ESA Document - Emits - ESA

s
PROJECT
Assessment Study
Report: CDF-20(A)
February 2004
page 12 of 422
FIGURE 4-23: CREW ACTIVITY SCHEDULE DURING MARTIAN SURFACE STAY ............................................................271
FIGURE 4-24: METABOLIC NEEDS AND PRODUCTS OF THE CREW................................................................................271
FIGURE 4-25: EVA SCENARIO....................................................................................................................................273
FIGURE 4-26: TOTAL PRESSURE VS. OXYGEN IN ATMOSPHERE ..................................................................................275
FIGURE 4-27: MARS SHM LSS DESIGN .....................................................................................................................277
FIGURE 4-28: MARS ALBEDO (L), ARS THERMAL INERTIA(R) ....................................................................................281
FIGURE 4-29: MARTIAN DAY DURATION VERSUS LATITUDE AND LS (L), SOLAR FLUX VERSUS LS (R) ......................281
FIGURE 4-30: GROUND TEMPERATURE VERSUS LOCAL TIME AND LATITUDE .............................................................282
FIGURE 4-31: SKY TEMPERATURE VERSUS LATITUDE (L), SKY TEMPERATURE VERSUS LATITUDE (R) ......................282
FIGURE 4-32: BOTTOM RADIATOR FACING GROUND SINK ..................................................................................................285
FIGURE 4-33: LOCAL SUN FLUX ON SHM (EQUINOX, LAT. 0).............................................................................................285
FIGURE 4-34: SENSITIVITY RAD. VERSUS SINK AND SUN FLUX (EQUINOX, LAT. 0)..................................................................285
FIGURE 4-35: SHM RADIATOR AND LOCATION ...............................................................................................................286
FIGURE 4-36: SURFACE HABITATION MODULE / PRIMARY LOOP PRINCIPLES........................................................................286
FIGURE 4-37: CLRC BEAGLE2 STUDY (L), AEROGEL THERMAL CONDUCTIVITY VERSUS PRESSURE (R) ...................................287
FIGURE 4-38: INSULATION LAYOUT ...........................................................................................................................287
FIGURE 4-39: POWER REQUIRED TO MAINTAIN TEMPERATURE............................................................................................288
FIGURE 4-40: THERMAL SYSTEM CONFIGURATION.....................................................................................................289
FIGURE 4-41: EQUIVALENT EFFICIENCY AND BOIL-OFF..............................................................................................290
FIGURE 4-42: NUMBER OF TANKS AND BOIL-OFF AS FUNCTION OF TANK DIAMETER FOR LOX AND H2......................290
FIGURE 4-43: CRYOCOOLER HEAT LIFT FOR THE HYDROGEN STORAGE......................................................................291
FIGURE 4-44: CRYOCOOLER HEAT LIFT AS FUNCTION OF THE NUMBER OF LAYERS AND TANK DIAMETER .................292
FIGURE 4-45: MEV MODES.......................................................................................................................................296
FIGURE 4-46: DM POWER INPUTS ..............................................................................................................................297
FIGURE 4-47: SHM POWER INPUTS............................................................................................................................298
FIGURE 4-48: MAV POWER INPUTS...........................................................................................................................299
FIGURE 4-49: POWER INPUTS AT MEV LEVEL ...........................................................................................................300
FIGURE 4-50: EXAMPLE OF DATA (SOLAR FLUX) FROM THE MARS CLIMATE DATABASE .........................................301
FIGURE 4-51: PRIMARY FC WITH AIR+H2 AS REACTANTS ........................................................................................304
FIGURE 4-52: REGENERATIVE FUEL CELL WITH O2/CO/H2 AS REACTANTS ...............................................................305
FIGURE 4-53: R-SOFC POTENTIAL SYSTEM ON MARS ...............................................................................................305
FIGURE 4-54: SOLAR IRRADIANCE ON THE MARTIAN SURFACE DURING ONE MARTIAN YEAR ...................................307
FIGURE 4-55: PERIODS FOR WHICH LANDING CANNOT BE PERFORMED BASED ON SOLAR-CELL DESIGN.....................307
FIGURE 4-56: LIST OF POWER ARCHITECTURE OPTIONS FOR SURFACE OPERATIONS...................................................308
FIGURE 4-57: MASS COMPARISON FOR THE EIGHT ARCHITECTURE OPTIONS ..............................................................308
FIGURE 4-58: AREA COMPARISON OF DEPLOYED SOLAR ARRAYS FOR THE EIGHT ARCHITECTURE OPTIONS ...............309
FIGURE 4-59: COMPARISON OF REQUIRED VOLUME FOR THE EIGHT ARCHITECTURE OPTIONS....................................309
FIGURE 4-60: MASS BUDGET OF OPTION 1 SHM POWER SUBSYSTEM........................................................................310
FIGURE 4-61: EVAS DATA RATES AND FREQUENCIES, RESPECTIVELY .......................................................................315
FIGURE 4-62: COMMUNICATION FREQUENCIES USING A REPEATER AND DATA RATES FROM FIGURE 4-61.................316
FIGURE 4-63: SAMPLE TRANSFER SCHEMATIC II........................................................................................................323
FIGURE 4-64: SAMPLE TRANSFER SCHEMATIC II........................................................................................................324
FIGURE 4-65: BIO-LOCK PRINCIPLE............................................................................................................................328
FIGURE 4-66: SHM MASS DISTRIBUTION...................................................................................................................330
FIGURE 4-67: ASSUMED ATMOSPHERIC DENSITY AND TEMPERATURE MODEL .........................................................332
FIGURE 4-68: ALTITUDE OVER TIME FOR SEVEN REGARDED CASES..........................................................................333
FIGURE 4-69: MACH NUMBER OVER TIME (L) AND ALTITUDE (R) FOR REGARDED CASES .......................................333
FIGURE 4-70: DYNAMIC PRESSURE OVER TIME (L) AND ALTITUDE (R) FOR REGARDED CASES ...............................334
FIGURE 4-71: G-LOAD OVER TIME (L) AND ALTITUDE (R) FOR REGARDED CASES...................................................334
FIGURE 4-72: ENTRY VELOCITY (L) AND ENTRY PHASE DURATION (R) AS FUNCTION OF ENTRY ANGLE ................335
FIGURE 4-73: PEAK DYNAMIC PRESSURE (L) AND PEAK G-LOAD (R) AS FUNCTION OF ENTRY ANGLE....................335
FIGURE 4-74: SIZE OF DEORBIT BURN AS FUNCTION OF ENTRY ANGLE .....................................................................335
FIGURE 4-75: BENT BICONIC SHAPE ...........................................................................................................................337
FIGURE 4-76: IBD SHAPE...........................................................................................................................................337
FIGURE 4-77: IBD SHAPES.........................................................................................................................................338
FIGURE 4-78: AERODYNAMIC COEFFICIENTS COMPARISON........................................................................................338