SPORE Mission Design - Georgia Tech SSDL - Georgia Institute of ...

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Nomenclature s = Stefan-Boltzmann constant (5.67e-8 W/cm 2 /K 4 ) e = Surface emissivity a = Semi-major Axis ACS = Attitude Control System D max = Maximum entry vehicle diameter (m) DOF = Degree of Freedom e = Eccentricity EDL = Entry, Descent, and Landing EME2000 = Earth-Centered Earth Mean Equator and Equinox of Epoch J2000 FIAT = Fully Implicit Ablation and Thermal Response program Fixed = Earth-Centered Earth Mean Equator and Prime Meridian of Date FPA = Flight Path Angle GPS = Global Positioning System GTO = Geosynchronous Transfer Orbit i = Inclination ISS = International Space Station LEO = Low Earth Orbit PD = Proportional Derivative PICA = Phenolic Impregnated Carbon Ablator (TPS) POST = Program to Optimize Simulated Trajectories q conv = Stagnation point convective heat flux (W/cm 2 ) q rad = Stagnation point radiative heat flux (W/cm 2 ) q rerad = Re-radiated heat flux (W/cm 2 ) R = Radius r a = Apogee Altitude r p = Perigee Altitude SPORE = Small Probes for Orbital Return of Experiments STK = Satellite Tool Kit TPS = Thermal Protection System T surf = TPS surface wall temperature (K) u = Argument of Latitude UTTR = Utah Test and Training Range Γ = Flight Path Angle δ = Latitude θ = Right Ascension λ = Longitude ν = True Anomaly Σ = Azimuth ϕ = Declination ω = Argument of Perigee Ω = Right Ascension of the Ascending Node
Table of Contents Nomenclature ............................................................................................................................................... 2 1 Introduction .......................................................................................................................................... 6 2 Requirements ........................................................................................................................................ 6 3 EV Geometry and Packaging ................................................................................................................. 8 4 SPORE Mission Design ......................................................................................................................... 11 4.1 Coordinate Frames ...................................................................................................................... 11 4.1.1 Classical Orbital Elements ................................................................................................... 11 4.1.2 EME2000: Earth-Centered Earth Mean Equator and Equinox of Epoch J2000 .................. 12 4.1.3 Fixed: Earth-Centered Earth Mean Equator and Prime Meridian of Date ......................... 12 4.1.4 Spherical Inertial Relative ................................................................................................... 13 4.1.5 Spherical Atmospheric Relative .......................................................................................... 13 4.1.6 Coordinate Frame Transformations .................................................................................... 14 4.2 Baseline Orbital Trajectories ....................................................................................................... 16 4.3 Deorbit Burn ............................................................................................................................... 18 4.4 Separation ................................................................................................................................... 19 4.5 EDL Sequence of Events .............................................................................................................. 20 4.6 Define baseline entry trajectories ............................................................................................... 21 4.7 Entry Trajectory Simulation ........................................................................................................ 21 4.7.1 One variable at a time sensitivities ..................................................................................... 29 4.7.2 Entry Uncertainties ............................................................................................................. 27 4.7.3 3 DOF Simulation and Monte Carlo Results ........................................................................ 29 4.7.4 6 DOF Stability Analysis ....................................................................................................... 33 4.7.5 6 DOF Monte Carlo Analysis ................................................................................................ 35 4.8 Parachute Selection .................................................................................................................... 39 4.9 Parachute Model ......................................................................................................................... 41 4.10 Thermal Soak-back Analysis ........................................................................................................ 42 4.11 TPS Sizing..................................................................................................................................... 42 4.12 Landing and Recovery Procedures .............................................................................................. 45 5 Conclusions ......................................................................................................................................... 45 6 References .......................................................................................................................................... 47
Page 1: SPORE Mission Design Nicole Bauer G
Page 5 and 6: Figure 39: Depicts Meyer’s Theory
Page 7 and 8: Figure 1. Diagram of SPORE design s
Page 9 and 10: Table 2.Mass budget for 1U entry ve
Page 11 and 12: Figure 5. Coordinate system used to
Page 13 and 14: Prime Meridian refers to the line o
Page 15 and 16: ̇ ̇ ⃗ (If eZ the ω ) (12) ⃗
Page 17 and 18: Table 8.The altitude of the LEO tra
Page 19 and 20: Figure 6. Deorbit simulation block
Page 21 and 22: Figure 8.SPORE EDL Sequence of even
Page 23 and 24: Figure 11.GTO 1U trajectory with st
Page 25 and 26: Altitude, km Acceleration, Earth g'
Page 27 and 28: 6 x 106 Stagnation Point Heat Rate
Page 29 and 30: 4.7.2 One variable at a time sensit
Page 31 and 32: Change in Peak Acceleration (Earth
Page 33 and 34: latitude (deg) latitude (deg) Both
Page 35 and 36: (a) (b) Figure 29. (a) 2x2U total a
Page 37 and 38: Number of Cases Number of Cases Geo
Page 39 and 40: 4.8 Parachute Selection To keep the
Page 41 and 42: Table 18. Summary of parameters use
Page 43 and 44: Number of Cases Number of Cases 200
Page 45 and 46: worst case heating trajectory from
Page 47 and 48: References 1. D. A. Spencer and R.

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