ESA Document - Emits - ESA

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s 4000 2000 0 Position PCI x,y,z [km] (blue, red, green) -2000 0 100 200 300 400 500 600 2 0 -2 Velocity PCI x,y,z [km/s] (blue, red, green) -4 0 100 200 300 400 500 600 20 10 0 -10 Angular Rates roll,pitch,yaw [deg/s] (blue, red, green) -20 0 100 200 300 Time [s] 400 500 600 12000 10000 30 20 10 8000 6000 Figure 4-96: 6DoF trajectory characteristics 4.4.5.6 MonteCarlo for performance verification Mach Number [-] 0 0 200 400 600 8 x 10 -3 Density [kg/m3] 6 4 2 0 0 200 400 600 Scale Height [m] 4000 0 200 Time [s] 400 600 HMM Assessment Study Report: CDF-20(A) February 2004 page 354 of 422 The next step in the design is to run a MonteCarlo campaign for performance verification. For this step, the following parameters were scanned during the simulations: • Uncertainty on Mass properties: o mass_delta = 1 % [%] Uncertainty of the nominal mass o CoG_x_delta = 1 % [%] Uncertainty of CoG position in X direction o CoG_y_delta = 1 % [%] Uncertainty of CoG position in Y direction o CoG_z_delta = 1 % [%] Uncertainty of CoG position in Z direction • Uncertainty on Initial state o pos_alt_delta = 0.0 % [m] Uncertainty in initial altitude o pos_LL = 0.03 % [degrees] Uncertainty in latitude/longitude o vel_speed_delta = 0.39 % [m/s] Uncertainty in speed o FPA = 0.129 % [degrees] Uncertainty in flight path angle and azimuth • Uncertainty on Aerodynamic model o total_lift = 10 % o total_drag = 10 % o aerotorque = 10 % • Uncertainty on Atmospheric properties o Atmos_P_D_T = 5 % • Uncertainty on Thrust level o Isp_direction = 0.5 % • Uncertainty on Sensors o IMU = 0.5 % o RA = 10 %
s Finally, the Figure 4-97 shown the MonteCarlo runs. Latitude [deg] [%] Latitude [deg] 49.25 49.24 49.23 49.22 49.21 5 0 -5 49.2 x y z 38.5 38.4 38.3 Lateral Geodetic Position 88.54 88.56 Longitude [deg] 88.58 Mass [metric tons] 49.5 50 CoG position [m] 50.5 3.8 3.85 3.9 -0.04 -0.02 0 0.02 0.04 1.46 1.48 1.5 1.52 Altitude MSL [km] 140 120 100 80 60 40 20 Density 0 -100 0 Dispersion [%] 100 Dispersions of thrust level on thruster number: Velocity Vector 3.3688 3.369 Speed [km/s] 3.3692 3.3694 -5 -4.95 -4.9 -4.85 -4.8 Flight Path Angle [deg] 102.3 102.35 102.4 102.45 102.5 Flight Path Azimuth [deg] Aerodynamic -5 0 Lift Dispersion [%] 5 -5 0 Drag Dispersion [%] 5 -5 0 5 Aero Torque Dispersion [%] 1 2 3 4 5 6 7 8 Lateral Geodetic Position 38.2 120.5 120.6 120.7 120.8 120.9 121 Longitude [deg] 300 200 100 0 5 10 15 20 Peak Heat Flux [kJ/m2] 80 70 Fuel Total [kg] 60 0 5 10 15 20 Total Heat [MJ] 13 12 11 0 5 10 15 20 Peak g-load [-] 2 1.5 1 0 5 10 15 20 MC Run Number Dyn. Pressure [Pa] -20 -25 -30 0 5 10 15 20 Beta max [deg] 2 4000 3000 2000 1000 1 AoA min/max [deg] 0 0 5 10 15 20 MC Run Number 0 0 200 Time [s] 400 600 Velocity Vector 0.4 0.5 0.6 0.7 Speed [km/s] 0.8 0.9 1 -24 -22 -20 -18 -16 -14 -12 -10 Flight Path Angle [deg] 105 110 115 120 125 130 Flight Path Azimuth [deg] Bank Angle [deg] Drag Acceleration [m/s2] 20 15 10 5 0 -5 0 200 200 Time [s] 400 600 100 0 -100 Figure 4-97: Monte Carlo runs -200 0 200 Time [s] 400 600 HMM Assessment Study Report: CDF-20(A) February 2004 page 355 of 422
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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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Page 373 and 374: s Inclination (deg) 47.5 47 46.5 46
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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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