ESA Document - Emits - ESA

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HMM
Assessment Study
Report: CDF-20(A)
February 2004
page 13 of 422
FIGURE 4-79: 60 DEGREES HALF CONE ANGLE, 25 M BASE DIAMETER.......................................................................339
FIGURE 4-80: AERODYNAMIC COEFFICIENTS VS MACH NUMBER ...............................................................................339
FIGURE 4-81: AERODYNAMIC COEFFICIENTS VS ANGLE OF ATTACK FOR MACH 7.....................................................340
FIGURE 4-82: TOTAL HEAT FLUX VERSUS TIME .........................................................................................................340
FIGURE 4-83: HEAT LOAD VERSUS TIME.....................................................................................................................341
FIGURE 4-84: LANDING-LEG CONFIGURATION ...........................................................................................................342
FIGURE 4-85: COMMUNICATIONS MEV/MAV-TV DURING TAKE OFF – RENDEZVOUS AND UNDOCKING-LANDING...345
FIGURE 4-86: MEV CDF MODEL ..............................................................................................................................346
FIGURE 4-87: GNC DESIGN CYCLE ............................................................................................................................346
FIGURE 4-88: VEHICLE COORDINATE SYSTEMS ..........................................................................................................347
FIGURE 4-89: CAUTION AND WARNING TUBES AROUND THE NOMINAL PATH .............................................................348
FIGURE 4-90: LANDING CONE (FLYABLE CORRIDOR) ................................................................................................348
FIGURE 4-91: MEV GNC EQUIPMENT .......................................................................................................................349
FIGURE 4-92: THRUSTER CONFIGURATION................................................................................................................350
FIGURE 4-93: ENTRY MODES......................................................................................................................................350
FIGURE 4-94: CONTROL LAW.....................................................................................................................................352
FIGURE 4-95: 3DOF AND 6 DOF TRAJECTORIES.........................................................................................................352
FIGURE 4-96: 6DOF TRAJECTORY CHARACTERISTICS ................................................................................................354
FIGURE 4-97: MONTE CARLO RUNS ...........................................................................................................................355
FIGURE 4-98: MOMENTUM BALANCE SYSTEM............................................................................................................356
FIGURE 4-99: MINIMUM FOOTPRINT VS. VERTICAL HEIGHT .......................................................................................358
FIGURE 4-100: VELOCITY AND ALTITUDE OF MEV FROM PARACHUTE OPENING TO LANDING ROCKET FIRING..........361
FIGURE 4-101: CD DATA............................................................................................................................................364
FIGURE 4-102: BASELINE TRAJECTORY STRATEGY ....................................................................................................365
FIGURE 4-103: BASELINE TRAJECTORY AND FLIGHT ENVIRONMENT..........................................................................366
FIGURE 4-104: R & D CONSTRAINTS .........................................................................................................................368
FIGURE 4-105: RENDEZVOUS STRATEGIES .................................................................................................................369
FIGURE 4-106: RENDEZVOUS STRATEGIES ADVANTAGES...........................................................................................370
FIGURE 4-107: RENDEZVOUS STRATEGIES DISADVANTAGES......................................................................................370
FIGURE 4-108: PLANE CHANGE MANOEUVRE RESULTS ..............................................................................................372
FIGURE 4-109: INCLINATION EVOLUTION...................................................................................................................373
FIGURE 4-110: INTERMEDIATE RENDEZVOUS.............................................................................................................374
FIGURE 4-111: GNC SCHEMATIC OF THE ORBITER.....................................................................................................376
FIGURE 4-112: RVD BUDGETS: TIME AND FUEL .........................................................................................................377
FIGURE 4-113: INSTRUMENTATION AND EQUIPMENT USED FOR MANUAL FINAL APPROACH.......................................378
FIGURE 4-114: MAV PROPULSION MODULE .............................................................................................................380
FIGURE 4-115: MAV SOLAR CELLS LOCATION...........................................................................................................381
FIGURE 4-116: MAV BUDGET....................................................................................................................................382
FIGURE 4-117: FLIGHT ENVIRONMENT (FROM TRAJECTORY ANALYSIS)...............................................................................384
FIGURE 4-118: RADIATOR LAYOUT (L), LOK RADIATORS (NOTA: BENT OVER THE YEARS) (R)...............................................386
FIGURE 4-119: ASCENT VEHICLE / PRIMARY AND SECONDARY LOOP PRINCIPLES ..................................................................386
FIGURE 4-120: INTERNATIONAL BERTHING & DOCKING MECHANISM ......................................................................389
FIGURE 4-121: AESTUS ENGINE ..............................................................................................................................392
FIGURE 4-122: CREW ACTIVITY SCHEDULE DURING MARTIAN SURFACE STAY.........................................................394
FIGURE 4-123: METABOLIC NEEDS AND PRODUCTS OF THE CREW..............................................................................395
FIGURE 4-124: MARS MAV LSS DESIGN ..................................................................................................................396
FIGURE 6-1: EXAMPLE OF BURIED REACTOR CORE.....................................................................................................407
FIGURE 6-2: LM REACTOR DESIGN (L) AND GC REACTOR DESIGN (R) ......................................................................407