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s Summary: 4.3.10 Structures Element Mass Bio-lock quarantine containers- SHM 224 Kg Container Mass Transported to Mars 509.8 Kg Estimated Sample Mass 64.5 Kg Sample & Container Mass returned 574.3 Kg Table 4-35: Budget summary HMM Assessment Study Report: CDF-20(A) February 2004 page 330 of 422 4.3.10.1 Requirements and design drivers For the design of the SHM on the Martian surface the following set of general requirements were taken into account: • Compatibility with the vehicle launcher Energia-induced mechanical loads • MEV centre of gravity has to be as low as possible, for stability during landing and on Martian surface. All module structures shall provide the mechanical support to ensure mission success. 4.3.10.2 Assumptions and trade-off The MAV centre of gravity is assumed to be at 1 m, with the referential at the bottom part of it. The aeroshell’s centre of gravity is assumed to be in the middle of it. 4.3.10.3 Baseline design The SHM consists of an aluminium cylinder with a cone on the top, of 4mm thickness. It has a total length of 7 m and a maximum diameter of 3.6 m. As preliminary analysis the stiffener’s mass was assumed to be half of the skin mass. The centre of gravity of the MEV was achieved for two different situations, case 1: including the aeroshell and parachutes, SHM and MAV; case 2: excluding the aeroshell and parachutes. To have the MEV centre of gravity as low as possible the centre of gravity of the SHM also has to be as low as possible. For the determination of it, the SHM was divided in equal parts and to each part was attributed a certain percentage of its mass. Figure 4-66 shows the mass distribution that was optimal for the centre of gravity. Figure 4-66: SHM Mass distribution
s HMM Assessment Study Report: CDF-20(A) February 2004 page 331 of 422 With the mass indicated at the bottom of the SHM, for the two cases analysed, the centre of gravity of the MEV is: • CASE 1: 5.04 m • CASE 2: 4.98 m After a preliminary analysis using a cantilever beam, the first lateral eigen-frequency results in 72.8 Hz for the SHM. The interior of the SHM is divided into two floors. The floor of the second level is assumed to be a plate, which has to support a uniform maximum load of 10 tonnes. This plate is made of aluminium, with 3.592 m diameter and 4 mm thick, [RD2] For strength of the SHM, it was assumed to have a ring every 0.5 m. The aim of these rings is to give the necessary rigidity to the SHM. The design requirement used for the rings, for a twinwalled cylinder, was the Shanley design requirement: 4 N cr R ( EI ) Ring = 1273. L Where Ncr is the axial load to be applied, R the radius of the cylinder and L the mutual distance between the rings. With this requirement the dimensions obtained for the aluminium rings was: 110mm for cross-section length and 5 mm for cross section thickness and web thickness, with a C cross-section area. 4.3.10.4 Budget Item Nr. Mass [kg] Margin [%] Mass with Margin [kg] SHM Skin 1 931.79 5 978.38 SHM Stiffeners 1 465.89 0 465.89 Ring Cylindrical part SHM 14 49.50 0 49.50 Ring Cone Part SHM 1 20.16 0 20.16 Floor-SHM 1 112.28 5 117.89 Support Cone 1 72.45 10 79.70 TOTAL 2355 4.4 Descent Module Table 4-36: SHM structures mass budget 4.4.1 Entry Analysis The entry analysis was performed as part of the Mission Analysis contribution to the CDF study. 4.4.1.1 Requirements and design drivers The main requirement was to obtain a feasible entry trajectory for a low-lift inflatable aeroshell. De-orbiting shall take place from a low circular orbit. The aeroshell shall be guided via controlled variation of the bank angle, this changes the direction of the lift vector. Violent or complex control actions shall be avoided and a wide margin shall remain between the current value of the control parameter and the control boundaries, at the initial part of the entry.
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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 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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