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s Initial and final conditions Vehicle characteristics and environment State vector measured using sensors Reference trajectory MEV MEV Model Model Thruster activation: Number, duration, and frequency State vector errors HMM Assessment Study Report: CDF-20(A) February 2004 page 346 of 422 Figure 4-86: MEV CDF Model The parameters that can be optimised are the initial flight path angle, initial azimuth, initial flight path velocity and the time duration for the entry. The purpose of the study is to select the appropriate values of those parameters. This study is also concerned to establish not only the 3DoF optimal entry trajectory but also the corresponding 6DoF full closed loop controlled trajectory. 4.4.5.2 Assumptions and trade-offs 4.4.5.2.1 MEV GNC design cyle Figure 4-87 shows the design cycle of the GNC of the MEV: Entry Entry corridor corridor design, design, Equipment Equipment design, design, Modes Modes design design Guidance Guidance law law generation generation Compute Compute optimal optimal 3DoF 3DoF controlled controlled entry entry trajectory trajectory Boundary Boundary and and path path constraints constraints Vehicle Vehicle features features Mars Mars environment environment Control Control law law generation generation MonteCarlo MonteCarlo for for performance performance verification verification Figure 4-87: GNC design cycle Compute Compute optimal optimal 6DoF 6DoF controlled controlled entry entry trajectory trajectory Final Final 6DoF 6DoF trajectory trajectory and and GNC GNC design design
s HMM Assessment Study Report: CDF-20(A) February 2004 page 347 of 422 The cycle starts with the collection of all constraints. Then, an optimal 3DoF trajectory is computed. From the corridor requirements, the equipment design and the mission arc GNC modes, a guidance law is generated. Next the control algorithms are developed to be able to follow the previously established guidance law, and finally a new 6DoF trajectory is computed in closed loop and with mathematical models of sensors and actuators. MoteCarlo analysis are run for performance verification and validation. Figure 4-88 shows the vehicle model coordinate and angle conventions: x A α -27,5deg x B v inf 4.4.5.3 3DoF optimal trajectory Axial Normal Pitch z A Drag Figure 4-88: Vehicle coordinate systems The optimal trajectory has been described in the relevant chapter 4.4.1. 4.4.5.3.1 Entry corridor design The performance factors to take into account are controllability, stability, algorithm speed, computational loads, etc. Predefined yellow (caution) and red tubes (warning) around the nominal path have been established to compute the controllability of the system around the pre-established optimal trajectory. Lift z B
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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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Page 373 and 374: s Inclination (deg) 47.5 47 46.5 46
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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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