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s 4.5.6 Mechanisms Table 4-59: Overall budget HMM Assessment Study Report: CDF-20(A) February 2004 page 388 of 422 4.5.6.1 Requirements and design drivers The HMM science requirements do not state any specific requirements applicable to the MAV Mechanisms. As a result of the MAV’s configuration, the following necessary mechanism and their requirements can be derived: • Vehicle Connections o Berthing & Docking Capability � Mars Ascent Vehicle • Berthing & Docking in Martian orbit • Un-docking during Martian orbit • Crew Egress Hatches o External Hatches and Locking Mechanism at the TV Docking Port and SHM Separation I/F. • Vehicle Stage Separation System o Release & Separation of Ascent Stage1. • Egress Hatch (MAV/TV I/F) contamination protection layer (disposable). 4.5.6.2 Assumptions and trade-offs Vehicle Connection In-orbit: The following assumptions have been derived as a result of the study:- • The same Berthing and docking Mechanism shall be used throughout the system- IBDM o Androgynous system- identical mechanism mounted to both vehicles o Full redundancy of system provided o Full Internal Mechanism redundancy o Treble redundancy for release/emergency release. o Mechanism independent of hatch door. o Hatch door diametre limited to ingress/egress suitability (diameter 813 mm).
s Crew Ingress/Egress Hatch: HMM Assessment Study Report: CDF-20(A) February 2004 page 389 of 422 Once on the Martian surface, the external face of the hatch will be exposed to the Martian atmosphere and will thus be contaminated. Once the MAV has re-docked with the TV in Mars orbit, the hatch is opened to allow egress of the astronauts. This will expose the external face of the hatch to the inner habitable volume. Therefore a disposable, cover shall be implemented, to be disposed of during MAV orbit prior to Berthing & Docking. 4.5.6.3 Baseline design 4.5.6.3.1 Vehicle connections The International Docking and Berthing Mechanism shall be implemented for the TV/DM Interface. Figure 4-120: International Berthing & Docking Mechanism The IBDM has the following mechanical characteristics: • Interface loads (at the sealing interface)- acting simultaneously while docked (Flightlimit) o Axial load (1200 lbf) 5338 N o Shear load (1000 lbf) 4448 N o Bending moment (80000 in*lbf) 9039 Nm o Torsion moment (70000 in*lbf) 7909 N*m • Internal Pressure (16 psi) 110316.1 Pa • Life 15 years, Functional Life 20 Berthing/un-berthing or Docking/undocking cycles 4.5.6.3.2 Crew egress hatches Sealable hatches are required for the following I/Fs • MAV to TV • MAV to SHM
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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 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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