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s 4.4.1.2 Assumptions and trade-offs HMM Assessment Study Report: CDF-20(A) February 2004 page 332 of 422 Figure 4-67: Assumed Atmospheric Density and Temperature Model The following assumptions are made: • Total mass of MEV at entry, including aeroshell: 46 500 kg • Initial circular orbital altitude: 500 km • Aerodynamic reference area 490.87 m 2 • Lift coefficient: 0.348 • Drag coefficient: 1.142 • Lift over drag: 0.305 • Aerodynamic parameters are assumed as independent of Mach number • Angle of attack with respect to incident flow: fixed • Control parameter: bank angle around direction of incident flow • Atmospheric density model: Simplified approximation of a low density profile of MarsGRAM 2001, as shown above, not regarding positional, diurnal, seasonal and solaractivity-related variations • Atmospheric temperature: Approximation of a temperature profile from MarsGRAM 2001 • Parachute deployment conditions: velocity < Mach 2 at altitude > 10 km 4.4.1.3 Baseline design A wide corridor of possible entry angles was studied for the given configuration as described in the previous section. This corridor ranges from -2º to -15º with respect to the local horizon in a rotating Mars-fixed frame. For all steep entry angles, starting with -3º, the bank angle is assumed to remain fixed at a value of 30º. This will leave ample control margins to cope with uncertainties in the atmospheric or aerodynamic properties. For a very shallow entry, this control strategy is not appropriate. For the -2º case, a much larger initial bank angle is required to prevent a skip-out, for this, 110º is chosen. When the danger of skip-out is over, the body rolls to a bank angle of 0. Even shallower entry angles would require an initial bank angle of up to 180º. The upper limit to the entry corridor is at around -1.9º, where even with a full-downward lift, skip-out cannot be prevented.
s HMM Assessment Study Report: CDF-20(A) February 2004 page 333 of 422 Figure 4-68 shows the altitude profile for seven regarded entry angles in the specified range from 2º-15º below the local horizon. The following sets of diagrams show the comparative evolution of Mach number, dynamic pressure and g-load. Figure 4-68: Altitude over Time for Seven Regarded Cases Figure 4-69: Mach Number over Time (L) and Altitude (R) for Regarded Cases
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s HMM Assessment Study Report: CDF-
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s STUDY TEAM HMM Assessment Study R
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s T A B L E O F C O N T E N T S HMM
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s L I S T O F F I G U R E S HMM Ass
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s L I S T O F T A B L E S HMM Asses
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s 1 INTRODUCTION 1.1 Background HMM
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s 2 GENERAL ARCHITECTURE 2.1 Study
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s 2.2.4.2 Accelerations HMM Assessm
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s 2.2.4.4 Temperature and relative
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s Figure 2-10: Trajectory Overview
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s 2.4.3.5 TEI and planetary protect
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s Mars Excursion Vehicle Transfer H
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s 2.7.5.1 Mission elements dry mass
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s 2.7.5.8 MEV release The MEV is re
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s Total mission time (days) 1200 10
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s stack 9 Propellant mass of the ne
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s The core supporting structure has
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s 2.7.7.1.3 Mars excursion module S
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s 2.7.7.1.4 Earth return capsule HM
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s Mission Phase Description Event s
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s Mission Phase Description Event s
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s 2.7.10 Mission performance Table
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s Days on Martian surface 450 400 3
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s Maximum manoeuvre duration 6 mont
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s % of loss from baseline 20 18 16
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s 2.7.15 Sensitivity analysis HMM A
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s 2.7.15.4 Influence of the mass of
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s Parameters used: • No Shuttle
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s 2.8.3.3 Launch 3- Front node Figu
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s 2.10.1.4 Communications HMM Asses
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s 2.10.2.2.2 LEO assembly HMM Asses
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s Basic RF link Four 70-m Ka-band s
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s 3 TRANSFER VEHICLE 3.1 Systems…
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s Operational Requirements It shall
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s Trans Mars Injection Module Mars
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s Figure 3-2: Parallel configuratio
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s Figure 3-6: Global dimensions com
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s Front Node 3.2.3.1.3 EVA systems
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s Trans Mars Injection (three stage
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s Figure 3-16: Recommendations for
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s Factors to be considered Impacts
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s Figure 3-24: Baseline design back
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s Figure 3-26: Baseline design priv
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s Module part 3............= 0 m 3
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s 3.3.2.1 Requirements and design d
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s 3.3.3.1 Requirements and design d
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s flux [W/m2] 250 200 150 100 50 0
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s Figure 3-38: Power required to ma
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s 3.3.4.3 Assumptions and trade-off
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s 3.3.4.3.3 Power conditioning and
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s 3.3.5 AOCS HMM Assessment Study R
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s Configuration Length (m) Total ma
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s 3.3.5.5 ACS for TMI 1 st HMM Asse
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s 3.3.6.2 Baseline design HMM Asses
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s 5 Reduce 2dB pointing precision t
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s 70-m antenna 70-m antenna 3.3.7.5
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s Angular separation SEM > 10º SEM
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s Figure 3-63: Communications MEV/M
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s Element 1: Transfer Habitation Mo
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s Radiation Shielding Shielding Req
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s The propulsion system and its cha
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s Item Nr. Mass [kg] Margin [%] Mas
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s 3.4.4 Mechanisms HMM Assessment S
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s 4 MARS EXCURSION VEHICLE 4.1 Syst
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s Figure 4-2: Option 2: Vertical co
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s 4.3 Surface habitation module Fig
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s Figure 4-11: Section through the
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s 4.3.1.5.3 Top level Figure 4-20:
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s Schedule in hours for the most ac
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s 4.3.3.6 Waste production HMM Asse
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s Figure 4-26: Total pressure vs. O
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s ECLS system mass: Figure 4-27: Ma
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s 4.5.5 Thermal HMM Assessment Stud
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s 4.5.5.3 Baseline thermal design H
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s Crew Ingress/Egress Hatch: HMM As
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s Element 3: Mars Ascent Vehicle HM
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s 4.5.7.5 Budgets Characteristic Va
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s PER DAY PER MISSION DRINKING WATE
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s 5 OVERALL CONCLUSIONS HMM Assessm
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s 6 APPENDIX A - MARTIAN SURFACE NU
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s Figure 6-1: Example of buried rea
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s 7 APPENDIX B - REFERENCES [RD1] C
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s [RD26] IES2, Phase A0: Final Repo
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s [RD85] Mars Transportation Enviro
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s 8 APPENDIX C - ACRONYMS AAA Avion
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s MLI Multi-Layer Insulation MMH Mo
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