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s Two system options were presented with following mass budgets: ECLSS power requirements The results are shown in Table 4-69. Today’s Technology Mass consumables (kg) 46 Mass system (kg) 549 Table 4-68: Mass budgets Characteristic Value Power requirement day (W) 375 Power requirement night (W) 375 Table 4-69: Power budgets HMM Assessment Study Report: CDF-20(A) February 2004 page 398 of 422 ECLSS volume requirements Only a first estimate for the volume of the life support system has been achieved in the course of the study. The internal volume requirement pertains to the volume occupied by the ECLSS inside the pressurised vessel, as opposed to the external volume requirement, which pertains to the volume needs outside the pressurised volume. 4.5.9 Data handling See 4.3.6. 4.5.10 Communications 4.5.10.1 Requirements and design drivers Characteristic Value Internal volume requirements (m3) 1.4 External volume requirements (m3) 0 Table 4-70: Volume requirements • The vehicle shall support Tracking, Telemetry and Command (TT&C) communications during all mission phases and any attitude. • Communications availability should be maximized. • The telecommand (TC) and telemetry (TM) data rates shall be selectable to improve the data rate depending on the distance to the receiving unit. • Data consists of housekeeping, audio, and any additional data. 4.5.10.2 Baseline 4.5.10.2.1 Links
s HMM Assessment Study Report: CDF-20(A) February 2004 page 399 of 422 During Mars ascent phase, similarly to the DM the communications will be maintained using an UHF link with TV and a X-band link with the relay satellite and therefore with Earth G/S. UHF link will be the same than for DM and the same antenna will be used. As in DM, UHF and Xband MAV transponders are used. The only difference is the location of the three X-band patch antennas, which will be in the MAV capsule chassis. • MAV patch antenna • Relay antenna: 1m 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 18600 Km Min distance: 16530 Km 4.5.10.2.2 Contingency communications 172 Kbps 97 Kbps Table 4-71: X-band link MAV-Relay satellite. Direct communications with the Earth could be possible using the X-band patches antennas, but with a very low data rate. See TV chapter for data rates and link schemes. 4.5.10.3 Budgets Unit Unit massTotal mass Power Number of units (Kg) (Kg) (W) UHF omni antenna 1 1.5 1.5 X-band patch antenna 3 0.1 0.3 UHF transceiver 2 1.0 2 10.0 X-band transponder 2 4.6 9.2 20.0 Global RFDU unit 2 1.2 2.4 X-band TWT 2 0.8 1.6 120.0 Harness 2.5 Total: 19.5 150.0 Table 4-72: MAV communications budget
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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 • a duty cycle value (duration
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s Figure 4-48: MAV Power Inputs HMM
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s 4.3.5.4.2 Power storage HMM Asses
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s Figure 4-52: Regenerative Fuel Ce
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s Figure 4-54: Solar irradiance on
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s 450.00 400.00 350.00 300.00 250.0
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s Surface Surface Container MAV Con
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s 4.3.9.3 Baseline design 4.3.9.3.1
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s Bio-Lock Masses: Core Samples No.
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s Figure 4-72: Entry Velocity (L) a
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s 2 3.9 233 923.1 347 923 12.3 352
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s Figure 4-85: Communications MEV/M
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Page 419 and 420: s 8 APPENDIX C - ACRONYMS AAA Avion
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