM State Vectors, Earth SOI



Click "Z+" or "Z-" to zoom in or out as necessary to more easily view the trajectory around the moonModify "TIn" to change the "PeT" in MFD2. Adjust "Rad" to change the "PeA" in MFD2. Adjust "Lat" and "Lon" to change the Lat and Lon in MFD2

PeT GET: 69:10:39 PeA: 121.9k Lon: 172.00W Lat: 8.60S***Try to make the PeT GET and PeA as close as possible, the Lon and Lat may be off by a few degrees***Continue to adjust the values in MFD1 until the values in MFD2 relate closely to those listed above. Once satisfied, continue

COMP ACTY will light for a momentpredicted ApA after burn in nmpredicted PeA after burn in nm

time until ignition in min/sec

sets align option flag for P52

AGC will automatically align CSM for burn

trims attitude, "V50 N18" will continue to flash on DSKY

DSKY blanks for a moment, GPI needles will fluctuate while gimbal test is performedtime until ignition in min/sec

2nd MIDCOURSE CORRECTIONCM State Vectors, Moon SOI


Click "Z+" or "Z-" to zoom in or out as necessary to more easily view the trajectory around the moon

PeT GET: 69:10:39 PeA: 121.9k

Continue to adjust the values in MFD1 until the values in MFD2 relate closely to those listed above. Once satisfied, continue




do not use any time acceleration from this point until after the burn

AGC will automatically align CSM for the burn


LUNAR ORBIT INSERTION

if "SPS PRPLNT TANK/TEMP INDICATOR" 10-45 degreesif "SPS PRPLNT TANK/TEMP INDICATOR" below 10 degreesif "SPS PRPLNT TANK/TEMP INDICATOR" above 75 degrees

CM State Vectors, Moon SOI


Fine-tune the "dVf" and "dVo" until the ApA in MFD1 is around 312.1k and the PeA is around 111.1k

COMP ACTY will light for a momentpredicted ApA after burn in 0.1 nmpredicted PeA after burn in 0.1 nm

LUNAR ORBIT CIRCULARIZATIONif "SPS PRPLNT TANK/TEMP INDICATOR" 10-45 degreesif "SPS PRPLNT TANK/TEMP INDICATOR" below 10 degreesif "SPS PRPLNT TANK/TEMP INDICATOR" above 75 degrees


Click "+" or "-" to change the Tej to match the "PeT" in MFD2 (Orbit MFD). Use "Adj" to change the increments as necessary

Fine-tune the "dVf" and "dVo" until the ApA in MFD1 is around 112.4k and the PeA is around 110.6k




TRANS-EARTH INJECTIONif "SPS PRPLNT TANK/TEMP INDICATOR" 10-45 degreesif "SPS PRPLNT TANK/TEMP INDICATOR" below 10 degreesif "SPS PRPLNT TANK/TEMP INDICATOR" above 75 degrees


Click "+" or "-" to zoom in or out as necessary to more easily view your planned trajectory towards Earth

Click "+" or "-" to change the Alt until the planned "ReA" in MFD3 displays around "6.1." Use "Adj" to change the increments as necessaryAdjust the "Ant" and "Alt" values until the GET in MFD3 is around +146:46:12 and the ReA is 6.1





Click "PG" and type "0" into the box. This shares the center MFD with the data from MFD1

Click "+" or "-" to zoom in or out as necessary to more easily view your planned trajectory towards Earth



3rd MIDCOURSE CORRECTIONCM State Vectors, Earth SOI


Click "Z+" or "Z-" to zoom in or out as necessary to more easily view the trajectory around the moon

ReT GET: 146:46:12 ReA: 6.40

Continue to adjust the values in MFD1 until the values in MFD2 relate closely to those listed above. Once satisfied, continue




do not use any time acceleration from this point until after the burn

AGC will automatically align CSM for the burn


INITIATE PTC

IMU Gimbal Angles PTC Anglesroll + 27333 roll + 24153

pitch + 35744 pitch + 16912yaw + 35677 yaw + 34380

Click "Orientation" and copy the Euler angles (alpha, beta, gamma) to the Euler Angles table above

AGC will automatically align CSM to PTC attitudeOnce AGC is finished aligning attitude, "V50 N18" will flash on AGC, then proceed with following steps

TERMINATE PTC

MET Panel G&N POWER DOWN1 MANUAL ATTITUDE - ALL MIN IMP (3 DOWN)8 AUTO RCS SELECT - OFF (16 CENTER)1 ROT CONTR PWR/NORMAL - BOTH CENTER (2 OFF)7 BMAG PWR - BOTH WARMUP (2 TURN)

FDAI/GPI POWER - OFF (TURN)LOGIC POWER 2/3 - OFF (DOWN)SCS ELECTRONICS POWER - OFF (TURN)SIG COND/DRIVER BIAS POWER - BOTH OFF (2 CENTER)

8 (cb) STABILIZATION CONTROL SYSTEM/LOGIC BUS - ALL OPEN (4 PULL)122 MODE - ZERO FOR 15 SECONDS (DOWN)

MODE - MANUAL (CENTER)100 G/N POWER/OPTICS - OFF (DOWN)

G/N POWER/IMU - OFF (DOWN)5 G/N PWR - OFF (CENTER)

(cb) GUIDANCE/NAVIGATION/OPTICS - BOTH OPEN (2 PULL)(cb) GUIDANCE/NAVIGATION/IMU - BOTH OPEN (2 PULL)ISS C/W light will illuminate

G&N POWER UP5 (cb) GUIDANCE/NAVIGATION/IMU - BOTH CLOSE (2 PUSH)

(cb) GUIDANCE/NAVIGATION/OPTICS - BOTH CLOSE (2 PUSH)G/N PWR - AC1 (UP)

100 G/N POWER/OPTICS - ON (UP)G/N POWER/IMU - ON (UP) (GUARDED)

8 (cb) STABILIZATION CONTROL SYSTEM/LOGIC BUS - ALL CLOSE (4 PUSH)7 LOGIC POWER 2/3 - ON (UP)

SIG COND/DRIVER BIAS POWER / 1 - AC1 (UP)SIG COND/DRIVER BIAS POWER / 2 - AC2 (DOWN)SCS ELECTRONICS POWER - GDC/ECA (TURN)BMAG PWR - BOTH ON (2 TURN)FDAI/GPI POWER - BOTH (TURN)

8 AUTO RCS SELECT - A/C ROLL - A1 & A2 - MNB (DOWN)AUTO RCS SELECT - A/C ROLL - C1 & C2 - MNA (UP)AUTO RCS SELECT - B/D ROLL - B1 & B2 - MNA (UP)AUTO RCS SELECT - B/D ROLL - D1 & D2 - MNB (DOWN)AUTO RCS SELECT - PITCH - A3 & C4 - MNB (DOWN)AUTO RCS SELECT - PITCH - C3 & A4 - MNA (UP)AUTO RCS SELECT - YAW - B3 & D4 - MNA (UP)AUTO RCS SELECT - YAW - D3 & B4 - MNB (DOWN)

1 ROT CONTR PWR/NORMAL - BOTH AC/DC (2 UP)MANUAL ATTITUDE - ALL RATE CMD (3 CENTER)

PERFORM "ALIGNMENT - P51 IMU ORIENTATION"

FUEL CELL H2 PURGE3 H2 PURGE LINE HTR - ON (UP)

Wait 20 minutesFUEL CELL INDICATOR - 1 OR 2 OR 3 (TURN)FUEL CELL PURGE - 1 OR 2 OR 3 - H2 (UP)

Possible Master Alarm - Push to turn offPurge for 1 minute, 20 secondsFUEL CELL PURGE - 1 OR 2 OR 3 - OFF (CENTER)Repeat for each fuel cellFUEL CELL INDICATOR - 2 (TURN)Wait 10 minutesH2 PURGE LINE HTR - OFF (DOWN)

FUEL CELL O2 PURGE3 FUEL CELL INDICATOR - 1 OR 2 OR 3 (TURN)

FUEL CELL PURGE - 1 OR 2 OR 3 - O2 (DOWN)Possible Master Alarm - Push to turn offPurge for 2 minutesFUEL CELL PURGE - 1 OR 2 OR 3 - OFF (CENTER)Repeat for each fuel cellFUEL CELL INDICATOR - 2 (TURN)

INITIATE BATTERY CHARGE5 (cb) BAT RLY BUS/BAT A - OPEN (PULL)

(cb) BAT RLY BUS/BAT B - OPEN (PULL)3 DC INDICATORS - BAT CHARGER (TURN)

BATTERY CHARGE - A, B, OR C (TURN)

TERMINATE BATTERY CHARGE3 BATTERY CHARGE - OFF (TURN)

DC INDICATORS - MAIN BUS A (TURN)5 (cb) BAT RLY BUS/BAT A - CLOSE (PUSH)

(cb) BAT RLY BUS/BAT B - CLOSE (PUSH)

INVERTER CHANGEOVERUse these steps for the Inverter you wish to switch TO

3 AC INVERTER - 1 OR 2 OR 3 - MNA OR MNB (UP OR DOWN)AC BUS 1 OR AC BUS 2 - 1 OR 2 OR 3 - ON (UP)Use these steps for the Inverter you wish to switch FROMAC INVERTER - 1 OR 2 OR 3 - MNA OR MNB (DOWN OR CENTER)AC BUS 1 OR AC BUS 2 - 1 OR 2 OR 3 - OFF (DOWN)

EMS TEST1 EMS FUNC - dV SET/VHF RNG (TURN)

dV EMS SET - INCR or DECRIncrease until "dV/RANGE" indicator displays the "1586.8"EMS FUNC - dV TEST (TURN)EMS/MODE - NORMAL (UP)"SPS THRUST" light will illuminate, dV/RANGE indicator will decrease. dV RANGE indicator stops at -0.1 to -41.5EMS/MODE - STBY (CENTER)EMS FUNC - OFF (TURN)

ECS REDUNDANCY TEST2 ECS INDICATORS - SEC (TURN)

SEC COOLANT LOOP/PUMP - AC1 (UP)GLY DISCH PRESS indicator - 39-51 psiACCUM PRIM/SEC H2O indicator - 30-55%SEC COOLANT LOOP - EVAP (UP)Wait 5 minutesGLY EVAP PRIM/SEC TEMP/OUTLET indicator - 38-50 °FSEC COOLANT LOOP - RESET (DOWN)Wait 1 minuteSEC COOLANT LOOP - OFF (CENTER)SEC COOLANT LOOP/PUMP - OFF (CENTER)ECS INDICATORS - PRIM (TURN)

PRIMARY EVAPORATOR TESTMinimum Load Test

MFD2 Open Project Apollo MFDClick "ECS"Click "PRM" and type "-2400" in the box Simulates minimal heat within the glycol loopsWait 30 minutes

2 ECS RAD TEMP INLET indicator - <60 °FECS RAD TEMP PRIM OUTLET indicator - -10 °FECS RADIATORS/HEATER - OFF (CENTER)ECS RAD TEMP PRIM OUTLET indicator will go off-scale low and trigger a GLYCOL TEMP LOW alarm

1,3 MASTER ALARM - PUSHECS RADIATORS/HEATER - PRIM 1 (UP)GLYCOL TEMP LOW alarm will extinguish

MFD2 Click "PRM" and type "0" in the box Returns glycol loops to normal operation

Maximum Load TestMFD2 Click "PRM" and type "3000" in the box Simulates maximum heat within the glycol loops

Wait 30 minutes2 ECS RAD TEMP INLET indicator will go off-scale high

MFD2 Click "PRM" and type "0" in the box Returns glycol loops to normal operation

G&N POWER DOWN

G&N POWER UP

FUEL CELL H2 PURGE

FUEL CELL O2 PURGE

INITIATE BATTERY CHARGE

TERMINATE BATTERY CHARGE

INVERTER CHANGEOVER

EMS TEST

"SPS THRUST" light will illuminate, dV/RANGE indicator will decrease. dV RANGE indicator stops at -0.1 to -41.5

ECS REDUNDANCY TEST

PRIMARY EVAPORATOR TEST

Simulates minimal heat within the glycol loops

ECS RAD TEMP PRIM OUTLET indicator will go off-scale low and trigger a GLYCOL TEMP LOW alarm

Returns glycol loops to normal operation

Simulates maximum heat within the glycol loops

Returns glycol loops to normal operation

MET Panel ENTRY+145:45:00 2 ECS INDICATORS - SEC (TURN)

SEC COOLANT LOOP/PUMP - AC2 (DOWN)SEC COOLANT LOOP/EVAP - EVAP (UP)SUIT CIRCUIT/HEAT EXCH - BYPASS FOR 20 SECONDS, THEN OFF (DOWN FOR 20 SEC, THEN CENTER)SUIT CIRCUIT/HEAT EXCH - ON FOR 20 SECONDS, THEN OFF (UP FOR 20 SEC, THEN CENTER)

1 CM RCS LOGIC - ON (UP)8 (cb) REACTION CONTROL SYSTEM/CM HEATER - BOTH CLOSE (2 PUSH)

101 CM RCS HTRS - ON (UP)2 RCS INDICATORS - CM/1 (TURN)

+146:00:00 101 CM RCS HTRS - OFF (DOWN)WASTE H20 DUMP - OFF (CENTER)URINE DUMP - OFF (CENTER)

1 CM RCS LOGIC - OFF (DOWN)3 DC INDICATORS - MAIN BUS B (TURN)8 (cb) REACTION CONTROL SYSTEM/CM HEATER - BOTH OPEN (2 PULL)

(cb) ELS - BOTH CLOSE (2 PUSH)(cb) SEQ EVENTS CONT SYS/LOGIC - BOTH CLOSE (2 PUSH)(cb) SEQ EVENTS CONT SYS/ARM - BOTH CLOSE (2 PUSH)SECS EVENTS CONT SYSTEM/LOGIC - BOTH ON (2 UP)

2 VERIFY CM RCS PRPLNT - BOTH ON (2 tb GRAY)CM RCS PRESS - ON (UP)

+146:10:00 325 PRIMARY GLYCOL TO RADIATORS - BYPASS (PULL)326 REPRESS PKG - FILL FOR 10 SECONDS THEN ON (TURN TWICE)

SM SUPPLY - OFF (TURN)2 SM RCS SEC PRPLNT FUEL PRESS - 4 OPEN (4 UP)

Yaw right 45 degrees, then null rotationVHF AM/A - OFF (CENTER)

5 (cb) ENVIRONMENTAL CONTROL SYS RADIATORS - CONT/HTRS - BOTH OPEN (2 PULL)(cb) ENVIRONMENTAL CONTROL SYS RADIATORS - HTRS OVLD - BOTH OPEN (2 PULL)(cb) ENVIRONMENTAL CONTROL SYSTEM/WASTE H2O URINE DUMP HTR - BOTH OPEN (2 PULL)

2 POT H20 HTR - OFF (CENTER)GLYCOL EVAP/TEMP IN - MAN (DOWN)

8 (cb) SERVICE PROPULSION SYS/PITCH - BOTH OPEN (2 PULL)(cb) SERVICE PROPULSION SYS/YAW - BOTH OPEN (2 PULL)

DSKY V37E 61ELine 1: xxx.xxLine 2: xxx.xxLine 3: xxxxxRecord Line 1 and Line 2 in the "Flight Data" tabPROLine 1: xxx.xxLine 2: xxxxxLine 3: xxx.xxRecord Line 1, Line 2, and Line 3 in the "Flight Data" tabPROLine 1: xxxx.xLine 2: xxxxx

Line 3: xx xx

+146:25:00 DSKY PROLine 1: 00041

275 (cb) FLIGHT/POST LANDING/BAT BUS A - CLOSE (PUSH)(cb) FLIGHT/POST LANDING/BAT BUS B - CLOSE (PUSH)(cb) MAIN A/BAT C - CLOSE (PUSH)(cb) MAIN B/BAT C - CLOSE (PUSH)

2 C/W - CM (DOWN)5 FUEL CELL PUMPS - ALL OFF (3 CENTER)3 FUEL CELL/MAIN BUS A/2 - OFF (DOWN)5 MAIN BUS TIE - BOTH ON (2 UP)1 CM RCS LOGIC - ON (UP)8 SECS EVENTS CONT SYSTEM/PYRO ARM - BOTH ON (2 UP)2 CSM/LM SEP/FINAL SEP - BOTH ON (2 UP)

CM/SM SEP - BOTH ON (2 UP)VERIFY BMAG MODE - 3 RATE 2 (3 UP)

2 RCS/TRNFR - CM (UP MOMENTARY)1 CM RCS LOGIC - OFF (DOWN)

DSKY PROLine 1: xxx.xxLine 2: xxx.xxLine 3: xxxxx

1 EMS FUNC - EMS TESTSlew the EMS scroll using dV/EMS SET until the yellow line is aligned with the dark line with "37" at the bottomEMS FUNC - ENTRY (TURN)EMS/MODE - NORMAL (UP)SC CONT - CMC (UP)CMC MODE - AUTO (UP)Do not use time acceleration from this point forward

DSKY PROLine 1: xxx.xxLine 2: xxxxxLine 3: xxxx.x

1 VERIFY MANUAL ATTITUDE - 3 RATE CMD (3 CENTER)ENTRY/.05 G - ON (UP)EMS ROLL - ON (UP)

".05G" light will illuminate on EMS when entry interface is reachedAGC will automatically change to P67 when .05G attained

DSKY Line 1: xxx.xxLine 2: xxxx.xLine 3: xxxx.x

AGC will change to flashing V16 N67 when velocity is less than 1000 fpsDSKY Line 1: xxxx.x

Line 2: xxx.xxLine 3: xxx.xx

50,000 ft 325 CABIN PRESSURE RELIEF (BOTH HANDLES) - BOOST/ENTRY (2 MOVE)1 ELS LOGIC - ON (UP)

ELS - AUTO (UP)2 RCS CMD - OFF (DOWN)

Landing Phase10,000 ft 3 VHF AM/A - SIMPLEX (DOWN)

VHF BCN - ON (UP)7 DIRECT O2 - OPEN (TURN HALFWAY)1 CM RCS LOGIC - ON (UP)

CM PRPLNT/DUMP - ON (UP)CM PRPLNT/PURGE - ON (UP)

3,000 ft 1 CM PRPLNT - BOTH OFF (2 DOWN)8 FLOOD - POST LDG (DOWN)1 EVENT TIMER - RESET (UP)

800 ft 325 CABIN PRESSURE RELIEF (BOTH HANDLES) - CLOSE (2 MOVE)

Splashdown 1 EVENT TIMER - START (UP)229 (cb) MAIN RELEASE - BOTH CLOSE (2 PUSH)2 MAIN RELEASE - ON (UP)8 SECS EVENTS CONT SYSTEM/PYRO ARM - BOTH SAFE (2 DOWN)

SECS EVENTS CONT SYSTEM/LOGIC - BOTH OFF (2 DOWN)(cb) PL VENT FLT/PL - CLOSE (PUSH)(cb) FLOAT BAG - 3 CLOSE (3 PUSH)

275 (cb) FLIGHT/POST LANDING/BAT C - CLOSE (PUSH)(cb) FLIGHT/POST LANDING/MAIN A - OPEN (PULL)(cb) FLIGHT/POST LANDING/MAIN B - OPEN (PULL)

5 (cb) BAT/RLY BUS - BOTH OPEN (2 PULL)325 CABIN PRESSURE RELIEF (LOWER HANDLE) - DUMP (MOVE)278 (cb) UPRIGHTING SYSTEM/COMPRESSOR - BOTH CLOSE (2 PUSH)

Record Splashdown GET (subtract event timer from mission timer) in the "Flight Data" tabRecord Line 1 and Line 2 indicated from the DSKY in the "Flight Data" tab

Proceed with following 10 minutes after splashdown

8 FLOAT BAG - ALL FILL (3 UP) FOR 7 MINUTES, THEN ALL OFF (3 DOWN)2 POST LANDING VENT VALVE UNLOCK - UNLOCK (PULL)15 POST LANDING/VENT - HIGH (UP)275 (cb) MAIN A - BOTH OPEN (2 PULL)

(cb) MAIN B - BOTH OPEN (2 PULL)(cb) FLIGHT/POST LANDING/BAT C - OPEN (PULL)

250 (cb) PYRO A/SEQ A - OPEN (PULL)(cb) PYRO B/SEQ B - OPEN (PULL)

5 MAIN BUS TIE - BOTH OFF (2 DOWN)

Crew Egress15 POST LANDING/VENT - OFF (DOWN)250 (cb) ALL OPEN (8 PULL)

SIDE HANDLE RELEASE KNOB - TURNHATCH LOCK - TURNHATCH CONTROL LEVER - OPEN (CLICK)

Mission Complete. Congratulations, you have flown Apollo 8!

ENTRY

SUIT CIRCUIT/HEAT EXCH - BYPASS FOR 20 SECONDS, THEN OFF (DOWN FOR 20 SEC, THEN CENTER)SUIT CIRCUIT/HEAT EXCH - ON FOR 20 SECONDS, THEN OFF (UP FOR 20 SEC, THEN CENTER)

(cb) REACTION CONTROL SYSTEM/CM HEATER - BOTH CLOSE (2 PUSH)

(cb) REACTION CONTROL SYSTEM/CM HEATER - BOTH OPEN (2 PULL)

(cb) SEQ EVENTS CONT SYS/LOGIC - BOTH CLOSE (2 PUSH)(cb) SEQ EVENTS CONT SYS/ARM - BOTH CLOSE (2 PUSH)SECS EVENTS CONT SYSTEM/LOGIC - BOTH ON (2 UP)

REPRESS PKG - FILL FOR 10 SECONDS THEN ON (TURN TWICE)

(cb) ENVIRONMENTAL CONTROL SYS RADIATORS - CONT/HTRS - BOTH OPEN (2 PULL)(cb) ENVIRONMENTAL CONTROL SYS RADIATORS - HTRS OVLD - BOTH OPEN (2 PULL)(cb) ENVIRONMENTAL CONTROL SYSTEM/WASTE H2O URINE DUMP HTR - BOTH OPEN (2 PULL)

(cb) SERVICE PROPULSION SYS/PITCH - BOTH OPEN (2 PULL)(cb) SERVICE PROPULSION SYS/YAW - BOTH OPEN (2 PULL)

predicted splashdown LAT in degrees + is north, - is southpredicted splashdown LON in degrees + is east, - is westroll attitude code, -00001 is down

estimated maximum G-force in G'sinertial velocity at entry interface in ft/secentry angle in degrees

range from .05G's to splashdown in nminertial velocity at .05G's in ft/sec

time til .05G in min/sec

code for "Perform CSM Separation"(cb) FLIGHT/POST LANDING/BAT BUS A - CLOSE (PUSH)(cb) FLIGHT/POST LANDING/BAT BUS B - CLOSE (PUSH)

SECS EVENTS CONT SYSTEM/PYRO ARM - BOTH ON (2 UP)jettisons docking probe

splashdown LAT in degrees + is north, - is southsplashdown LON in degrees + is east, - is westroll attitude code, -00001 is down

Slew the EMS scroll using dV/EMS SET until the yellow line is aligned with the dark line with "37" at the bottom

AGC will align CM for entryG force in G'sinertial velocity in ft/secrange to splashdown in nm

VERIFY MANUAL ATTITUDE - 3 RATE CMD (3 CENTER)

".05G" light will illuminate on EMS when entry interface is reached

commanded bank angle in degreesestimated cross-range error in nmestimated down-range error in nm

AGC will change to flashing V16 N67 when velocity is less than 1000 fpsrange from target in nmpresent LAT in degrees + is north, - is southpresent LON in degrees + is east, - is west

CABIN PRESSURE RELIEF (BOTH HANDLES) - BOOST/ENTRY (2 MOVE)

CABIN PRESSURE RELIEF (BOTH HANDLES) - CLOSE (2 MOVE)

SECS EVENTS CONT SYSTEM/PYRO ARM - BOTH SAFE (2 DOWN)SECS EVENTS CONT SYSTEM/LOGIC - BOTH OFF (2 DOWN)

CABIN PRESSURE RELIEF (LOWER HANDLE) - DUMP (MOVE)(cb) UPRIGHTING SYSTEM/COMPRESSOR - BOTH CLOSE (2 PUSH)Record Splashdown GET (subtract event timer from mission timer) in the "Flight Data" tabRecord Line 1 and Line 2 indicated from the DSKY in the "Flight Data" tab

FLOAT BAG - ALL FILL (3 UP) FOR 7 MINUTES, THEN ALL OFF (3 DOWN)POST LANDING VENT VALVE UNLOCK - UNLOCK (PULL)

opens hatch

Mission Complete. Congratulations, you have flown Apollo 8!

FLIGHT DATAInsertionPeA (Orbit MFD) 183.0 kmApA (Orbit MFD) 199.5 kmT (Orbit MFD) 5293 secVel (Orbit MFD) 7798 m/secInc (Orbit MFD) 31.93 deg

Trans-Lunar InjectionGET of Ignition (Maneuver Tab/PAMFD) hours mindV x (PAMFD) ft/secdV y (PAMFD) ft/secdV z (PAMFD) ft/secPlanned PeT GET 69 hours 13 min 58Planned PeA -241.1 kmPlanned Pericinthion Lon (- = W) 178.47 degPlanned Pericinthion Lat (- = S) 0.69 degPeT GET (IMFD Map) after burn hours minPeA (IMFD Map) after burn kmPeV (IMFD Map) after burn m/secLon (IMFD Map) after burn (- = W) degLat (IMFD Map) after burn (- = S) deg

1st Midcourse CorrectionGET of Ignition (Maneuver Tab) hours mindV x (PAMFD/DSKY) ft/secdV y (PAMFD/DSKY) ft/secdV z (PAMFD/DSKY) ft/sectotal dV (DSKY/dV RANGE) ft/secSPS Quantity (panel 3) prior to burn %Planned PeT GET 69 hours 10 min 39Planned PeA 121.9 kmPlanned Pericinthion Lon (- = W) -172.00 degPlanned Pericinthion Lat (- = S) -8.60 degSPS Quantity (panel 3) after burn %PeT GET (IMFD Map) after burn hours minPeA (IMFD Map) after burn kmPeV (IMFD Map) after burn m/secLon (IMFD Map) after burn (- = W) degLat (IMFD Map) after burn (- = S) deg

2nd Midcourse CorrectionGET of Ignition (Maneuver Tab) hours mindV x (PAMFD/DSKY) ft/secdV y (PAMFD/DSKY) ft/secdV z (PAMFD/DSKY) ft/sectotal dV (DSKY/dV RANGE) ft/secPlanned PeT GET 69 hours 10 min 39Planned PeA 121.9 kmPlanned Pericinthion Lon (- = W) -172.00 deg

Planned Pericinthion Lat (- = S) -8.60 degPeT GET (IMFD Map) after burn hours minPeA (IMFD Map) after burn kmPeV (IMFD Map) after burn m/secLon (IMFD Map) after burn (- = W) degLat (IMFD Map) after burn (- = S) deg

Lunar Orbit InsertionGET of Ignition (Maneuver Tab) hours minPlanned ApA 312.1 kmPlanned PeA 111.1 kmdV x (PAMFD/DSKY) ft/secdV y (PAMFD/DSKY) ft/secdV z (PAMFD/DSKY) ft/sectotal dV (DSKY/dV RANGE) ft/secSPS Quantity (panel 3) prior to burn %SPS Quantity (panel 3) after burn %PeA (Orbit MFD) after burn kmApA (Orbit MFD) after burn kmT (Orbit MFD) after burn secVel (Orbit MFD) after burn m/secInc (Orbit MFD) after burn deg

Lunar Orbit CircularizationGET of Ignition (Maneuver Tab) hours minPlanned ApA 112.4 kmPlanned PeA 110.6 kmdV x (PAMFD/DSKY) ft/secdV y (PAMFD/DSKY) ft/secdV z (PAMFD/DSKY) ft/sectotal dV (DSKY/dV RANGE) ft/secSPS Quantity (panel 3) prior to burn %SPS Quantity (panel 3) after burn %PeA (Orbit MFD) after burn kmApA (Orbit MFD) after burn kmT (Orbit MFD) after burn secVel (Orbit MFD) after burn m/secInc (Orbit MFD) after burn deg

Trans-Earth InjectionGET of Ignition (Maneuver Tab) hours mindV x (PAMFD/DSKY) ft/secdV y (PAMFD/DSKY) ft/secdV z (PAMFD/DSKY) ft/sectotal dV (DSKY/dV RANGE) ft/secSPS Quantity (panel 3) prior to burn %Planned ReT GET 146 hours 46 min 12Planned ReA 6.10 degSPS Quantity (panel 3) after burn %ReT GET (IMFD Map) after burn hours min

ReV (IMFD Map) after burn m/secReA (IMFD Map) after burn degLon (IMFD Map) after burn (- = W) degLat (IMFD Map) after burn (- = S) deg

3rd Midcourse CorrectionGET of Ignition (Maneuver Tab) hours mindV x (PAMFD/DSKY) ft/secdV y (PAMFD/DSKY) ft/secdV z (PAMFD/DSKY) ft/sectotal dV (DSKY/dV RANGE) ft/secPlanned ReT GET 146 hours 46 min 12Planned ReA 6.40 degReT GET (IMFD Map) after burn hours minReV (IMFD Map) after burn m/secReA (IMFD Map) after burn degLon (IMFD Map) after burn (- = W) degLat (IMFD Map) after burn (- = S) deg

Entry PhasePredicted splashdown LAT (DSKY) degPredicted splashdown LON (DSKY) degEstimated Maximum G's (DSKY) G'sInertial Velocity at Entry Interface (DSKY) ft/secEntry Angle (DSKY) deg

Landing PhaseSplashdown GET (Deorbit Tab) hours minSplashdown LAT (DSKY) degSplashdown LON (DSKY) deg

SYSTEMS CHECKSPS CHECK 1 2 3 4 5

3 SPS PRPLNT TANK/TEMP - RECORD °FSPS/PRESS IND - N2 A (CENTER)SPS PRPLNT TANK/PRESS/He - RECORD PSIASPS/PRESS IND - N2 B (DOWN)SPS PRPLNT TANK/PRESS/He - RECORD PSIASPS/PRESS IND - He (UP)SPS PRPLNT TANK/PRESS/He - RECORD PSIASPS PRPLNT TANK/PRESS/FUEL - 170 to 195 PSIASPS PRPLNT TANK/PRESS/OXID - 170 to 195 PSIAVERIFY SPS ENGINE INJECTOR VALVES - 4 CLOSEVERIFY OXID UNBAL - 0 LBSVERIFY OXID FLOW VALVE - PRIM (UP)SPS QUANTITY - RECORD %VERIFY SPS He VLV - BOTH AUTO (2 UP)

SM RCS CHECK 1 2 3 4 52 VERIFY SM RCS HELIUM 1&2 tb - 8 GRAY

VERIFY SM RCS PRIM & SEC PRPLNT tb - 8 GRAYVERIFY RCS INDICATORS - SM/A (TURN)SM RCS/PKG TEMP - RECORD TEMPSM RCS/PRESS/He - RECORD PSIASM RCS/SEC FUEL - 178 to 192 PSIASM RCS IND - He TK TEMP (UP)SM RCS/He TK TEMP - RECORD °FSM RCS IND - PRPLNT QTY (DOWN)SM RCS/PRPLNT QTY - RECORD lbsRCS INDICATORS - SM/B (TURN)SM RCS/PKG TEMP - RECORD TEMPSM RCS/PRESS/He - RECORD PSIASM RCS/SEC FUEL - 178 to 192 PSIASM RCS IND - He TK TEMP (UP)SM RCS/He TK TEMP - RECORD °FSM RCS IND - PRPLNT QTY (DOWN)SM RCS/PRPLNT QTY - RECORD lbsRCS INDICATORS - SM/C (TURN)SM RCS/PKG TEMP - RECORD TEMPSM RCS/PRESS/He - RECORD PSIASM RCS/SEC FUEL - 178 to 192 PSIASM RCS IND - He TK TEMP (UP)SM RCS/He TK TEMP - RECORD °FSM RCS IND - PRPLNT QTY (DOWN)SM RCS/PRPLNT QTY - RECORD lbsRCS INDICATORS - SM/D (TURN)SM RCS/PKG TEMP - RECORD TEMPSM RCS/PRESS/He - RECORD PSIASM RCS/SEC FUEL - 178 to 192 PSIASM RCS IND - He TK TEMP (UP)SM RCS/He TK TEMP - RECORD °FSM RCS IND - PRPLNT QTY (DOWN)SM RCS/PRPLNT QTY - RECORD lbsRCS INDICATORS - SM/A (TURN)

CM RCS CHECK2 VERIFY CM RCS PRPLNT tb - 2 GRAY

RCS INDICATORS - CM/1 (TURN)CM RCS/He TEMP - 60 to 90°FCM RCS/PRESS/He - 4100 to 4200 PSIACM RCS/PRESS/MANF - 20 to 105 PSIARCS INDICATORS - CM/2 (TURN)CM RCS/He TEMP - 60 to 90°FCM RCS/PRESS/He - 4100 to 4200 PSIACM RCS/PRESS/MANF - 20 to 105 PSIA

EPS CHECK 1 2 3 4 55 VERIFY MAIN BUS TIE - BOTH OFF (2 DOWN)2 CRYOGENIC TANKS/PRESSURE/H2 1&2 - 225 to 260 PSIA

CRYOGENIC TANKS/PRESSURE/O2 1&2 - 865 to 935 PSIA

O2 PRESS IND - SURGE TANK (DOWN)CRYOGENIC TANKS/PRESSURE/O2 1 - 865 to 935 PSIAO2 PRESS IND - TANK 1 (UP)CRYOGENIC TANKS/QUANTITY/H2 1&2 - RECORD %CRYOGENIC TANKS/QUANTITY/O2 1&2 - RECORD %VERIFY H2 FANS - BOTH AUTO (2 UP)VERIFY O2 FANS - BOTH AUTO (2 UP)

3 VERIFY FUEL CELL HEATERS - ALL ON (3 UP)VERIFY FUEL CELL RADIATORS tb - 3 GRAYVERIFY FUEL CELL REACTANTS tb - 3 GRAYFUEL CELL INDICATOR - 1 (TURN)FUEL CELL/FLOW/H2 - RECORD LBS/HRFUEL CELL/FLOW/O2 - RECORD LBS/HRFUEL CELL/MODULE TEMP/SKIN - 400 to 500°FFUEL CELL/MODULE TEMP/COND EXH - 160 to 170°FFUEL CELL INDICATOR - 2 (TURN)FUEL CELL/FLOW/H2 - 0.03 to 0.15 LBS/HRFUEL CELL/FLOW/O2 - 0.25 to 1.2 LBS/HRFUEL CELL/MODULE TEMP/SKIN - 400 to 500°FFUEL CELL/MODULE TEMP/COND EXH - 160 to 170°FFUEL CELL INDICATOR - 3 (TURN)FUEL CELL/FLOW/H2 - 0.03 to 0.15 LBS/HRFUEL CELL/FLOW/O2 - 0.25 to 1.2 LBS/HRFUEL CELL/MODULE TEMP/SKIN - 400 to 500°FFUEL CELL/MODULE TEMP/COND EXH - 160 to 170°FFUEL CELL INDICATOR - 2 (TURN)VERIFY pH HI tb - GRAYVERIFY FC RAD TEMP LO tb - GRAYVERIFY FUEL CELL/MAIN BUS A tb - 1 & 2 GRAY, 3 bpVERIFY FUEL CELL/MAIN BUS B tb - 1 & 2 bp, 3 GRAYDC INDICATORS - FUEL CELL 1 - RECORD DC AMPSDC INDICATORS - FUEL CELL 2 - RECORD DC AMPSDC INDICATORS - FUEL CELL 3 - RECORD DC AMPSDC INDICATORS - MAIN BUS A - RECORD DC VOLTSDC INDICATORS - MAIN BUS B - RECORD DC VOLTSDC INDICATORS - BAT BUS A - RECORD DC VOLTSDC INDICATORS - BAT BUS B - RECORD DC VOLTSDC INDICATORS - BAT C - 36 to 38 VOLTSDC INDICATORS - PYRO BAT A - 36.5 to 37.5 VOLTSDC INDICATORS - PYRO BAT B - 36.5 to 37.5 VOLTSDC INDICATORS - MAIN BUS A - (TURN)

101 SYSTEM TEST - 4B (BAT RELAY BUS VOLTAGE) - 3.4 to 4.1 VOLTSSYSTEM TEST - 4A (BAT COMPT PRESS) - BELOW 1.5 VOLTS

3 AC INDICATOR - TURN - 113 to 117 VOLTS FOR EACH PHASE

ECS CHECK 1 2 3 4 52 SUIT CABIN ∆P - -1 to -3.5 IN H2O

O2 FLOW - 0.2 to 0.45 LB/HRVERIFY ECS RADIATORS tb - GRAYVERIFY ECS INDICATORS - PRIM

ECS RADIATOR TEMP/PRIM/SEC/INLET - RECORD °FECS RADIATOR TEMP/PRIM/OUTLET - RECORD °FGLY EVAP PRIM/SEC/STEAM PRESS - .10 to .20 PSIAGLY DISCH/PRESS - RECORD PSIATEMP/SUIT - RECORD °FTEMP/CABIN - RECORD °FPRESS/SUIT - RECORD PSIAPRESS/CABIN - RECORD PSIAPART PRESS CO2 - RECORD mm HgSUIT COMPR ∆P - .3 to .5 PSIACCUM PRIM/SEC/QUANTITY - 30 to 65%If below 30%

379 PRIM ACCUM FILL - ON (TURN) UNTIL ACCUM QUANTITY 45 to 55%, THEN OFF (TURN)2 H2O QTY IND - POT (UP)

H2O/QUANTITY - 10 to 100%H2O QTY IND - WASTE (DOWN)H2O/QUANTITY - 25 to 85%If above 85%

251 WASTE MANAGEMENT/OVBD DRAIN - DUMP (TURN) UNTIL H2O/QUANTITY 25%, THEN OFF (TURN)

FLIGHT DATA

sec

sec

sec

sec

sec

sec

sec

sec

sec

sec

sec

sec

sec

sec

sec

sec

sec

sec

SYSTEMS CHECK6 7 8 9 10 11 12

6 7 8 9 10 11 12

6 7 8 9 10 11 12

WASTE MANAGEMENT/OVBD DRAIN - DUMP (TURN) UNTIL H2O/QUANTITY 25%, THEN OFF (TURN)

MET Panel SEPARATION+003:10:00 1 EMS FUNC - dV (TURN)

2 H2 FANS - BOTH AUTO (2 UP)O2 FANS - BOTH AUTO (2 UP)

8 AUTO RCS SELECT - A/C ROLL - A1 & A2 - MNB (DOWN)AUTO RCS SELECT - A/C ROLL - C1 & C2 - MNA (UP)

3 FC REACS VALVES - LATCH (DOWN)2 RCS CMD - ON (UP MOMENTARY)

DSKY V66E1 EMS MODE - NORMAL (UP)

+003:21:00 1 CSM/LV SEP - PUSH3 S BAND ANTENNA/OMNI - C (DOWN)

225 (cb) HIGH GAIN ANTENNA/FLT BUS - CLOSE (PUSH)(cb) HIGH GAIN ANTENNA/GROUP 2 - CLOSE (PUSH)

2 HIGH GAIN ANTENNA/TRACK - MAN (CENTER)HIGH GAIN ANT/POWER - ON (UP)HIGH GAIN ANTENNA/PITCH POSITION - -30 (TURN)HIGH GAIN ANTENNA/YAW POSITION - 300 (TURN)

3 S BAND ANTENNA - HI GAIN (DOWN)2 HIGH GAIN ANTENNA/TRACK - REACQ (DOWN)8 SECS EVENTS CONT SYSTEM/PYRO ARM - BOTH SAFE (2 DOWN)

SECS EVENTS CONT SYSTEM/LOGIC - BOTH OFF (2 DOWN)7 EDS POWER - OFF (DOWN)

(cb) EDS - 3 OPEN (3 PULL)3 TAPE RECORDER/RECORD - OFF (CENTER)8 (cb) SEQ EVENTS CONT SYS/ARM - BOTH OPEN (2 PULL)

(cb) SEQ EVENTS CONT SYS/LOGIC - BOTH OPEN (2 PULL)7 TVC SERVO POWER/1 - OFF (CENTER)1 LV/SPS IND - GPI (DOWN)

RATE - LOW (DOWN)3 FC REACS VALVES - NORM (UP)1 ATT DEADBAND - MAX (UP)

TRANS CONTR PWR - OFF (DOWN)ROT CONTR PWR/DIRECT - BOTH OFF (2 CENTER)EMS/MODE - STBY (CENTER)EMS FUNC - OFF (TURN)Null Rotation

SEPARATION

AUTO RCS SELECT - A/C ROLL - A1 & A2 - MNB (DOWN)

updates SIVB state vector to match current CSM state vector

SECS EVENTS CONT SYSTEM/PYRO ARM - BOTH SAFE (2 DOWN)SECS EVENTS CONT SYSTEM/LOGIC - BOTH OFF (2 DOWN)

(cb) SEQ EVENTS CONT SYS/ARM - BOTH OPEN (2 PULL)(cb) SEQ EVENTS CONT SYS/LOGIC - BOTH OPEN (2 PULL)

MET Panel ABORT MODE 1A1 ABORT PUSHBUTTON - PUSH

Wait for event timer to read 14 seconds2 TWR JETT - BOTH ON (2 UP)1 ELS LOGIC - ON (UP)

PERFORM "DEORBIT - LANDING PHASE"

ABORT MODE 1B1 ABORT PUSHBUTTON - PUSH

Wait for event timer to read 11 seconds2 TWR JETT - BOTH ON (2 UP)1 ELS LOGIC - ON (UP)2 RCS/CMD - ON (UP)


ABORT MODE 1C1 ABORT PUSHBUTTON - PUSH2 RCS/CMD - ON (UP)

Wait for event timer to read 11 secondsTWR JETT - BOTH ON (2 UP)CM RCS PRESS - ON (UP)RCS/TRNFR - ON (UP)CAUTION/WARNING - CM (DOWN)

1 MANUAL ATTITUDE/PITCH - RATE CMD (CENTER)BMAG MODE - ALL ATT1/RATE2 (3 CENTER)EMS FUNC - ENTRY (TURN)EMS MODE - NORMAL (UP)

2 RCS INDICATORS - CM/1 (TURN)Wait for ".05G" light to illuminate on EMSENTRY/.05 G - ON (UP)


ABORT MODE 21 ABORT PUSHBUTTON - PUSH

SWITCH TO TRANSLATIONAL MODE - KEYPAD "/"APPLY 24 SECONDS FORWARD RCS THRUST - KEYPAD "6"SWITCH TO ROTATIONAL MODE - KEYPAD "/"YAW LEFT 45 DEGREES THEN NULL ROTATIONBMAG MODE - ALL ATT1/RATE2 (3 CENTER)

275 (cb) MAIN A/BAT C - CLOSE (PUSH)(cb) MAIN B/BAT C - CLOSE (PUSH)

2 CAUTION/WARNING - CM (DOWN)CM/SM SEP - BOTH ON (2 UP)CM RCS PRESS - ON (UP)RCS/TRNFR - CM (UP)RCS INDICATORS - CM/1 (TURN)

EMS FUNC - ENTRY (TURN)EMS MODE - NORMAL (UP)Wait for ".05G" light to illuminate on EMSENTRY/.05 G - ON (UP)EMS ROLL - ON (UP)


GIMBAL LOCK RECOVERYDSKY Verify "NO ATT" and "GIMBAL LOCK" lights lit on AGC

1 IMU CAGE - ON (UP)Use rotational RCS thrust to orient general direction of CSM progradeIMU CAGE - OFF (DOWN) (GUARDED)

PERFORM "ALIGNMENT - P53 ALIGNMENT"

CMC RESTARTDSKY V36E

PERFORM "AGC - STATE VECTOR UPDATE"

Roll, Pitch, and Yaw CSM until FDAI 2 is centeredV41 N20ELine 1: BlankLine 2: BlankLine 3: Blank+00000E +00000E +00000EV40 N20EV25 N07E77E, 10000E, 1EV37E 51EPRO

DSKY V37E 00EV48EPROPROPROV46E

PERFORM "ALIGNMENT - P51 IMU ORIENTATION"

CMC CLOCK UPDATEDSKY V16 N65E

Line 1: 00xxxLine 2: 000xxLine 3: 0xx.xxNote the difference in time between the mission timer and the DSKYV55ELine 1: BlankLine 2: Blank

Line 3: BlankKey in the noted difference in time between the mission timer and the DSKYV25E +00000E (+or-)000(minutes)E (+or-)0(seconds)00EV16 N65ELine 1: 00xxxLine 2: 000xxLine 3: 0xx.xxV37E 00E

ABORT MODE 1A

ABORT MODE 1B

ABORT MODE 1C

ABORT MODE 2

APPLY 24 SECONDS FORWARD RCS THRUST - KEYPAD "6"

GIMBAL LOCK RECOVERY

Use rotational RCS thrust to orient general direction of CSM prograde

CMC RESTARTresets CMC

check in IMFD map program to determine of CSM is in Earth SOI or Moon SOI

roll angle in .01 degreespitch angle in .01 degreesyaw angle in .01 degreesloads centered alignment angle from FDAI 2, FDAI 1 will realign, NO ATT alarm will lightzeroes ICDU angles, wait for V40 N20 to dim

sets REFSMMAT flag

sets drift flagCOMP ACTY may light for a few moments

reactivates DAP

CMC CLOCK UPDATE

mission time in hoursmission time in minutesmission time in seconds

Note the difference in time between the mission timer and the DSKYDSKY will display flashing V21 N24mission time in hoursmission time in minutes

mission time in secondsKey in the noted difference in time between the mission timer and the DSKY

mission time in hoursmission time in minutesmission time in seconds

Welcome aboard Apollo 8!

MISSION SUMMARY

One of the most groundbreaking missions in the Apollo program was undoubtedly Apollo 8. Not only was this the first manned mission to ever leave Earth orbit, but it

marked the first time in history that humans would enter the gravitational influence of another celestial body. Apollo 8 had also set several records which were never

attained previously, such as human relative speed and altitude. The objectives of this mission were met with great success, and Apollo 8 (although shadowed in some

respects by Apollo 11) is still regarded by many today as one of the more important events in human history.

WHAT YOU WILL PERFORM

Assuming the role of Frank Borman, Jim Lovell, and Bill Anders, you will begin the mission riding one of the most powerful vehicles designed by man, the Saturn V

rocket, into Earth orbit. You will then compute and initiate a maneuver which will set you on a trajectory towards the moon, called the Trans-Lunar Injection (TLI) burn.

After TLI, you will separate the CSM from the SIVB booster stage and perform other housekeeping tasks. Eleven hours into the mission, you will perform a SPS burn to

modify your trajectory towards the Moon, referred to as a Midcourse Correction, or MCC. Also, during much of the Trans-Lunar Coast (TLC), you will perform star

sighting for state vector verification and PTC (Passive Thermal Control) maneuvers, or "Barbecue Roll," to evenly heat the skin of the CSM as it comes into contact

with sunlight. On the third day of the mission, you will begin preparations to enter the Moon's sphere of influence by performing another MCC. Once you reach the time

of perilune (the point which you are closest to the lunar surface), you will perform a long SPS burn to establish orbit around the Moon, called Lunar Orbit Insertion (LOI).

At the time of the next perilune, you will perform yet another burn to establish a nearly circular 60nm (121.3km) orbit around the Moon, called LOC, or Lunar Orbit

Circularization. Much of the lunar orbital period on the fourth day of the mission will be devoted to landmark and future landing point sighting and photography, then

calculating and performing the Trans-Earth Injection (TEI) maneuver, a long burn which will set you on a trajectory adequate for splashdown. Later, you will perform a

final MCC which will fine tune your re-entry angle and coordinates for splashdown. You will perform additional star sighting and PTC maneuvers, until the time of entry

preparation, where you will separate the Command Module from the Service Module and re-enter Earth's atmosphere.

WHAT YOU WILL LEARN

If this is your first time flying a Project Apollo scenario, it is recommended that you complete Apollo 7 prior to attempting Apollo 8. The following are some of the new

features you will likely become proficient with over the previous scenario:

* Using IMFD to calculate high-precision trajectories and integrate its values (using Project Apollo MFD) into the vAGC for performing maneuvers.* Passive Thermal Control (PTC)

* The High Gain Antenna (once implemented)

* Trans-Lunar Injection (TLI)

* Midcourse Corrections (MCC's)

* Lunar Orbit Insertion (LOI)

* Lunar Orbit Circularization (LOC)

* Trans-Earth Injection (TEI)

* Monitoring your trajectory, GET of periapsis/perilune (PeA, PeT), and re-entry angle (ReA) in the IMFD Map program.

This mission is different from Apollo 7 in many respects, most notably that only a small portion of Apollo 8 takes place in Earth orbit. You will come to rely on MFD's

more on Apollo 8 than on the previous mission, due to the intricacy and accuracy of the maneuvers that must be performed. In Apollo 8, the most acute changes in

velocity could greatly impact conditions later on. For example, during Trans-Lunar Coast, while closer to Earth than the Moon, a small change in your velocity will have

a much larger impact on your perilune altitude and time once you reach the moon. In contrast, when you are closer to the Moon, the same change in velocity would have

a smaller impact. This is where the IMFD Map program will become invaluable to monitoring your trajectory during coasting periods. Its use is included in the procedures,

as well as a few reminders to monitor your trajectory when necessary for future events.

Good luck, and godspeed on Apollo 8!

INITIAL CONFIGURATION

- Ensure you have downloaded the latest Project Apollo beta modules or have built the modules yourself with no errors

- Ensure you have downloaded and installed the latest version of Interplanetary MFD (IMFD) from Jarmo Nikkanen at http://koti.mbnet.fi/jarmonik/Orbiter.html

- Start Orbiter

- On the Orbiter Launchpad, click the "Parameters" tab

- Ensure the Complex Flight Model, Limited Fuel, and Nonspherical Gravity Sources boxes are checked

- On the "Modules" tab, ensure that InterplanetaryMFD, OrbiterSound, ProjectApolloMFD, and ScnEditor modules are active

- Open your Apollo 8 vAGC Launch scenario under the scenario tab

- Press F4 to open the simulator menu

- Click the "Camera" button, then click "FOV"

- Use the slider or type "45" in the box to change the field of view to 45 degrees

- Close the simulator menu windows and proceed with the flightplan

One of the most groundbreaking missions in the Apollo program was undoubtedly Apollo 8. Not only was this the first manned mission to ever leave Earth orbit, but it

marked the first time in history that humans would enter the gravitational influence of another celestial body. Apollo 8 had also set several records which were never

attained previously, such as human relative speed and altitude. The objectives of this mission were met with great success, and Apollo 8 (although shadowed in some

Assuming the role of Frank Borman, Jim Lovell, and Bill Anders, you will begin the mission riding one of the most powerful vehicles designed by man, the Saturn V

rocket, into Earth orbit. You will then compute and initiate a maneuver which will set you on a trajectory towards the moon, called the Trans-Lunar Injection (TLI) burn.

After TLI, you will separate the CSM from the SIVB booster stage and perform other housekeeping tasks. Eleven hours into the mission, you will perform a SPS burn to

modify your trajectory towards the Moon, referred to as a Midcourse Correction, or MCC. Also, during much of the Trans-Lunar Coast (TLC), you will perform star

sighting for state vector verification and PTC (Passive Thermal Control) maneuvers, or "Barbecue Roll," to evenly heat the skin of the CSM as it comes into contact

with sunlight. On the third day of the mission, you will begin preparations to enter the Moon's sphere of influence by performing another MCC. Once you reach the time

of perilune (the point which you are closest to the lunar surface), you will perform a long SPS burn to establish orbit around the Moon, called Lunar Orbit Insertion (LOI).

At the time of the next perilune, you will perform yet another burn to establish a nearly circular 60nm (121.3km) orbit around the Moon, called LOC, or Lunar Orbit

Circularization. Much of the lunar orbital period on the fourth day of the mission will be devoted to landmark and future landing point sighting and photography, then

calculating and performing the Trans-Earth Injection (TEI) maneuver, a long burn which will set you on a trajectory adequate for splashdown. Later, you will perform a

final MCC which will fine tune your re-entry angle and coordinates for splashdown. You will perform additional star sighting and PTC maneuvers, until the time of entry

If this is your first time flying a Project Apollo scenario, it is recommended that you complete Apollo 7 prior to attempting Apollo 8. The following are some of the new

This mission is different from Apollo 7 in many respects, most notably that only a small portion of Apollo 8 takes place in Earth orbit. You will come to rely on MFD's

more on Apollo 8 than on the previous mission, due to the intricacy and accuracy of the maneuvers that must be performed. In Apollo 8, the most acute changes in

velocity could greatly impact conditions later on. For example, during Trans-Lunar Coast, while closer to Earth than the Moon, a small change in your velocity will have

a much larger impact on your perilune altitude and time once you reach the moon. In contrast, when you are closer to the Moon, the same change in velocity would have

a smaller impact. This is where the IMFD Map program will become invaluable to monitoring your trajectory during coasting periods. Its use is included in the procedures,

- Ensure you have downloaded and installed the latest version of Interplanetary MFD (IMFD) from Jarmo Nikkanen at http://koti.mbnet.fi/jarmonik/Orbiter.html

Trans-Lunar Maneuver Summary

Ignition Time Time, Local Velocities, ft/sec VelocityManeuver Hrs Min Sec Sec X Y Z Change

ft/secTrans-Lunar Injection 0 0 0 0.0 0.0 0.0

First MidcourseCorrection 0 0 0 0.0 0.0 0.0 0.0 0.0

Second Midcourse 0 0 0 0.0 0.0 0.0 0.0Correction

Lunar Orbit Maneuver Summary


ft/secLunar OrbitInsertion 0 0 0 0.0 0.0 0.0 0.0 0.0

Lunar OrbitInsertion 0 0 0 0.0 0.0 0.0 0.0 0.0

Trans-Earth Maneuver Summary


ft/secTrans-EarthInjection 0 0 0 0.0 0.0 0.0 0.0 0.0

Third MidcourseCorrection 0 0 0 0.0 0.0 0.0 0.0

Entry Interface Splashdown

Time, hr:min:sec 0 0 0 Time, hr:min:sec 0 0Velocity, ft/sec 0 Predicted Lat/Lon 0.00

Entry Angle, deg 0.00 Actual Lat/Lon 0.00Maximum G-force 0.00

Cryogenic Storage

Oxygen, lb Hydrogen, lbLoaded prior to flight 639.4 51.5Quantity Used 639.4 51.5Quantity Remaining 0.0 0.0

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

Fuel Cell Bus Amperage

Fuel Cell 1Fuel Cell 2

Am

pera

ge

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

Battery Voltage

Battery A

Battery B

Volt

s

Service Module RCS

Propellant loaded, lbs 1600.0Propellant Used, lbs 1600.0Propellant Remaining, lbs 0.0

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

Cryogenic Quantity Remaining

Hydrogen

Oxygen

Perc

ent

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

Service Module RCS Package Temperature

Quad A

Quad B

Quad C

Quad D

Tem

pera

ture

°F

0

2

4

6

8

10

12

Service Module RCS Helium Tank Temperature

Quad A

Quad B

Quad C

Quad D

Tem

pera

ture

°F

Service Propulsion System

Oxidizer, lbs Fuel, lbsLoaded prior to flight 25105.1 15730.9Quantity Used 25105.1 15730.9Quantity Remaining 0.0 0.0

Environmental Control System

0

2

4

6

8

10

12


Quad A

Quad B

Quad C

Quad D

Tem

pera

ture

°F

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

SPS Propellant Tank Temperature

Tem

pera

ture

°F

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

Primary Evaporator PerformanceInlet

Outlet

Tem

pera

ture

°F

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

Suit and Cabin Pressure Suit PressureCabin Pressure

Pre

ssure

, psi

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

Suit and Cabin TemperatureSuit Temper-ature

Tem

pera

ture

°F

Trans-Lunar Maneuver Summary

Resultant Pericinthion ConditionsAltitude Velocity Lat. Lon. Arrival Time

nm. ft/sec deg. deg. Hrs Min Sec

0.0 0.0 0.00 0.00 0 0 0

0.0 0.0 0.00 0.00 0 0 0

0.0 0.0 0.00 0.00 0 0 0

Lunar Orbit Maneuver Summary

Resultant OrbitInc. Velocity Apogee Perigee Perioddeg. ft/sec nm. nm. min.

0.00 0.0 0.0 0.0 0.00

0.00 0.0 0.0 0.0 0.00

Trans-Earth Maneuver Summary

Resultant Entry Interface ConditionsAngle Velocity Lat. Lon. Arrival Timedeg. ft/sec deg. deg. Hrs Min Sec

0.00 0.0 0.00 0.00 0 0 0

0.00 0.0 0.00 0.00 0 0 0

Splashdown

00.00

0.00

Cryogenic Storage

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

Fuel Cell Bus Amperage

Fuel Cell 1Fuel Cell 2

Am

pera

ge

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

Battery Voltage

Battery A

Battery B

Volt

s

Service Module RCS

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

Cryogenic Quantity Remaining

Hydrogen

Oxygen

Perc

ent

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

Service Module RCS Package Temperature

Quad A

Quad B

Quad C

Quad D

Tem

pera

ture

°F

0

2

4

6

8

10

12


Quad A

Quad B

Quad C

Quad D

Tem

pera

ture

°F

Service Propulsion System

Environmental Control System

0

2

4

6

8

10

12


Quad A

Quad B

Quad C

Quad D

Tem

pera

ture

°F

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

SPS Propellant Tank Temperature

Tem

pera

ture

°F

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

Primary Evaporator PerformanceInlet

Outlet

Tem

pera

ture

°F

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

Suit and Cabin Pressure Suit PressureCabin Pressure

Pre

ssure

, psi

+000:

30:0

0

+012:

30:0

0

+024:

00:0

0

+036:

00:0

0

+050:

00:0

0

+062:

00:0

0

+076:

00:0

0

+091:

00:0

0

+105:

00:0

0

+119:

00:0

0

+135:

30:0

0

+145:

15:0

00

2

4

6

8

10

12

Suit and Cabin TemperatureSuit Temper-ature

Tem

pera

ture

°F

copy of apollo 8 flightplan vagc

Documents