ESA Document - Emits - ESA

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s Liquid Metal cooled thermoelectric reactor Table 6-1: Comparison of basic reactor design choices 6.4 Radiation protection and shielding issues Gas-cooled particle bed Brayton reactor Electric power [kW] 50 50 Thermal power [kW] (efficiency in %) Core mass (fuel mass) [kg] 186 (54) 1250 (4%) 185 (26.9%) HMM Assessment Study Report: CDF-20(A) February 2004 page 406 of 422 1075 (93) (rad refl. Be: 622 kg) (axial refl. BeO: 218 kg) Power conversion [kg] 371-712 340 Radiator mass [kg] 718 (steel: 618 kg) (mercury: 100 kg) Packaging [kg] 111-180 250 Total Mass [kg] 1386-1796 1665 Size (diam/height) [m] Core: 0.45/0.6 Conv.Syst: 0.5/0.4 Both designs make use of Martian regolith for additional shielding purposes. For the purpose of this preliminary assessment, an all-side shielding requirement is assumed together with an acceptable dose limit at about 100 metres from the reactor site. According to preliminary calculations such a shield would need about 10 tonnes of Martian regolith, distributed in an about 5 metre radial layer and an about 3 metre axial (assuming a cylindrical reactor core) layer. Options of using locally produced binding materials and deepening the core into an (artificial) hole need to be further explored. An example for a buried reactor core with a subsurface heat rejection unit is shown in Figure 6-1. n/a Core: 0.8(0.17)/1.5 Conv.Syst: 0.8/1.2
s Figure 6-1: Example of buried reactor core. Figure 6-2: LM reactor design (L) and GC reactor design (R) HMM Assessment Study Report: CDF-20(A) February 2004 page 407 of 422 The liquid metal cooled reactor (LMR) with thermoelectric power conversion and radiative head rejection system was considered more conservative than the gas-cooled particle bed rector (GCR) with a Brayton cycle and forced convection waste head removal using the Martian atmosphere. The LMR was thus chosen as the prime choice, leaving the GCR design as the more advanced alternative. 6.5 Reactor operation
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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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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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Page 373 and 374: s Inclination (deg) 47.5 47 46.5 46
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Page 385 and 386: s 4.5.5.3 Baseline thermal design H
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Page 411 and 412: s 7 APPENDIX B - REFERENCES [RD1] C
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Page 419 and 420: s 8 APPENDIX C - ACRONYMS AAA Avion
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