1 student launch initiative 2010 – 2011 aiaa oc section frr presentation \ student launch...

$: 1 STUDENT LAUNCH INITIATIVE 2010 – 2011 AIAA OC SECTION FRR PRESENTATION \ Student Launch Initiative AIAA OC Section$
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STUDENT LAUNCH INITIATIVE2010 – 2011

AIAA OC SECTION

FRR PRESENTATION

\

Student Launch Initiative

AIAA OC Section

Agenda Finalized Vehicle Motor type and selection Rocket flight stability Parachute and descent rates Test plans and procedures

• Black Powder test• Dual Deployment• Full scale lunch

Lessons learned – Vehicle Payload Payload integration Lessons learned – Payload Educational Outreach Questions

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Finalized Vehicle – Black BrantFull Scale Model

Diameter 4 inches

Length 84.5 Inches

Liftoff Weight 17.75 pounds

Descent Weight 13.85 pounds

Center of Pressure 62.0220 inches

Center of Gravity 52.4814 inches

Launch Rail Diameter 1 inch

Launch Rail Length 6 feet

Motor Retention Method Aero pack Qwik Change Motor Retainer

Thrust to weight ratio 8.28:1

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Finalized Vehicle – Black Brant

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Full Scale Model

Size of Shock Cord 5/8th inch

Length of Shock Cord 15 feet in each section

Material of Shock Cord Tubular Nylon

Drogue ‘Chute 24 inches

Main ‘Chute 72 inches

Black Powder for Drogue 1.74 grams

Black Powder for Main 2.00 grams

Cesaroni K635 Redline

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Pro54 1994K635-

17AMotor Data

Brandname Pro54 1994K635-17A Manufacturer Cesaroni

Technology

Man. Designation 1994K635-17A CAR

Designation

1994-K635-17A

Test Date 7/6/2003

Single-Use/Reload/Hybrid Reloadable Motor

Dimensions mm

54.00 x 488.00

mm (2.13 x 19.21

in)

Loaded Weight 1989.90 g (69.65 oz) Total Impulse 1749.50 Ns

(393.64 lb.s)

Propellant Weight 1281.00 g (44.84 oz) Maximum

Thrust

728.70 N (163.96

lb)

Burnout Weight 658.40 g (23.04 oz) Avg Thrust 656.00 N (147.60

lb)

Delays Tested 17 - 7 secs ISP 139.30 s

Samples per second 1000 Burntime 2.66 s

Notes Red Lightning™

Motor Selection

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Motor Properties

Manufacturer Cesaroni

Motor Type K635 Redline

Max, Average Thrust(Newtons)

656

Total Impulse (Newton – Seconds)

1749.5

Mass of Motor Before and After Burn(Pounds)

4.38/1.45

Cesaroni K490(alternate)

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Pro54 1990K490-16A

Motor Data

Brandname Pro54 1990K490-16A

Manufacturer Cesaroni Technology

Man. Designation 1990K490-16A

CAR Designation 1990-K490-16A

Test Date 1/7/2010Single-Use/Reload/Hybrid Reloadable Motor Dimensions

mm54.00 x 488.00 mm (2.13 x 19.21 in)

Loaded Weight 1854.1 g Total Impulse 1978.4 Ns (44.8 lb-s)

Propellant Weight 1155.4 g Maximum Thrust 590.9 N (132.8 lb)

Burnout Weight 652.9 g Avg Thrust 485.5 N (109.2 lb)

Delays Tested 16 - 6 secs ISP 174.16 s

Samples per second 1000 Burntime 4.08 sNotes Green3™

Representative CMT Thrust Curve

Click Here for Larger View of Graph

Alternate Motor Selection

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Motor Properties

Manufacturer Cesaroni

Motor Type K490

Max, Average Thrust(Newtons)

485.5

Total Impulse (Newton – Seconds)

1978.4

Mass of Motor Before and After Burn(Pounds)

2.54722 / 1.43939

Parachute Size and Descent Rates

Rocket mass = 221.65 oz Drogue chute diameter = 24 in. Main chute diameter = 72 in. Calculated projected velocity for each chute with

online calculator and by hand v2 = 2FD / (ρ)(CD)(A)

• CD = 1.00

• FD = mg = (6.285 kg)(9.8 m/s2) Hand: vdrogue = 60.99 ft/s Online: vdrogue = 68.57 ft/s Hand: vmain = 17.43 ft/s Online: vmain = 19.59 ft/s

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Test Plans and Procedures We will further test our electronics . All of the tests that are done are to ensure that our vehicle

subsections are safe. In our FRR we have Appendices which explain the procedure of

each test that it completed. Some appendices are:

• Appendix H; Black Powder• Appendix I; Battery Life• Appendix J; GPS Testing• And so on

Videos and pictures of these tests are on our website: http://aiaaocrocketry.org/?page_id=13

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Black Powder Charge Test The table below shows the testing our team has done with black

powder charges

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Full Scale Amount Successful?

Sustainer with out parachute

1.74 Yes

Sustainer with parachute

1.74 Yes

Main without Parachute

1.43 Yes

Main with parachute 1.43 No

Main with parachute 1.74 No

Main with parachute 2.00 Yes

Black Powder Charge Test We learned that we needed to refold the

parachute to have it deploy. Also we moved the ejection charge for the top section to the front of the rocket. It will now lay against the bulkhead that the first attachment point is.

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Dual Deployment Electronics: MAWD Perfect Flight, HCX G-Wiz Partners The electronics will “back” one another up incase one

pyro (either drogue or main) does not fire. Drogue Parachute will be deployed at apogee Main Parachute will be deployed at 900ft The electronics have been tested four tests have been

done:• Christmas tree light test • Vacuum Chamber test• First flight in the scale rocket (MAWD Only)• Second Flight in scale model (MAWD Only)

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Dual Deployment Tests Christmas Tree Light:

Vacuum Chamber:

First Launch

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Dual Deployment – Flight Test Fist Flight

• Our dual Deployment was partially successful. Both of our ejection charges went off, but only our drogue shoot deployed.

• We learned that the gases from the ejection charge won’t necessarily eject the parachute. So, we will wrap the shock cord around the parachute to ensure a successful deployment of the main parachute.

Second Flight

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Full Scale Launch

Second Launch Video

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Lessons Learned - Vehicle

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Scale model fault How we applied it Was it successful

Complex wiring Our team made the wiring less complicated and added slack to the wires so there was extra room for easier assembly

Yes it was successful but we learned we have to be careful so we don’t stress the key switches

Instability when reaching apogee

Our team took their time to assemble the rocket. The rocket was looked over before it was launched and the checklist was followed.

Yes it was successful because our design proved stable in 15mph wind.

Drag/impulse Separation Our team used three #2 sheer pins on both the bottom section and the top section of our rocket.

Yes this was successful because our rocket did not have drag/impulse separation.

Payload G-Wiz Partners HCX flight computer - measures acceleration

of the rocket Toshiba hard drive – test subject; we will run a Linux script

on the hard drive over and over again; the time the hard drive takes to run the script each time is measured

Simple net computer/Linux computer – the mini computer that will execute the Linux script on the hard drive; it will be initialized by a PC; the flight data will be recorded on a flash drive inserted into this computer

Power converter – Keeps a steady flow of power to the payload components

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Lessons Learned - PayloadFault How are we going to

fix itWill it be successful

File system is corrupt on the hard drive, but the hard drive is ok

We worked around the file system the raw sector on the disk

Yes because there no file system code to work through, there is no risk of “erroring out” due to a corrupt file system, we will have more control over the “seeking” of the drive, and this will speed things up.

Accuracy We are going to fix this by flushing the caches.

Yes because in Linux, there is a 'sync' command, which does this

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Website aiaaocrockectry.org SLI 2010-2011

• Documents• Calender• Photos/Videos• Manuals• MSDS

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Educational Outreach Cloverdale 4-H club Girl Scouts workshop Presentations to Sunny Hills High School Science classes to

get involved Articles published/ will be published in the Orange County

Register, The Foothill Sentry, and the Sunny Hills High School Accolade

We will have a booth at youth expo, April 9th to April 11th, we will reach a few hundred kids.

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Thank you for letting us be part of SLI

Questions?

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