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s HMM Assessment Study Report: CDF-20(A) February 2004 page 36 of 422 • Impulsive TMI: 3.590 – 3.639 km/s from 400 km LEO • De-orbit burns for 1 st and 2 nd stages: approx 95 m/s and 41 m/s, depending on staging assumptions • Maximum sensitivity of escape manoeuvre: 150 000 km position error at Mars per m/s error in manoeuvre • De-biasing and correction of escape manoeuvre dispersion: Max. 6 times the 3sigmadispersion of the final escape manoeuvre, if performed 7 days after final escape • Declination of escape hyperbola outgoing asymptote with respect to Earth equator: -47º – -62º. This leads to the inclination of the initial LEO, which must also be at least 62º 2.4.4.2 Mars arrival window • Arrival period: 24 October 2033 – 11 November 2033 • Hyperbolic arrival velocity: 3.315 – 3.413 km/s • Impulsive MOI: 1.143 – 1.201 km/s, assuming an initial orbit of 500 x 96000 km (period 4 sols) • Additional ∆v to raise pericentre of jettisoned stage to 3000 km: 48 m/s • Final Orbit Acquisition to 500 km orbit: 1.285 km/s (impulsive) 2.4.4.3 Mars escape window • Escape window: 28 April 2035 – 18 May 2035 • Hyperbolic escape velocity: 2.960 – 2.990 km/s • Impulsive TEI from 500 km orbit: 2.229 – 2.245 km/s • De-biasing and correction of escape manoeuvre dispersion: Maximum 4.6 times the 3 sigma-dispersion of the Mars escape manoeuvre, if performed seven days after Mars escape • Declination with respect to Mars equator: -29º – -32º. This defines the target inclination with respect to the Mars equator, which must be at least 32º. 2.4.4.4 Earth arrival window • Arrival period: 20 October 2035 – 27 November 2035 • Retargeting manoeuvre 60 days before arrival: maximum 25 m/s for change of arrival time by +/- 12 hours • Perigee altitude change from 1000 to 100 m/s (or vice versa, depending on final strategy): 17 m/s. This is applied to ERC or THM, depending on which body needs to be moved • Hyperbolic arrival velocity: 2.999 – 3.052 km/s • Speed at 100 km altitude (not taking into account Earth’s rotation): 11.506 km/sOptions
s HMM Assessment Study Report: CDF-20(A) February 2004 page 37 of 422 All mission opportunities in the 15-year cycle from 2028 through 2043 were studied. The characteristics are listed in Table 2-2. The following assumptions apply for the data in the table: • All cited manoeuvres are impulsive • The maximum TMI, MOI and TEI values are provided for every launch opportunity. This maximum MOI includes only the orbit insertion. The column “Total ∆v” cites the maximum of the subs of all three throughout the launch and return windows. This maximum total is not necessarily equal to the sum of the maximum TMI, MOI and TEI • The column titled “Max. Varr” cites the maximum hyperbolic velocity at the Earth for the respective opportunity • All given durations cite the maximum possible value occurring for a transfer or Mars phase. They do not necessarily add up to the maximum total mission duration given in the last column Mission 2028 2031 2033 2035 2037 2039 2041 2043 Max. TMI [km/s] 3.637 3.717 3.639 3.696 4.005 3.810 3.658 3.619 Max. MOI [km/s] 0.975 1.310 1147 0.794 0.918 0.745 0.707 0.877 E→M cost [km/s] 4.585 4.946 4.786 4.450 4.797 4.492 4.365 4.495 Max. TEI [km/s] 1.977 1.969 2.254 2.595 2.366 2.159 2.053 1.955 Total ∆v [km/s] 6.562 6.915 7.040 7.045 7.163 6.651 6.418 6.450 Max. V arr [km/s] 5.793 4.255 3.052 3.736 2.926 3.091 4.151 5.525 E→M dur. [d] 306 285 200 204 360 342 323 311 Mars dur. [d] 423 490 571 560 390 362 372 405 M→E dur. [d] 256 225 207 271 287 306 334 337 Tot. dur. [d] Table 2-2: Comparison of Characteristics for Opportunities 2028 Through 2043 2.5 Cruise and surface operations 2.5.1 Planetary protection Robotic precursor missions have to verify that life is at least not widespread on Mars. As such, it has to be shown that life is not part of the global dust-cycle. However, even if life is not widespread on Mars, planetary protection regulations for forward and backward contamination have to be applied because astronauts will investigate sites of potential extant or extinct biological activity. A human mission to Mars will contaminate the planet to a certain extent. This forward contamination can be minimised by using appropriate procedures. The philosophy for backward contamination is to break the chain between Mars and Earth. Any contamination of the habitat has to be avoided as this contamination would be transferred to the crew, and hence the Earth. Strict isolation of the crew upon return is not practicable and would be difficult to implement. 971 996 962 1033 997 992 1022 1041
Page 1 and 2: s HMM Assessment Study Report: CDF-
Page 3 and 4: s STUDY TEAM HMM Assessment Study R
Page 5 and 6: s T A B L E O F C O N T E N T S HMM
Page 9 and 10: s L I S T O F F I G U R E S HMM Ass
Page 15 and 16: s L I S T O F T A B L E S HMM Asses
Page 19 and 20: s 1 INTRODUCTION 1.1 Background HMM
Page 21 and 22: s 2 GENERAL ARCHITECTURE 2.1 Study
Page 25 and 26: s 2.2.4.2 Accelerations HMM Assessm
Page 27 and 28: s 2.2.4.4 Temperature and relative
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Page 45 and 46: s Mars Excursion Vehicle Transfer H
Page 47 and 48: s 2.7.5.1 Mission elements dry mass
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Page 51 and 52: s Total mission time (days) 1200 10
Page 57 and 58: s stack 9 Propellant mass of the ne
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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 HMM Assessment Study Report: CDF-
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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 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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s 4.3.9.3 Baseline design 4.3.9.3.1
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s Bio-Lock Masses: Core Samples No.
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s Figure 4-72: Entry Velocity (L) a
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s 2 3.9 233 923.1 347 923 12.3 352
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s Figure 4-85: Communications MEV/M
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s 4.4.5.3.2 GNC equipment HMM Asses
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s 4.4.5.4 Control laws generation H
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s Finally, the Figure 4-97 shown th
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s velocity (m/sec) altitude (km) 50
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s 4.5 Mars Ascent Vehicle 4.5.1 Tra
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s Term Value Unit Radius of equator
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s Inclination (deg) 47.5 47 46.5 46
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s 4.5.3 Structures HMM Assessment S
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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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