ESA Document - Emits - ESA

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s int. foam structure aluminised foil ext. foam radiator Figure 4-118: Radiator layout (L), LOK radiators (nota: bent over the years) (R) 4.5.5.3.3 Primary and secondary loop SHM primary loop air 230 m3/hr at 27C max 931W mean + 330W metabolic cold plates assembly N liquid/air HX N acquisition system Pump assembly 360 kg/hr at 0.5b 5 / 9 C liquid/liquid HX thermostatic coils (hull, propulsion, ...) 0 W worst case Internal shell coil N � � Flow control valve 250 kg/hr at 2 b, 18C pump assembly accumulator Figure 4-119: Ascent vehicle / primary and secondary loop principles 4.5.5.3.4 The insulating system and thermal protection Radiator assembly 360 kg/hr at 0.5 b Pump assembly transfer vehicle primary loop N HMM Assessment Study Report: CDF-20(A) February 2004 page 386 of 422 • TPS sizing to be done utterly. A provision of 50 kg has been taken into account for the mass budget • Fuel tank insulation The ascent vehicle fuel tanks are insulated by lightweight foam, type Basotect (open cell foam) appropriate to the Martian environment. An external goldenized kapton foil is added to reduce radiative heat exchange. The tanks are assumed to be enclosed in a protective frame whereas a thin TPS layer is added. 4.5.5.3.5 The thermostatic system
s HMM Assessment Study Report: CDF-20(A) February 2004 page 387 of 422 Certain surfaces that cannot be protected by insulating means (docking system for the MAV) are treated (oxidation anodic, alodine) to minimise heat losses. On the internal face, coils (circulating fluid from primary loop) thermostatically control the temperature (condensation avoidance) and the heat exchanges (control of the heat losses). An adequate redistribution of the rejected heat (thermostatic coils) therefore reduces the use of heater power to the minimum. 4.5.5.4 Budget 4.5.5.4.1 Synthesis per subsystem (main features) Primary loop Secondary loop Fluid loops Pump assembly: 10 kg, 50W nominal (250 kg/hr) (x 2) Condenser heat exchangers: 20.6 kg (x 1), cold plates: 3.4 kg (x 5), valves (on/off, manual): 4 kg (x 10) 26 kg of tubing (dry including insulation, brackets) + 21 kg of water Pump assembly: 6 kg, 30W nominal (x 2) Heat exchangers: 5 kg, cold plates: 3.4 kg (x 2), flow control valve: 10 kg 37.3 kg of tubing (dry including insulation, brackets) + 31kg of PMS Passive thermal control External radiator One radiator of 8 m2, weighting 43 kg (5.4 kg/m2) Insulation 0 kg for the main body of the transfer vehicle: the thermal properties of the MOD shield are exploited, the related budget transferred to structure. 50 kg are provisioned for specific external and internal elements insulation. 50 kg are provisioned as heat shield Heating system 300W installed power (heating of the lines) 2 control units (1 on), each 6 kg, 29W when shell heaters are 100% duty cycle Thermal Protection System and underneath structure Fairing Composite structure (core honeycomb, carbon shell) TBD mm of Norcoat (TPS), provision of 50 kg Tanks 30 mm of basotect + goldenized kapton layer: TBD kg/m2 encapsulated structure (honeycomb TBD mm) + TBD mm Norcoat (TPS): TBD kg per tank (x 4) Table 4-58: Main features 4.5.5.4.2 Overall budget (as introduced to the system)
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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 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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Page 373 and 374: s Inclination (deg) 47.5 47 46.5 46
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Page 389 and 390: s Crew Ingress/Egress Hatch: HMM As
Page 391 and 392: s Element 3: Mars Ascent Vehicle HM
Page 393 and 394: s 4.5.7.5 Budgets Characteristic Va
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Page 401 and 402: s 5 OVERALL CONCLUSIONS HMM Assessm
Page 403 and 404: s 6 APPENDIX A - MARTIAN SURFACE NU
Page 407 and 408: s Figure 6-1: Example of buried rea
Page 411 and 412: s 7 APPENDIX B - REFERENCES [RD1] C
Page 413 and 414: s [RD26] IES2, Phase A0: Final Repo
Page 417 and 418: s [RD85] Mars Transportation Enviro
Page 419 and 420: s 8 APPENDIX C - ACRONYMS AAA Avion
Page 421 and 422: s MLI Multi-Layer Insulation MMH Mo
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