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s HMM Assessment Study Report: CDF-20(A) February 2004 page 390 of 422 The hatch diametre is sized to fit within the (current) IBDM tunnel; ≈800 mm. Both hatches will require Latch and Seal mechanisms. Mass estimates shall be realised using a ‘simple geometry’ model. A disposable cover shall be implemented over the outer surface of the Egress hatch door. The method of separation shall be pyrotechnic bolts. Vehicle Separation: The separation of the MAV first and second stages shall be realised with a pyrotechnic operated Clamp-band of about ∅1.5 to ∅2.0. 4.5.6.4 Budgets Element 3: Mars Ascent Vehicle MASS [kg] DIMENSIONS [m] Unit Element 3 Unit Name Quantity Mass per Maturity Level Margin Total Mass Dim1 Dim2 Dim3 Click on button below to insert new unit quantity incl. margin Length Width Height 1 Docking Mechanism- IBDM 1 334.4 To be modified 10 367.8 1.371 0.813 0.254 2 Electronic Box- IBDM 6 8.8 To be modified 10 58.1 0.4 0.25 0.25 3 Hatch Door- Egress External 2 18.0 To be developed 20 43.2 0.9 0.01 4 Hatch Door Locking Mechanisms- Egress Externa 2 120.0 To be developed 20 288.0 0.95 0.80 0.05 5 Hatch Door Cont. Protection Cover 1 15.0 To be modified 10 16.5 6 Clamp-band- Stage 1/Stage 2 I/F 1 15.6 To be modified 10 17.2 1.200 - Click on button below to insert new unit To be developed 20 0.0 - ELEMENT 3 SUBSYSTEM TOTAL 6 693.8 14.0 790.8 Table 4-60: MAV Mass Budget Unit Element 3 Unit Name Quantity Ppeak DESM DESM DESM Click on button below to insert new unit Pon Pstby Dc 1 Docking Mechanism- IBDM 1 784.0 1.1 2 Electronic Box- IBDM 6 3 Hatch Door- Egress External 2 4 Hatch Door Locking Mechanisms- Egress Externa 2 5 Hatch Door Cont. Protection Cover 1 6 Clamp-band- Stage 1/Stage 2 I/F 1 - Click on button below to insert new unit - ELEMENT 3 SUBSYSTEM TOTAL 6 0.0 784.0 0.0 Table 4-61: Power Budget- Descent Element 3: Mars Ascent Vehicle AND POWER SPECIFICATION PER M Unit Element 3 Unit Name Quantity Ppeak RVDM RVDM RVDM Click on button below to insert new unit Pon Pstby Dc 1 Docking Mechanism- IBDM 1 1806.0 12.7 2 Electronic Box- IBDM 6 152.0 75.7 3 Hatch Door- Egress External 2 4 Hatch Door Locking Mechanisms- Egress Externa 2 5 Hatch Door Cont. Protection Cover 1 6 Clamp-band- Stage 1/Stage 2 I/F 1 - Click on button below to insert new unit - ELEMENT 3 SUBSYSTEM TOTAL 6 0.0 1958.0 0.0 Table 4-62: Power Budget- Docking
s Element 3: Mars Ascent Vehicle HMM Assessment Study Report: CDF-20(A) February 2004 page 391 of 422 TEMPERATURE REQs [deg C] Unit Element 3 Unit Name Quantity Operation Operation NOP NOP Click on button below to insert new unit (max) (min) (max) (min) 1 Docking Mechanism- IBDM 1 50.0 -50.0 100.0 -100.0 2 Electronic Box- IBDM 6 50.0 -20.0 70.0 -50.0 3 Hatch Door- Egress External 2 4 Hatch Door Locking Mechanisms- Egress Externa 2 5 Hatch Door Cont. Protection Cover 1 6 Clamp-band- Stage 1/Stage 2 I/F 1 - Click on button below to insert new unit - ELEMENT 3 SUBSYSTEM TOTAL 6 4.5.7 Propulsion Table 4-63: Thermal Constraints 4.5.7.1 Requirements and design drivers The payload mass for ascent is estimated 4200 kg. A thrust of 130 kN is required for the first stage to maintain the T/M ratio at acceptable value A thrust of 20 kN is required for the second stage to maintain the T/M ratio at the same value 4.5.7.2 Assumptions and trade-offs The ascent manoeuvre is staged in with two different modules. Only storable bi-propellant are considered. No attitude and steering manoeuvres are considered 4.5.7.3 Baseline design 1 st stage Four improved pump feed version of the AESTUS engine has been chosen as propulsion system for the first stage. The engine derives from the AESTUS pressure feed engine used in Ariane-5 upper stage. Recently this engine was proposed in a pump-feed version with an increase of the Isp performances and reduced system mass derived from the relaxed pressure tank operating system typical of pump feed engines. The engine nozzle has been resized (shortened) for the Martian atmosphere with reduced performances in Isp and thrust level in comparison to the vacuum performances The propulsion system presents the following characteristics:
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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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Page 355 and 356: s Finally, the Figure 4-97 shown th
Page 361 and 362: s velocity (m/sec) altitude (km) 50
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Page 373 and 374: s Inclination (deg) 47.5 47 46.5 46
Page 379 and 380: s 4.5.3 Structures HMM Assessment S
Page 383 and 384: s 4.5.5 Thermal HMM Assessment Stud
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
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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ESA Document - Emits - ESA

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