Event Profile

DIRECT S C ULLAGE ON (TLM) +2.5 (PITCH & YAW STAB. INHIBITED) (ROLL STAB.ONLY WITH ULLAGE) 8. TERMINATE ULLAGE AFTER SPS IGNITION 19. APEX COVER JETTISONED (TLM) adapter is separated, an .8 second time delay is triggered which, when timed out, will enable the SM's RCS SCS for roll stabilization only. Stabilization in pitch and yaw is inhibited as long as the ullage maneuver is on. At this writing it is felt that the crew will have made their choice of a steering program and that the SPS...

Launch Escape System

Apollo Boost Protective Cover

LAUNCH ESCAPE MOTOR THRUST ALIGNMENT FITTING LAUNCH ESCAPE MOTOR THRUST ALIGNMENT FITTING POWER SYSTEMS amp INSTRUMENTATION WIRE HARNESS BOOST PROTECTIVE COVER APEX SECTION POWER SYSTEMS amp INSTRUMENTATION WIRE HARNESS BOOST PROTECTIVE COVER APEX SECTION ABORT BECO EVENT TIMER RESET C M-S M UMB DEADFACED C M RCS PRESS. TLM RCS CONTROL TRANS MAIN DC BUS TIED TO BATS C M-S M SEP TLM C M RCS SCS ENABLED TLM C M-S M SEP PYRO CUTOFF CANARDS DEPLOYED TLM BARO. SW LOCK-IN C M RCS SCS DISABLED TOWER...

Earth Landing System

APEX COVER JETTISONED BY 24,000 FT .4 SEC 2. DROGUE CHUTES DEPLOYED BY 24,000 FT 2 SEC REEFED FOR 8 SEC 3. DROGUE CHUTES DISREEFED PILOT CHUTES DEPLOYED amp DROGUE CHUTES RELEASED BY 10,000 FT 5. MAIN CHUTES DEPLOYED BY 10,000 FT REEFED FOR 8 SEC 6. MAIN CHUTES DISREEFED, RECOVERY ANTENNA, amp BEACON DEPLOYED 7. MAIN CHUTES RELEASED AFTER TOUCHDOWN TOUCHDOWN VELOCITIES 3 CHUTES - 28 FT SEC 2 CHUTES - 33.5 FT SEC release of the Drogue parachutes and the deployment of the Pilot parachutes as...

Tower Separation Mechanism

Rockets With Parachutes And Detonators

The Tension Tie Plate is common to a bolt which screws up into the CM structure and another bolt which screws down into the CM support structure on top of the SM as shown in figure 4-10. After the CM has been bolted down to the SM under tension, an FLSC Cutter Assembly is installed on each of the 3 Tension Tie Plates in the manner shown in figure 4-11. Note the face-to-face mounting of the FLSC onto the Tension Tie Plate and a Detonator provided for each. When CM - SM Separation is...

Actuator

Apollo Saturn Launch Control

The Sequential Events Control System is directly concerned with certain Displays and Controls on separate panel assemblies located on the Main, Left Hand, and Right Hand Displays and Controls Consoles. Each of these Displays and Controls and their functions will be described in the following text. Figure 5-1 is the complete Displays and Controls layout presently approved for the first manned flight of Apollo. Figure 5-2 is a panel assembly locator designed to aid the student in locating those...

Earth Impact System

Secondary Keyway

Many operations in the SECS are initiated or accomplished by pyrotechnic devices of various types. This section describes these pyrotechnic devices both functionally and physically and indicates where they are used throughout the SC. 4.1 ELECTRICAL HOTWIRE INITIATOR Figure 4-1 shows the Apollo Standard Initiator ASI . This Initiator, because of its simple circuitry, is used throughout the Apollo SC to ignite all pyrotechnic devices. The Initiator acts as the primer, in most all applications,...

Grain Configuration

Cored Laminated

The Launch Escape motor has 4 nozzles positioned 90 apart. Each nozzle is canted 35 from the X axis. The Z nozzle has an inside diameter of 5.6 inches as compared to the -Z nozzle's 4.S inches. The Y and -Y nozzles are identical, each having an inside diameter of 5.2 inches. This nozzle size variance causes an off-set thrust vector of approximately 2,75 . The Pitch Control motor is ignited simultaneously with the Launch Escape motor upon the initiation of any LES abort either from the launch...

Reefing Une Cutter Installation

Suspension Lines

TIME DELAY COMPOUND MIL-C-13739 3-4 PRESSINGS VERTICAL TAPE SKIRT REINFORCEMENT ATTACHMENT LOOP GORE FROM SKIRT TO VENT-BETWEEN SUSPENSION LINES are filled with air and the Pilot parachutes and the Main Landing parachute bags collapse onto the canopies of their respective Main Landing parachute, no longer needed. The Main Landing Parachutes are the ring sail type, as illustrated in figure 3-H, with the diameter of the canopies being 83.5 feet. Excess nylon in the lower portion of each panel...

Canard Thrust Linkage Assemblies

Apollo Rcs Engines

CANARD THRUSTER IN RETRACTED POSITION CANARD THRUSTER IN RETRACTED POSITION Figure 3-1 lists the components of the ELS. These components are the Apex Cover Separation Mechanism and the Parachute Subsystem consisting of 2 Drogue parachutes, 3 Pilot parachutes, 3 Main Landing parachutes, 2 Drogue parachute mortars, 3 Pilot parachute mortars, and are described in the text following. 3.1 APEX COVER SEPARATION MECHANISM One of the requirements of the LE5 was to provide acceptable conditions for Apex...

Umbilical Separation System

Apollo Lem Control Panel

UMBILICAL SEPARATION lt LEM TO ADAPTER UMBILICAL SEPARATION lt LEM TO ADAPTER ELECTRICALLY INITIATED HOTWIRE CARTRIDGE GAS ASSEMBLY ME453-0005 generates gas pressures, according to the number of pellets in the assembly, to actuate the Apex Cover Thruster Assemblies shown in figure 4-18, the Parachute Deployment Mortars shown in figure 4-19 and the Canard Actuator shown in figure 4-20. Note that in all applications 2 Pressure Cartridges are used for redundancy.

Earth Landing System Parachutes

Drogue Chute

13.7 FT DIAMETER 11.0 FT NOMINAL INFLATED DIAMETER 7.2 FT DIAMETER 6.0 FT NOMINAL INFLATED DIAMETER DEPLOYED BY PILOT CHUTES REEFED FOR 8 SEC expel the parachute by actuating a Sabot piston which forces the parachute to shear the pins that hold the mortar cover in place. Refer to figure 3-6 for an exploded view of the mortar assembly. These parachutes are deployed and maintained in a reefed condition for 8 seconds when they are allowed to open fully. Reefed means to take in or reduce in size....