The crew module system.

The crew module is integrated into the FB-111A aircraft encompassing the pressurized cabin and forward portion of the wing glove. Two crew seats with restraints are positioned side by side in the crew module. Freedom of movement and comfort are enhanced by precluding the necessity for a personal parachute and survival equipment, these are provided as a part of the crew module system. During an emergency, the crew module is separated from the aircraft and propelled to a height sufficient for successful recovery throughout the aircraft performance envelope. Upon land or water impact of crew module, landing shock reduction is provided. The crew module system also is provided with self-righting buoyancy, flotation capacity, and occupant environmental hazard protection. An emergency oxygen supply is a portion of the crew module system.

Ejection sequence.

For crew escape and survival, the crew module system is composed of many systems (initiation, severance, separation, stabilization, recovery, landing, flotation, survival, seat and restraint, and emergency oxygen). The systems are interconnected by means of shielded mild detonating cord (SMDC), a stimulus transfer medium. To ensure proper sequencing of functions, SMDC is provided with time delay initiators and one-way explosive transfers. Explosive transfer connectors are incorporated in the systems for firing redundancy. After actuation of the initiation system, automatic sequencing of all systems through landing and flotation is provided.

During an emergency, ejection is initiated by manually actuating either of the ejection handles to fire dual ejection initiators and, in turn, to detonate the SMDC. Due to SMDC detonation, both upper restraint harness are retracted by the inter-lock reel power retraction devices; secondary controls guillotine, blade antenna leads guillotine, and leading edge antenna leads guillotine are activated; and the emergency oxygen system is actuated. Control cables, oxygen line, and antenna leads are severed by the guillotines. Upon propagation through a mechanical explosive interrupt and a 3-second time delay initiator, the chaff dispenser and radio beacon set is actuated.

After 0.350 second, the rocket motor is ignited, if not already actuated, the guillotines, emergency oxygen systems and chaff dispenser are activated by one set of SMDC. By the sane set of SMDC, a flexible linear-shaped charge (FLSC) of the severance system is detonated, thereby cutting the crew module free of the aircraft and the stabilization-brake parachute cover free of the crew module. At the same moment the FLSC cuts the crew module free of the aircraft, the rocket motor propels the crew module upward and away from the aircraft.

By shock wave propagation through SMDC, the stabilization-brake parachute catapult is fired after a 0.15-second delay. At ejection speeds below 300 knots, the dual-mode q-actuated selector prevents propagation to the rocket motor upper nozzle cone diaphragm and activates the barostat lock initiators in 1.0 seconds. At all ejection speeds above 300 knotts, the barostat lock initiator cannot be activated through the dual-mode q-actuated selector. However, propagation is continued to the rocket motor upper nozzle diaphragm through the q-actuated selector and a 0.15 second time delay initiator. After a 1.6-second time delay and after the forward component of acceleration decays to 2.2 G's, the g-sensor initiator is fired to activate the barostat lock initiator. Another explosive train with time delay initiator is provided to ensure that activation time of barostat lock initiator is never more than 4.4 seconds.

Upon activation of the barostat lock initiator, the aneroid bellows are released to begin functioning, and the firing pins are released to bellows control. The firing pins are retained by the bellows until the crew module falls to between 14,000 and 16,000 feet. When the barostat lock initiator firing pins are released, detonation propagation is continued to the recovery parachute cover FLSC and the recovery parachute catapult. The cover and catapult are fired simultaneously, causing the catapult to deploy the recovery parachute.

Following a 3-second delay, detonation propagation is continued to sever the impact attenuation bag severance cover. Concurrently with cover severances, the impact attenuation pressure sources are actuated by puncturing a disk in each sealed pressure bottle by means of explosive valves. The impact attenuation bag is inflated by air from the impact attenuation pressure source through a pressure regulator. After a 7-second delay, the recovery parachute repositioning retractor is activated and the recovery parachute forward and aft bridles are deployed, permitting the crew module to assume landing position. Concurrently with the firing of the repositioning retractor, the emergency UHF antenna actuator is fired and the antenna is extended. Upon landing, shock is attenuated by controlled deflation of the impact attenuation bag. Controlled deflation is accomplished by blowout plugs which shear retainers upon impact, allowing air to escape from the impact bag.

Upon landing in water, the severance and flotation handle is actuated to provide inflation of self-righting and aft flotation bags. However, if the crew module is still attached to a ditched aircraft, the severance and emergency oxygen systems are actuated by the severances and flotation handle. Detonation shock wave from the severance-flotation initiator is propagated through SMDC to FLSC that cuts covers from the crew module. The pressure source is activated to release compressed gas to inflate the aft flotation and left self-righting bags. The crew module is allowed to surface and, if inverted, to begin rolling to the upright position with aid of the left self-righting bags. After a 75-seconds delay, the pressure source is activated to inflate the right self-righting bag, thereby pushing the crew module to the upright position. The recovery parachute release retractors are fired by by actuation of the recovery parachute release handle to disconnect both recovery parachute bridles from attachment to the crew module. The auxiliary flotation bag is deployed by pulling the auxiliary flotation handle on the auxiliary flotation and parachute deploy initiator located on the canopy center beam.