ESA Document - Emits - ESA

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s PROPULSION 1% CREW 43% ECLSS 0% RISK REDUCTION POTENTIAL PER TV-SUB-SYSTEM LAUNCHER 0% GNC & LANDING 1% AOCS 4% COMMS 1% STRUCTURES 18% MECH/PYROS 1% TH.CTRL 1% POWER 12% CMND+DH 18% LAUNCHER PROPULSION AOCS STRUCTURES MECH/PYROS TH.CTRL POWER CMND+DH COMMS GNC & LANDING ECLSS CREW HMM Assessment Study Report: CDF-20(A) February 2004 page 104 of 422 Figure 2-58: Risk reduction potential Note that the results must be interpreted as a first trend of the technical risk status, therefore of a purely indicative nature. The risk analysis should be further developed during the project definition to analyse all the system, refine the risk identification and classification, and provide evidence that all the risks have been effectively controlled. The colour codes in Table 2-40 represent (ref: ECSS-M-00-03A risk management): Red: maximum or high risk. Proposed actions: implement new team process or change baseline and seek project management attention at appropriate high management level. Yellow: Medium or low risk. Proposed actions: control, monitor and seek work package management attention. Green: Minimum that is, acceptable risk.
s HMM Assessment Study Report: CDF-20(A) February 2004 page 105 of 422 Risk acceptability Risk domain & scenario (indicative nature) Reason-status Unacceptable 1. Maximum likelihood with catastrophic 3. Numerous critical areas consequences: with uncertain 1. Human factors inadequate to mission. environment definition. 2. EVA Suits inadequate to environment. 4. Research level only. 3. Inadequacy to radiation environment. 5. New project beyond the 4. Landing on Mars failure. status of the art. 5. ECLSS failure. 6. High level of autonomy 2. Maximum likelihood with critical consequences. required for operations. Failures during AIV activities Highly complex Program. Acceptable if 7. Medium likelihood with critical consequences. 8. Qualified technologies but reduction Communications loss. never applied in projects. impossible Numerous modifications of qualified product. Acceptable Others Defined environmental conditions, qualified products, existing processes & facilities. 2.9.8 Risk assessment process example Table 2-40: Risk acceptability Figure 2-59 shows how the analysis is done, following the sequence of steps already mentioned at section 2.9.5. Loss of ECLSS Analysis performed per Mission Phase Loss of Propulsion Loss of DHS Scenario Loss of THM OR Loss of Comms OR Loss of MEV Loss of TCS Loss of mission Mission Objectives NOT met Loss of PWR Loss of ERC OR Loss of crew Crew Sickness Loss of Structure Figure 2-59: Risk assessment process Loss of life OR Likelihood depends on: •Technology readiness status; •Redundancy; •Abort capabilities, etc Loss of Mech. Crash at landing Illness … …
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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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Page 57 and 58: s stack 9 Propellant mass of the ne
Page 65 and 66: s The core supporting structure has
Page 67 and 68: s 2.7.7.1.3 Mars excursion module S
Page 69 and 70: s 2.7.7.1.4 Earth return capsule HM
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Page 77 and 78: s Days on Martian surface 450 400 3
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Page 85 and 86: s % of loss from baseline 20 18 16
Page 87 and 88: s 2.7.15 Sensitivity analysis HMM A
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Page 93 and 94: s Parameters used: • No Shuttle
Page 95 and 96: s 2.8.3.3 Launch 3- Front node Figu
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Page 109 and 110: s 2.10.1.4 Communications HMM Asses
Page 113 and 114: s 2.10.2.2.2 LEO assembly HMM Asses
Page 117 and 118: s Basic RF link Four 70-m Ka-band s
Page 125 and 126: s 3 TRANSFER VEHICLE 3.1 Systems…
Page 127 and 128: s Operational Requirements It shall
Page 129 and 130: s Trans Mars Injection Module Mars
Page 131 and 132: s Figure 3-2: Parallel configuratio
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Page 135 and 136: s Front Node 3.2.3.1.3 EVA systems
Page 137 and 138: s Trans Mars Injection (three stage
Page 139 and 140: s Figure 3-16: Recommendations for
Page 141 and 142: s Factors to be considered Impacts
Page 149 and 150: s Figure 3-24: Baseline design back
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Page 153 and 154: 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 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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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 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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