ESA Document - Emits - ESA

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s Real trajectory Nominal trajectory Caution tube Warning tube HMM Assessment Study Report: CDF-20(A) February 2004 page 348 of 422 Figure 4-89: Caution and warning tubes around the nominal path In general, the control system strategies shall be robust for the flight conditions at specific Mach numbers and dynamic pressures chosen by the control engineer along the complete flight path. Assuming a TAEM required accuracy of 30 km, the allowable flyable corridor is a tube defined by a limit flight path angle. Allowable TAEM cone 10 km 30 km 300 m Target Figure 4-90: Landing cone (flyable corridor) TAEM required accuracy Allowable landing cone Landing accuracy with active automatic GNC
s 4.4.5.3.2 GNC equipment HMM Assessment Study Report: CDF-20(A) February 2004 page 349 of 422 The MEV will be fully three-axis stabilized control entry vehicle. The MEV has to be able to deploy the drogue chute at a given Mach speed (Mach 2.0 is the baseline at about 10 km). This will be achieved by means of an IMU. This IMU will also be used during the powered phase. The mass and power budget can be found in the chapter 4.5.2 explaining that phase. The time sequence for the deployment of the main chute and release of front cover will be implemented in the computer on-board. This equipment is taken into account in the Data Handling chapter 4.5.9. Figure 4-91 shows a schematic view of the foreseen GNC equipment. There is a possibility of manual control by the crew in case of failure of the automatic system. NAVIGATION IMU Altimeter LIDAR Camera GUIDANCE Backup manual control system: display + Joysticks On-board On board Computer CONTROL Automatic loop Off-line Off line reference trajectory Manual loop Thrusters Figure 4-91: MEV GNC equipment For stability and controllability reasons, the thrusting capability is as follows: • The design of the reaction control system is performed based on the attitude controller requirements. • The foreseen RCS system is composed of eight thrusters. With 8 thrusters, it is possible to provide thrust moment of yaw, pitch and roll, according to the following scheme: • for positive roll moment, thruster pods 1, 3, 5, and 7 are fired; no thrust force generated • for negative roll moment, thruster pods 2, 4, 6, and 8 are fired; no thrust force generated • for positive pitch moment, thruster pods 3, and 8 are fired; thrust force generated • for negative pitch moment, thruster pods 4, and 7 are fired; thrust force generated • for positive yaw moment, thruster pods 2, and 5 are fired; thrust force generated • for negative yaw moment, thruster pods 1, and 6 are fired; thrust force generated To generate yaw and pitch moments, forces also are generated. However, they will not have a significant impact on the point-mass motion of the spacecraft, because these forces are considerably lower than the aerodynamic forces.
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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 355 and 356: s Finally, the Figure 4-97 shown th
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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
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Page 385 and 386: s 4.5.5.3 Baseline thermal design H
Page 389 and 390: s Crew Ingress/Egress Hatch: HMM As
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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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