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s Minimum Foot-print dimension 'L' (m) 12 10 8 6 4 2 Leg Minimum Footprint Dimension (L) as a function of Vertical Height at Thrust Cut-off (& Vertical Velocity Component- Max. 2 m/s) and Horizontal Velocity [Hv]- Landing Mass 42 tonnes, CoG at 6.0 m Leg Footprint Dimension (Hv=1.5 m/s, Vv0= 0 m/s) Leg Footprint Dimension (Hv=1.5 m/s, Vv0= max.) Leg Footprint Dimension (Hv=1 m/s, Vv0= 0 m/s) Leg Footprint Dimension (Hv=1 m/s, Vv0= max.) Leg Footprint Dimension (Hv=0.5 m/s, Vv0= 0 m/s) Leg Footprint Dimension (Hv= 0.5 m/s, Vv0= max.) Leg Foot-Print Dimension- Envelope Limit Leg Foot-Print Dimension- Structure Dia Limit HMM Assessment Study Report: CDF-20(A) February 2004 page 358 of 422 0 0 0.15 0.3 0.45 0.6 0.75 0.9 1.05 1.2 1.35 1.5 1.65 1.8 1.95 Thrust 'Cut-off' Height (m) Figure 4-99: Minimum footprint vs. vertical height The main structure of the SHM is about 4 m in diameter and the maximum allowable envelope dimension is about 6 m in diameter. From the graph it can be seen that for a horizontal velocity component up to 1 m/s, a foot print dimension within about 6 m in diameter can be realised for all vertical velocity cases and therefore a deployable landing foot is not required. What can also be observed is that a residual vertical velocity is beneficial to the landing as this component acts against the tendency to topple and leads to a smaller footprint dimension. For the higher horizontal velocity of 1.5 m/s, it can be seen that, to realise a footprint dimension within the enveloping limit, an additional (residual) vertical velocity component is required (either residual velocity due to the descent of the engine thrust cut-off above about 0.5 m) i.e. a near zero residual height and vertical velocity at engine thrust cut-off with a horizontal velocity of 1.5 m/s will lead to the system toppling. In conclusion, if the a limit to the residual horizontal velocity is set to 1 m/s (requirement on the control system), a non-deployable or static landing leg system can be realised within the enveloping dimension of about 6 m in diameter that can remain stable when subject to the residual vertical velocity and height control dispertions. This shall be assumed to be the baseline. Additional conclusions from the analysis performed are; • A Large Mass aids stability as does a residual vertical velocity and height component.. • The landing system leg has to be designed assuming a single leg contact as worst case. • Leg Loading of the order of 350 000 N (estimate of the load along the angular vector calculated above). o This load is mainly influenced by the vertical Force components (Mass, Cut-off Height, Residual Vertical Velocity). L L
s HMM Assessment Study Report: CDF-20(A) February 2004 page 359 of 422 It should also be noted, that the landing feet minimum footprint dimension is (largely) independent of the Lander’s mass as the mass term is present in both the Vertical and Horizontal resultant force components. The major parameter affecting the footprint dimension is the CoG or CoM position. The footprint dimension is a direct ration of the CoM height, which should be kept as low as possible to maintain the required footprint within the envelope dimension of ∅6 m. 4.4.6.3 Baseline design 4.4.6.3.1 Vehicle separation Due to the potentially large diameter of the MAV to Propulsion module, the separation of the MAV from the propulsion unit prior to entry and descent launch, shall be realised with a pyrotechnically cut bolts at up to four locations around the I/F. 4.4.6.3.2 Heat shield jettison Due to the four point mounting of the heat-shield on to the four landing system feet, the jettison shall be realised with a pyrotechnically cut bolts at the four foot locations. 4.4.6.4 Budgets Element 1: Descent Module Unit Element 1 Unit Name Quantity Click on button below to insert new unit Mass per quantity excl. margin MASS [kg] Maturity Level Margin Total Mass incl. margin 1 Pyro Release system- De-orbit 4 5.0 To be modified 10 22.0 2 Separation Spring Units- De-orbit 4 5.0 To be modified 10 22.0 3 Pyro Release System- Heat-shield 4 5.0 To be developed 20 24.0 4 To be developed 20 0.0 5 To be developed 20 0.0 - Click on button below to insert new unit 0.0 To be developed 20 0.0 ELEMENT 1 SUBSYSTEM TOTAL 3 60.0 13.3 68.0 4.4.7 Parachute design 4.4.7.1 Requirements and design drivers Table 4-44: DM Mass Budget The parachutes for the MEV Descent Module provide a means of decelerating the vehicle from the high velocity reached at the end of the guided entry to a velocity that can be handed by the system of landing rockets. The design is driven by the velocity and altitude requirements at the beginning and end of the parachute descent phase. These are summarised below.
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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 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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