ESA Document - Emits - ESA

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s RECEIVER CHARACTERISTICS (X-BAND) Carrier acquisition threshold -153 dBm Carrier tracking Threshold -156 dBm Carrier Loop bandwidth (2BL in a C/N=10dB) 1000 Hz Noise Figure 1.6 dB Table 3-44: X-band transponder. Receiver characteristics RECEIVER CHARACTERISTICS (Ka-BAND) Carrier acquisition threshold -153 dBm Carrier tracking Threshold -156 dBm Carrier Loop bandwidth (2BL in a C/N=10dB) 100 Hz Noise Figure 1.6 dB Ranging Bandwidth (double sided) 3 MHz Table 3-45: Ka-band transponder. Receiver characteristics Figure 3-58: UHF TV-SHM link HMM Assessment Study Report: CDF-20(A) February 2004 page 212 of 422 The communications links are shown Figure 3-59 to Figure 3-62, under different modes (standard and contingency), distances and mission phases (cruise, surface operations, rendezvous and docking and orbiting around Mars). Three different bands are used: Ka-, X- and UHF-band. Additionally, a laser link is used. To calculate the data rates, the distance variation depending on the mission phase has been taken into account. The maximum distance Earth-TV during cruise to Mars is 0.92 AU. The maximum and minimum distances while the MEV is on the Martian surface are 1.37 and 1.1 AU respectively. During the whole mission, the maximum distance will be 2.7 AU and will happen during the solar superior conjunction. Data rates of laser and RF Ka-band links during the different SEM (Sun-Earth-Mars angle) of the superior solar conjunction are shown in Table 3-46.
s Angular separation SEM > 10º SEM < 10º 60 2º < SEM < 3º 17 SEM < 2° 11 Duration (days) TV Ka-band (3 m antenna) and laser link •Laser communications: 10 Mbps. •RF: From G/S -> TV : 1.76 Mbps From TV -> G/S: 1.5 Mbps •Laser communications difficult. Reduced data rate. •RF: like for SEM > 10º •Laser link not possible. •RF: like for SEM > 10º •No laser link. •RF: reduced rate. Worst case SEM=1.145º: From G/S -> TV : 176 Kbps From TV -> G/S: 300 Kbps HMM Assessment Study Report: CDF-20(A) February 2004 page 213 of 422 Relay satellite link (4 m antenna) Ka-band •RF: From G/S -> RS : 4.1 Mbps From RS -> G/S: 3.2 Mbps •RF: From G/S -> RS : 264 Kbps From RS -> G/S: 550 Kbps Table 3-46: Data rates of RF Ka-band and laser links at different angular separations In the figures below it is shown the different links for the different phases, data rates in bps. Figure 3-59: Communications links during cruise and Mars orbit phases worst 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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Page 193 and 194: s Configuration Length (m) Total ma
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Page 211: s 70-m antenna 70-m antenna 3.3.7.5
Page 215 and 216: s Figure 3-63: Communications MEV/M
Page 225 and 226: s Element 1: Transfer Habitation Mo
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Page 233 and 234: s The propulsion system and its cha
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Page 249 and 250: s 4 MARS EXCURSION VEHICLE 4.1 Syst
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s 4.3.1.5 Baseline design HMM Asses
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s 4.3.1.5.3 Top level Figure 4-20:
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s 4.3.2.3 Baseline design HMM Asses
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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 4.3.6.1 Budgets HMM Assessment St
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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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s 4.4.5.3.2 GNC equipment HMM Asses
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s 4.4.5.4 Control laws generation H
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s Finally, the Figure 4-97 shown th
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s velocity (m/sec) altitude (km) 50
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s 4.5 Mars Ascent Vehicle 4.5.1 Tra
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s Term Value Unit Radius of equator
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s 4.5.2.1 Requirements and design d
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s Inclination (deg) 47.5 47 46.5 46
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s 4.5.3 Structures HMM Assessment S
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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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