recovered file 1 -...
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![Page 1: Recovered File 1 - spacecraft.ssl.umd.eduspacecraft.ssl.umd.edu/old_site/academics/483F01/08_param_design_prt.pdf · 1.E+00 1.E+01 1.E+02 1.E+03 1.E+04 1.E+05 1.E+06 1.E+07 H yp er](https://reader036.vdocuments.net/reader036/viewer/2022081418/5f02b9757e708231d405b231/html5/thumbnails/1.jpg)
Parametric DesignPrinciples of Space Systems Design
Parametric Design
• The Design Process• Example: Project Diana
© 2001 David L. Akin - All rights reservedhttp://spacecraft.ssl.umd.edu
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Parametric DesignPrinciples of Space Systems Design
Akin’s Laws of Spacecraft Design - #3
Design is an iterative process. Thenecessary number of iterations is onemore than the number you havecurrently done. This is true at anypoint in time.
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Parametric DesignPrinciples of Space Systems Design
Overview of the Design Process
System-level Design(based on discipline-
oriented analysis)
Vehicle-level Estimation(based on a few
parameters from prior art)
System-level Estimation(system parameters based
on prior experience)
Program Objectives ✑System Requirements
Increasing complexity
Increasing accuracy
Decreasing abilityto comprehend the “bigpicture”
Basic Axiom:
Relative rankings betweencompeting systems willremain consistent fromlevel to level
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Parametric DesignPrinciples of Space Systems Design
Regression Analysis of Existing Vehicles
Veh/Stage prop mass gross mass Type Propel lants Isp vac isp sl sigma eps delta( l b s ) ( l b s ) ( s e c ) ( s e c )
Delta 6925 Stage 2 13 ,367 15 ,394 Storab N2O4-A50 319.4 0.152 0.132 0.070Delta 7925 Stage 2 13 ,367 15 ,394 Storab N2O4-A50 319.4 0.152 0.132 0.065Titan II Stage 2 59 ,000 65 ,000 Storab N2O4-A50 316.0 0.102 0.092 0.087Titan III Stage 2 77 ,200 83 ,600 Storab N2O4-A50 316.0 0.083 0.077 0.055Titan IV Stage 2 77 ,200 87 ,000 Storab N2O4-A50 316.0 0.127 0.113 0.078Proton Stage 3 110 ,000 123 ,000 Storab N2O4-A50 315.0 0.118 0.106 0.078Titan II Stage 1 260 ,000 269 ,000 Storab N2O4-A50 296.0 0.035 0.033 0.027Titan III Stage 1 294 ,000 310 ,000 Storab N2O4-A50 302.0 0.054 0.052 0.038Titan IV Stage 1 340 ,000 359 ,000 Storab N2O4-A50 302.0 0.056 0.053 0.039Proton Stage 2 330 ,000 365 ,000 Storab N2O4-A50 316.0 0.106 0.096 0.066Proton Stage 1 904 ,000 1 ,004 ,000 Storab N2O4-A50 316.0 285.0 0.111 0.100 0.065
average 3 1 2 . 2 2 8 5 . 0 0 . 1 0 0 0 . 0 8 9 0 . 0 6 1standard deviation 8 . 1 0 . 0 3 9 0 . 0 3 3 0 . 0 1 9
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Parametric DesignPrinciples of Space Systems Design
Regression Analysis
• Given a set of N data points (xi,yi)• Linear curve fit: y=Ax+B
– find A and B to minimize sum squared error
– Analytical solutions exist, or use Solver in Excel
• Power law fit: y=AxB
• Polynomial, exponential, many other fits possible
error Ax B yi ii
N= + −( )∑
=
2
1
error A x B yi ii
N= + −[ ]∑
=log( ) log( )
2
1
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Parametric DesignPrinciples of Space Systems Design
Regression Analysis of Inert Mass Fraction
Hypergolic stages
0.000
0.010
0.020
0.030
0.040
0.050
0.060
0.070
0.080
0.090
0.100
1.E+00 1.E+01 1.E+02 1.E+03 1.E+04 1.E+05 1.E+06 1.E+07
Hypergolic stages
Stage Gross Mass (lbs)
Inert MassFraction
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Parametric DesignPrinciples of Space Systems Design
Regression Values for Design Parameters
Isp (vac) delta Max DV( s e c ) ( m / s e c
LOX/LH2 4 3 3 0.078 1 0 8 2 5L O X / R P - 1 3 2 0 0.063 8 6 7 0Storables 3 1 2 0.061 8 5 5 2Solids 2 8 3 0.087 6 7 7 2
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Parametric DesignPrinciples of Space Systems Design
Project Diana - Mission Statement
Design a system to return humans tothe moon within the shortest feasibletime span for the minimum achievablecost.
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Parametric DesignPrinciples of Space Systems Design
Project Diana - Requirements Document
• System must be based on the use ofAmerican launch vehicles in operationalstatus as of 2005
• System shall be at least as capable forlunar exploration as the J-mission Apollosystem– Two landed crew– 72 hour stay time, 3 x 6 hour EVAs– 300 kg of science payload (each way)
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Parametric DesignPrinciples of Space Systems Design
American Heavy-Lift Vehicles (2005)
• Space Shuttle -27K kg to LEO
• Delta IV Heavy -23K kg to LEO
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Parametric DesignPrinciples of Space Systems Design
∆∆∆∆V Requirements for Lunar MissionsTo:
From:
Low EarthOrbit
LunarTransferOrbit
Low LunarOrbit
LunarDescentOrbit
LunarLanding
Low EarthOrbit
3.107km/sec
LunarTransferOrbit
3.107km/sec
0.837km/sec
3.140km/sec
Low LunarOrbit
0.837km/sec
0.022km/sec
LunarDescentOrbit
0.022km/sec
2.684km/sec
LunarLanding
2.890km/sec
2.312km/sec
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Parametric DesignPrinciples of Space Systems Design
Mission Scenario 1
• What can be accomplished with a single shuttlepayload (27K kg)?
• Assume δ=0.1, Isp=320 sec• Direct landing
– LEO-lunar transfer orbit ∆V=3.107 km/sec– Lunar transfer orbit-lunar landing ∆V=3.140 km/sec– Lunar surface-earth return orbit ∆V=2.890 km/sec– Direct atmospheric entry to landing
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Parametric DesignPrinciples of Space Systems Design
Scenario 1 Analysis• Trans-lunar injection
• Lunar landing– r=0.3674– mLS=1958 kg
• Earth return– r=0.3978– mER=583 kg
r eTLI
V
gITLI
sp= =−
∆
0 3713.
m m r kgTLI o TLI= −( ) =δ 7325
This scenario would work for amoderate robotic sample returnmission, but is inadequate for ahuman program.
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Parametric DesignPrinciples of Space Systems Design
Mission Scenario 2
• Assume a single shuttle payload is used to sizethe lunar descent and ascent elements
• Assume δ=0.1, Isp=320 sec• Direct landing
– LEO-lunar transfer orbit ∆V=3.107 km/sec– Lunar transfer orbit-lunar landing ∆V=3.140 km/sec– Lunar surface-earth return orbit ∆V=2.890 km/sec– Direct atmospheric entry to landing
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Parametric DesignPrinciples of Space Systems Design
Scenario 2 Analysis• Lunar landing
– r=0.3674– mLS=7219 kg
• Earth return– r=0.3978– mER=2150 kg
• Trans-lunar injection– r=0.3713
Payload mass still too low forhuman spacecraft. TLI stagemass of 72,520 kg is too largefor any existing launch vehicle.(Ideal situation is to ensure 100%load factors on all launches.)
mm
rkgLEO
TLI
TLI
=−( )
=δ
99 520,
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Parametric DesignPrinciples of Space Systems Design
Mission Scenario 3
• Assume three Delta-IV Heavy missions carryidentical boost stages which perform TLI andpart of descent burn
• Space shuttle payload completes descent andperforms ascent and earth return
• All other factors as in previous scenarios
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Parametric DesignPrinciples of Space Systems Design
Scenario 3 Standard Boost Stage
• mo=23,000 kg• mi =2300 kg• mp =20,700 kg• LEO departure configuration is three boost
stages with 27,000 kg descent/ascentstage as payload
• mLEO =96,000 kg
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Parametric DesignPrinciples of Space Systems Design
Scenario 3 TLI Performance• Boost stage 1
– VTLI remaining=2345 m/sec• Boost stage 2
– r=0.7; ∆V2=1046 m/sec– VTLI remaining=1300 m/sec
• Boost stage 3– r=0.55; ∆V3=1300 m/sec– Residual ∆V after TLI=376 m/sec
∆V gIm m
mm
spLEO prop
LEO1 762= −
−
=ln sec
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Parametric DesignPrinciples of Space Systems Design
Alternate Staging Possibilities
• Three identical stages• Serial staging (previous chart) ∆V=3483 m/sec• Parallel staging (all three) ∆V=3264 m/sec• Parallel/serial staging (2/1) ∆V=3446 m/sec• Pure serial staging is preferred
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Parametric DesignPrinciples of Space Systems Design
Scenario 3 Ascent/Descent Performance
• 376 m/sec of lunar descent maneuver performedby boost stage 3
• Remaining descent requires 2764 m/sec– r=0.4143– mi=2700 kg– mLS=8485 kg
• Earth return– r=0.3978– mi=849 kg– mER=2528 kg
Return vehicle mass is stillsignificantly below that of theGemini spacecraft - need toexamine other numbers of boostvehicles
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Parametric DesignPrinciples of Space Systems Design
Effect of Number of Boost Stages
0
500
1000
1500
2000
2500
3000
3500
Number of Boost Modules
Ear
th R
etu
rn P
aylo
ad (
kg)
Payload 583 1068 1809 2528 32290 1 2 3 4
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Parametric DesignPrinciples of Space Systems Design
Baseline System Schematic - Project Diana
Boost Stage 123,000 kg
Boost Stage 223,000 kg
Boost Stage 423,000 kg
Boost Stage 323,000 kg
Descent/Landing Stage
16,160 kg
Ascent Stage7611 kg
Crew Cabin3299 kg
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Parametric DesignPrinciples of Space Systems Design
Alternate Lunar Transport Architectures
• Transportation node at intermediate point (low lunarorbit, Earth-Moon L1)
• Leave systems at node if not needed on the lunarsurface, e.g.:– TransEarth injection stage– Orbital life support module– Entry, descent, and landing systems
• Will increase payload capacities at the expense ofadditional operational complexity, potential for safetycritical failures
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Parametric DesignPrinciples of Space Systems Design
Mass Breakdown of Payload Systems• 27,000 kg assembly delivered to LEO by space shuttle• mi,orbit = orbital maneuvering module inert mass• mp,node = propellants for arrival at transport node• mp,TEI = trans Earth injection propellants• mi,asc = inert mass of lunar ascent vehicle• mp,asc = propellant mass of lunar ascent vehicle• mi,des = inert mass of lunar descent vehicle• mp,des = propellant mass of lunar descent vehicle• mL,node = payload transported to node and back• mL,LS = payload transported to/from lunar surface only• mL,thru = payload transported to/from lunar surface and
returned to Earth (assumed to be ≥500 kg)
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Parametric DesignPrinciples of Space Systems Design
Variation 1: Lunar Orbit Staging• Assume same process as baseline, but use lunar
parking orbit before/after landing• Additional DV’s required for LLO stops
– Lunar landing additional ∆V=+31 m/sec– Lunar take-off additional ∆V=+53 m/sec
• Low lunar orbit waypoint changes baseline payloadto 3118 kg (-3.5%)
• Not useful without taking advantage of node tolimit lunar landing mass
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Parametric DesignPrinciples of Space Systems Design
Variation 2: Lunar Orbit Rendezvous• Use specialized vehicle for descent/ascent• Use four boost stages as per baseline• Boost stage 4 residual propellants
– 10,680 kg following trans lunar insertion– 1315 kg following lunar orbit insertion– Use remaining stage 4 capacity to aid descent stage
• Leave TEI stage in lunar orbit during ascent/descent– Descent ∆V=2334 m/sec– Ascent ∆V=2084 m/sec– TEI ∆V=837 m/sec
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Parametric DesignPrinciples of Space Systems Design
Baseline System Schematic - Project Diana
Boost Stage 123,000 kg
Boost Stage 223,000 kg
Boost Stage 423,000 kg
Boost Stage 323,000 kg
Descent/Landing Stage
16,160 kg
Ascent Stage7611 kg
Crew Cabin3299 kg
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Parametric DesignPrinciples of Space Systems Design
LOR System Schematic - Project Diana
Boost Stage 123,000 kg
Boost Stage 223,000 kg
Boost Stage 423,000 kg
Boost Stage 323,000 kg
Descent/Landing Stage
15,010 kg
TEI Stage
Ascent Stage5811 kg
Crew Cabin4114 kg
2066 kg
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Parametric DesignPrinciples of Space Systems Design
The Next Steps From Here
• Perform parametric sensitivity analyses– Inert mass fractions– Specific impulse– Size of entry package left in orbit
• Investigate reduction from 4 to 3 boost stagesfor minimal system
• Examine growth options allowed by system– One-way cargo variants– Larger module with more boost modules