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

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Figure 7.Separation sequence of events 2. 4.5 EDL Sequence of Events The SPORE entry vehicle will separate from the service module after the de-orbit maneuver is executed. The deployment attitude targets zero angle-of-attack at entry with respect to the atmosphere-relative velocity vector. The general EDL sequence of events for SPORE is as follows. Atmospheric entry occurs at a radius of 6,503 km (altitude of 125 km). Peak heating and maximum deceleration are experienced during the hypersonic regime, where the TPS is exposed to the target aerothermal environment. The parachute is deployed after transition to subsonic flight. The heatshield does not need to be jettisoned since the payload is thermally isolated from the heatshield soak-back by an aluminum heat sink. The vehicle approaches terminal velocity on the parachute prior to impact. Impact velocities vary based upon the vehicle configuration. A UHF beacon signal is transmitted throughout EDL to aid in the recovery process. Recovery is required to occur within 24 hours of touchdown. Figure 1 details the baseline EDL sequence of events for SPORE.
Figure 8.SPORE EDL Sequence of events. 3 4.6 Define baseline entry trajectories The 1U baseline trajectories that meet the TPS requirements are given in Table 10. Figure 9, Figure 10, Figure 11, and Figure 12 illustrate that the requirements are met. To reduce the size of the landing ellipse and decrease the total integrated heat load, the entry trajectories were biased to have a steep entry flight path angle. The 1U entry vehicle has a 4.5 m diameter parachute with a 1.06 kg mass to enforce the 5 m/s landing requirement. Table 10: Baseline entry trajectory for 1U cases in spherical atmosphere relative coordinates. R (km) Lon (°E) Lat (°N) V (m/s) γ (°) Σ (°) LEO 6503.1 137.29 -22.98 7780 -5 182.9 GTO 6503.1 128.64 -35.92 9964.4 -6.72 57.8
Page 1 and 2: SPORE Mission Design Nicole Bauer G
Page 3 and 4: Table of Contents Nomenclature ....
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: Figure 6. Deorbit simulation block
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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