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Splashdown Spacecraft Landing

HEAT SHIELD JETTISONED BY 24,000 FEET AFTER TIME DELAY DROGUE CHUTES DEPLOYED REEFED AFTER TIME DELAY DROGUE CHUTES DEPLOYED REEFED MAIN CHUTES FULLY OPENED AFTER BEING REEFED DROGUE CHUTES RELEASED AND MAIN CHUTES DEPLOYED REEFED BY 10,000 FT DROGUE CHUTES RELEASED AND MAIN CHUTES DEPLOYED REEFED BY 10,000 FT MAIN CHUTES FULLY OPENED AFTER BEING REEFED G FORCES, LUNAR MISSION, BLOCK II REF DESIGN REFERENCE MISSION, LED-540-12dtd OCT64

Earth Landing System Parachutes

Hydrogen Fuel Cell Control Schematic

13.7 ft diameter llo ft nominal inflated diameter 7.2 ft diameter 6.0 ft nominal inflated diameter deployed by pilot chutes (reefed for 8 sec) 83.5 ft diameter 77.0 ft nominal inflated diameter + 2 SEC (REEFED FOR 8 SEC (TLM> CHUTES RaEASED AT 10,000 FT (TLM) MAIN CHUTES RELEASED & LM PRESS. PYRO VALVE CLOSED AFTER TOUCHDOWN (TLM) HF ANTENNA DEPLOYED (TLM) TOUCHDOWN VELOCITIES 3 CHUTES - 30.5 FT SEC ELS ARMED TOWER, BPC, AND DOCKING RING JETTISONED (14 SEC) ELS ARMED TOWER, BPC, AND...

TFt

Apollo Command Module Compartments

BATTcRY B rcs purge or1 He dumf i HEIGHT 44 IN. DIAM 22 IN. WEIGHT 245 LB EACH HYDROGEN & HYDROXYL ION PRODUCES WATER & ELECTRONS WATER, HEAT & RECIRCULATING HYDROGEN OUT WATER, HEAT & RECIRCULATING HYDROGEN OUT ELECTRODES DUAL POROSITY NICKEL SINTERS MAXIMUM REACTANT CONSUMPTION-POUNDS PER HOUR WATER GENERATION RATE-POUNDS PER HOUR-PURGING NOT INCLUDED GROSS POWER PER POWERPLANT-KILOWATTS TO BATTERY VENT VALVE ON WASTE MANAGEMENT PANEL (RHEB 252)...

Service Propulsion System

NON-THROTTLEABLE, PRESSURE FEED SYSTEM, HYPERGOLIC PROPELLANTS AND ABLATIVE CHAMBER WITH RADIANT COOLED NOZZLE EXTENSION. ONE SYSTEM CONSISTING OF A PROPELLANT FEED SYSTEM AND ONE ENGINE PROPELLANTS - INHIBITED NITROGEN TETROXIDE AND BLENDED HYDRAZINE 50 UDMH amp 50 HYDRAZINE SYSTEM CONTROLLED BY CMC OR SCS WITH A MANUAL BACK-UP CAPABILITY PROVIDE THRUST FOR MAJOR VELOCITY CHANGES AFTER BOOSTER SEPARATION UNTIL C M S M SEPARATION. IN ADDITION SUPPORTS S M ABORT AFTER THE LAUNCH ESCAPE TOWER HAS...

Structures

APOLLO INTEGRATED STATION amp CSM AXIS LAUNCH ESCAPE MOTOR THRUST ALIGNMENT FITTING POWER SYSTEMS amp INSTRUMENTATION WIRE HARNESS BOOST PROTECTIVE COVER APEX SECTION BOOST PROTECTIVE COVER APEX SECTION HONEYCOMB CORED-LAMINATED FIBERGLASS PANEL HONEYCOMB CORED-LAMINATED FIBERGLASS PANEL COMMAND MODULE ABLATIVE MATERIAL THICKNESS BONDED ALUMINUM HONEYCOMB INSULATION BRAZED STEEL HONEYCOMB SUBSTRUCTURE ABLATIVE MATERIAL BONDED ALUMINUM HONEYCOMB INSULATION BRAZED STEEL HONEYCOMB SUBSTRUCTURE...

Engine Location

Apollo Rcs Quad

PURPOSE PROVIDE POWER FOR ATTITUDE AND OR TRANSLATION CONTROL AFTER BOOSTER SEPARATION UNTIL C M AND S M SEPARATION TYPE OF SYSTEM NON THROTTLEABLE, PRESSURE FEED SYSTEM, HYPERGOLIC PROP- ELLANTS AND RADIANT COOLED THRUST CHAMBERS. SYSTEM DESCRIPTION FOUR INDIVIDUAL SUB-SYSTEMS EACH SUBSYSTEM CONSISTS OF A SEPARATE PROPELLANT FEED SYSTEM AND FOUR THRUST CHAMBERS PROPELLANTS - INHIBITED NITROGEN TETROXIDE AND MONOMETHYL HYDRAZINE SYSTEM CONTROLLED BY CMC OR SCS WITH A MANUAL BACK-UP CAPABILITY...

Pgncs Equipment

Thrust Vector Control Systems

PIPA ELECTRONICS SIGNAL CONDITIONER ASSEMBLY PIPA ELECTRONICS SIGNAL CONDITIONER ASSEMBLY GIMBAL POSITION FUEL PRESSURE INDICATOR GP FPI REACTION JET AND ENGINE ON-OFF CONTROL RJ EC THRUST VECTOR POSITION SERVO AMPLIFIER ttVSA TRAVEL PRIOR TO SWITCH ACTUATION TRAVEL TO HARDSTOP MAXIMUM TORQUE 8.0 MIN 25.0 MAX 1.0 POUND INCHES BREAKOUT SWITCH ACTUATION CONTROLLER LOCK TO ARM DISPLACEMENT 1L 5 0.50 1L0 10 1 1.5 0.5 5 10 HARD STOP, DETENT amp SWITCH CLOSURE FORCE INTO DETENT OUT OF DETENT...