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s Kind of antenna Telescope 1 Dish antenna MGA Patch Dish antenna Patch antenna Wire antenna Quantity Band Gain 1 2 1 Optica l Ka- Band Xband Xband 1 UHF 3.3.7.6 Options 4 UHF/ VHF 3.3.7.6.1 Ka+ band Minimum required pointing precision 59.1 dBi 0.01 deg 18 dBi 20 deg 30 dBi 2.25 deg 6 dBi 40 deg -3 dBi Omnidirectio nal Size Radiated power Data rate Uplink Data rate Downlink 2µrad 30.5 cm 5 W No uplink 10 Mbps 3 m 65 W 1.8 Mbps 1.5 Mbps 8.2 x 8.2 x 2 cm 65 W 22 Kbps 460 bps 45 cm 65 W 30 Mbps 30 Mbps 35 x 35 cm 10 W 128 Kbps 128 kbps 20 x 10 x 10 cm Table 3-47: TV antennas summary HMM Assessment Study Report: CDF-20(A) February 2004 page 216 of 422 Steering mechanism Commentaries 180° hemispherical 180° hemispherical 180° hemispherical 180° hemispherical 180° hemispherical LASER link, only used for downlink Main link. Intelligence to point the Earth in a contingency case, even with loss of TV attitude Link with relay satellite UHF link with MAV/MEV 5 W 2048 Kbps 2048 kbps None For TV EVAs Unit Number Unit massTotal MassPower of units (kg) (kg) (W) Optical transmitter 2 20.0 40 150.0 Optical transmitter device (telescope)1 25.0 25 UHF antenna system (EVA) 4 2.0 8 Ka-band transponder 2 6.5 13 160.0 Ka-band antenna (3m) 1 35.3 35.3 X-band transponder 2 6.5 13 100.0 MGA (X-band), patch 2 0.6 1.2 UHF patch antenna 1 1.0 1 UHF transceiver 2 2.5 5 16.5 X-band dish antenna (0.45 m) 1 1.0 1 Harness 21 Total: 163.5 370 Figure 3-64: TV communications budget summary One of the most straightforward ways of improving link capacity is moving to higher frequency bands. The 40 GHz up and 37 GHz down band (Ka+/Ka+) was allocated by ITU for the very purpose of human space exploration. Contrary to the 34 GHz up / 32 GHz down (Ka/Ka), the Ka+ band can be used for both deep-space (Mars) and near-Earth (Moon) missions, while Kaband can not be used from the Moon, but from Mars. To use the same frequencies for all human missions, Ka+ band is the best option. The problems of this band are firstly that Ka+ band is new to space activities and no technology development has been performed so far. Secondly,
s HMM Assessment Study Report: CDF-20(A) February 2004 page 217 of 422 atmospheric and rain attenuation is higher than for Ka-band in approximately 3 dB, so the improvement of gain due to the higher frequency is cancelled by the higher attenuation. 3.3.7.6.2 Laser link coding Turbo code 4 st. for laser link could be used. A higher data rate with respect to the option was chosen in this design, Reed Solomon code, would be obtained. The problem is that the high bit rate to support a net data rate needed after coding is four times higher than before coding. Technology should be prepared for those rates, especially for short distances TV-Earth where from the link budget point of view, high net data rates could be achieved (for example 250 Mbps at 0.7 AU). See [RD54]. 3.3.8 Mechanisms 3.3.8.1 Requirements and design drivers The HMM requirements do not state any specific requirements applicable to the TV & Propulsion module Mechanisms. As a result of the TV’s configuration, the following necessary mechanism and their requirements can be derived: Transfer Habitation Module • Power Generation System: • Deployable Solar Arrays to provide up to 380 m 2 area. • Sun-tracking ability, unlimited rotation (driven by Martian orbit) • Survivability of deployed array during propulsion manoeuvres • Potential for Re-stowage and Latching capability- this is dependent upon the loading introduced by propulsive manoeuvres • Communication System: • Antenna Pointing and Tracking Mechanism Ka-band Antenna: � Antenna Diameter: 3 m � Antenna Mass: 35 kg Est � Coverage: 180° Hemispherical. � Pointing Accuracy: 0.001° • Antenna Pointing and Tracking Mechanism laser Communications Link: � Antenna Size 0.4x0.5x0.4 m (LxWxH) � Antenna Mass: 25 Kg Est � Coverage: 180° Hemispherical. � Pointing Accuracy: 2 µrad°. • Antenna Pointing Mechanism Aero-stationary satellite communications: � Antenna Dia: 0.5 m. � Antenna Mass: 5 Kg Est � Coverage: 180° Hemispherical. � Pointing Accuracy: 2.°. • Deployment capability for 2x 3 m booms and 1x 0.5 m boom. • Survivability of deployed array during propulsion manoeuvres • Potential for Re-stowage and Latching capability- if deployable solution selected and dependent upon the loading introduced by propulsive manoeuvres.
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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 187 and 188: s 3.3.4.3.3 Power conditioning and
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Page 213 and 214: s Angular separation SEM > 10º SEM
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Page 249 and 250: s 4 MARS EXCURSION VEHICLE 4.1 Syst
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s 4.3.1.5.3 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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