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s Radio Frequency Finder System (RFF) Star Tracker (STR) Inertial Measurement Unit (IMU) LIDAR Camera Infra-red sensor LIDAR 2 X IMU 2 x SUN sensor Camera RF system Validity range 4000 km … 0.5 km 0o … 360o 0o … 360o 0o … 360o 0o /s … 360 o 0 /s 0g … 5g o … 360o 0o /s … 360 o /s 0g … 5g 5000 m .. 0m 200m … 0m Accuracy 10 m D ∈ [1km,3000m] 1 m D ∈ [100m,1000m] 0.7 m D ∈ [10m,100m] 0.07 m D ∈ [0m,10m] ±0.3 deg ±0.3 deg 1 deg/hr drift 2% error in accel. 2 m, 2mrad D ∈ [1km,5000m], 0.2 m, 2mrad D ∈ [100m ,1km] 0.02 m, 20 mrad D ∈ [0m,100m] 0.1 m, 50 mrad D ∈ [0m,50m] Table 4-53: GNC equipment characteristics Spacecraft Dynamics and Kine matics Guidance, Navigation, and Control Comments 4 antennae with FoV:120 deg Wheels Figure 4-111: GNC schematic of the orbiter FoV: 25 deg NA FoV: 10 deg FoV: 10 deg Position control Thrusters Attitude control Thrusters SADM HMM Assessment Study Report: CDF-20(A) February 2004 page 376 of 422 4.5.2.6 Budgets Table 4-54 shows the mass and power budget of the baseline design for the GNC equipments.
s HMM Assessment Study Report: CDF-20(A) February 2004 page 377 of 422 Element 3: Mars Ascent Vehicle MASS [kg] Unit Element 3 Unit Name Quantity Mass per Maturity Level Margin Total Mass Click on button below to insert new unit quantity excl. margin incl. margin 1 IMU 2 2.500 Fully developed 5 5.3 2 Altimeter 1 1.000 Fully developed 5 1.1 3 LIDAR 1 4.000 To be developed 20 4.8 4 Camera 1 3.500 To be modified 10 3.9 5 Display 1 0.200 To be developed 20 0.2 6 Hand controls and buttons 2 0.800 To be developed 20 1.9 7 Electromecanic equipment 3 3.000 To be developed 20 10.8 8 Rendez-vous joysticks 4 0.200 To be developed 20 1.0 9 Rendez-vous TV 1 2.500 To be modified 10 2.8 10 Rendez-vous Radio Frecuency System 1 4.000 To be modified 10 4.4 11 Rendez-vous Camera 1 2.500 To be modified 10 2.8 12 Rendez-vous LIDAR 1 4.000 To be developed 20 4.8 - Click on button below to insert new unit To be developed 20 0.0 ELEMENT 3 SUBSYSTEM TOTAL 12 38.1 14.4 43.6 Table 4-54: GNC equipment: mass budget Figure 4-112 shows the RvD budget in terms of time and fuel consumption. Delta V budget (m/s) 60 50 40 30 20 10 Impulsive Hohmann Transfer Applied Delta V Station Keeping Forced Motion Station Keeping Forced Motion Free Drift Delta V budget 0 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 Time (s) 4.5.2.6.1 Manual rendezvous backup system Figure 4-112: RvD budgets: time and fuel This manual system is based on the one that is on-board the Soyuz. The astronaut controls the vehicle by manually translating and rotating around its centre of gravity. In order to do this the astronaut needs to perform a loop with these steps.
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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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Page 373 and 374: s Inclination (deg) 47.5 47 46.5 46
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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
Page 389 and 390: s Crew Ingress/Egress Hatch: HMM As
Page 391 and 392: s Element 3: Mars Ascent Vehicle HM
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Page 403 and 404: s 6 APPENDIX A - MARTIAN SURFACE NU
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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
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