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s HMM Assessment Study Report: CDF-20(A) February 2004 page 344 of 422 • The telecommand (TC) and telemetry (TM) data rates shall be selectable to improve the data rate depending on the distance to the receiving unit. • During descent phases, data consist of housekeeping audio and any additional data. 4.4.4.2 Baseline Communications during undocking, entry, descent and landing will be done using an UHF and a X-band link. An UHF slot antenna will be located in the docking port of MAV and will be used to communicate with the TV. Three switched X-band patches antennas will be located in the DM back shell (thermal protection) and will use the transponders and amplifiers located in the MAV (see MAV communications section 4.5.10 for further details). Therefore, the DM will not have active elements, since they will be present in SHM and MAV. After the DM shell is released, MAV antennas and transponders will be used for communications with the relay satellite. The achieved data rates are shown in Figure 4-85. See section 4.3.8 TV report for details about the UHF link, MEV-TV link in it. DM patch antenna Relay antenna: 1 m with steering mechanism Uplink Downlink Frequency 7.23 GHz 8.5 GHz Tx power 65 W 65 W Modulation QPSK QPSK Coding Concatenated, Interleaving=5 FER 10 -5 Bit rate: Max distance 18 600 km Min distance: 16 530 km 4.4.4.3 Contingency communications 172 kbps 97 kbps Table 4-42: X-band link DM-Relay satellite Direct communications with the Earth could be possible using the X-band patches antennas, but at a very low data rate.
s Figure 4-85: Communications MEV/MAV-TV during take off – rendezvous and undocking-landing 4.4.4.4 Budgets 4.4.5 GNC Unit Number Unit massTotal massPower of units (Kg) (Kg) (W) UHF slot omnidirectional antenna 1 1.5 1.5 X-band patch antenna 3 0.1 0.3 Harness 3 Total : 4.8 0 Table 4-43: DM communications budget HMM Assessment Study Report: CDF-20(A) February 2004 page 345 of 422 4.4.5.1 Requirements and design drivers The MEV entry, descent and landing is a 6-degree of freedom (6DoF) closed loop control entry with automatic steering law that will allow the safe landing of the astronauts to the Martian surface. The GNC requirements can be listed as follows: • Starting from a 3DoF optimal trajectory that satisfies certain boundary and path constraints • To find a flyable 6DoF trajectory within allowable margins that follows the optimal 3DoF trajectory previously calculated off-line • To define a GNC equipment that controls and steers the MEV in terms of sensors and actuators The initial and final boundary constraints as well as the path constraints are as follows: • Safety of the astronauts with a possible manual control during entry, descent and landing • Minimise the heat flux • Maintain a given load factor for the health of the crew • Minimise the descent time to be able to cope with the limited life support system available on-board the MEV • Touch down in a specified point on the Martian surface The output of the optimal trajectory establishes the corresponding roll, pitch and yaw profiles to be followed by the control law of the MEV. The Figure 4-86 shows the MEV model during this study:
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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 Figure 4-28: Mars albedo (L), ars
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s sun flux (W/m2) 450 400 350 300 2
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s Insulation structure (external) F
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s cryocooler heat lift [W] cryocool
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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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