Grumman Aerospace Corporation

Northrop Grumman Systems Corporation

Other

Armand J Aronne

A testing device for testing the continuity of a firing circuit for a squib of an electro-ballistic system which includes a propellant and a plurality of spaced pin-like detonator wires embedded in the propellant. Each of the detonator wires has a first end positioned outside the propellant and a spaced opposite second end embedded in the propellant. Low resistance bridge detonating wires are embedded in the propellant, and electrically connect the second ends of selected ones of the detonator wires. The testing device is embedded in the propellant in spaced relation with the detonator wires and tests the continuity of the firing circuit for the squib. The testing device includes a pair of spaced pin-like test wires embedded in the propellant, with each test wire having a first end outside the propellant and a spaced opposite second end embedded in the propellant. A low-resistance bridge test wire is embedded in the propellant and electrically connects the second ends of the test wires. The continuity of the firing circuit for the squib is tested by passing a low magnitude electrical current through the test wires, the magnitude of which is low compared with the current passed through the detonating wires during ignition of the squib.

Testing device for and method of testing a squib of an electro ballistic

A cylinder is closed to form a sealed container for gases and the like. The cylinder is closed by means of a pair of specially constructed end caps each having annular recesses formed around their circumference. The ends of the cylinders are engaged within the recess and joined by magnetic pulse forming. The magnetic pulse foxing force is asserted radially inward against a mandrel which mates with a depression formed in the caps so that the assembled cylinder and cap are squeezed into sealed relation.

Method and apparatus for sealing a pressure vessel

Start-up electrical power modules are utilized in electroballistic sequencing systems for initiating the ballistic sequence necessary for seat and canopy ejection in military aircraft. The power modules utilize aircraft power to initiate the ballistic sequence necessary for ejection of the pilot or pilots. The power module also comprises two independent internal power supplies as back-up power sources in the event of total aircraft power failure. The power modules are activated by the manual pulling action of an actuation shaft by the pilot or by the automatic pushing action of the actuation shaft by a piston once the pilot initiates the ejection sequence. Once the actuation shaft is pulled into an armed position, dual switches are activated thereby supplying electrical power from the aircraft or from the back-up power sources to a signal conditioner and controller. The signal conditioner and controller processes the signals and outputs a single direct current signal to a ballistic sequencer.

Power source for an electroballistic sequencing system

A strap adjusting device for a harness-adjustment strap having a length, a first end affixed to an aircraft seat-mounted harness and a spaced opposite second end which is free. A wind up device removably affixed to the strap at the second end. The wind up device automatically winds up the strap for a determined length from the second end. The determined length of the strap is thus compacted and restrained from hanging loose. The wind up device includes a housing and a spring in the housing for winding up the strap. A clamp releasably clamps the second end of the strap to the spring.

Strap adjusting device

An ejection seat firing mechanism has a primary cartridge and a firing pin within a housing. A firing head is outside the housing coaxial with the primary cartridge and the firing pin, and a nut affixes the firing head to the firing pin thereby enclosing the housing. A first bore is formed through the flange of the housing and a second bore is formed in the nut spaced from the housing and aligned with the first bore in spaced parallel relation with the axis. A torquing shaft with an internally threaded axial coupling bore formed therein extends a determined distance into the torquing shaft. A spring is coaxially positioned around the torquing shaft and has a top end abutting the nut and a spaced opposite bottom end biasing the torquing shaft toward the flange. A bolt member extends through the first bore and is threadedly coupled with the torquing shaft via the coupling bore. The bolt provides a visual and sensory indication that the primary cartridge is installed and the firing head is torqued.

Indicator for an ejection seat firing mechanism

An ejected pilot's seat deploys a drogue chute shortly upon ejection so as to slow the pilot's seat. A strain gauge is connected in line with a drogue chute to sense the load thereon. The load corresponds to speeds at which the ejected seat travels. As the ejected seat slows, the first possible safe speed for main parachute deployment is detected and a sequence controller causes rotation of a rotary solenoid shaft. The shaft displaces a mechanical stop for a parachute deployment timer. The main parachute is deployed shortly upon actuation of the parachute deployment timer. The result is main parachute deployment as soon as the ejected seat has reached a safe deployment speed, as opposed to after a longer fixed interval of time. This maximizes the altitude of descent for an ejected pilot, thereby increasing his safety factor for descent.

Parachute deployment system as a function of ejected pilot seat speed

An aviator suit is provided with a sewn-on channel of hook and eye material which encloses an elongated line that extends to a floor bracket by a shear fastener. The enclosed line prevents snagging on objects within a cockpit and becomes easily removed when the VELCRO gives way during ejection when forces are exerted upon the enclosed channel line. A simplified snubber plug is releasably clamped to the aviator's seat and becomes released after the aviator has cleared a cockpit.

Pilot ejection leg restraint assembly

An aircraft system battery pack is housed in a housing having a removable cover with a window formed therein. A pair of batteries is positioned in the housing. A lamp is mounted in the window of the cover. A pushbutton switch is mounted in the cover and manually depressible from outside the cover. Electrical conductors electrically connect the batteries in series and provide a DC output voltage and electrical conductors electrically connect the batteries in circuit with the lamp and the switch in a manner whereby manual depression of the switch closes the circuit with the batteries and the lamp. The lamp then indicates the power output condition of the batteries.

Aircraft system battery pack

Threaded shafts engage threaded fittings at the top and bottom of a pilot's ejection seat. A motorized gear train selectively rotates the threaded shafts so as to adjust the fore-aft position of a seat while maintaining it behind a pre-designed emergency ejection path from a cockpit.

Fore and aft articulation adjustment of pilot ejection seat

An assembly for restraining the upper limbs of an occupant of a seat, particularly an aircraft ejector seat, includes a storage unit which is adapted to be fixedly secured to an upper back portion of the seat. The storage houses a pair of movable cover members and first and second bladder units. The cover members and bladder units are connected by means of straps to a quick release mechanism which mates with a corresponding fitting carried by the occupant and then to a fixed structure adjacent the seat. When it is desired to deploy the restraint assembly, a tension is applied to the straps which causes the cover members to extend around opposite sides and laterally inward of the occupant's body, about respective arms of the occupant, and the bladder units to extend about the occupant's neck. The bladder units are then inflated so as to permit undesirable movement of the occupant's head.

Occupant arm and head restraining assembly

A pilot's ejection seat is propelled in an upward direction after ejection by employing a high gain signal from a radio altimeter on board an aircraft. The vertically downward high gain vector is inverted by adding 180.degree. to its phase component and providing the resultant signal to an inexpensive gyro or assembly of gyros installed in the seat. The gyros are constantly updated with information concerning the upward vertical direction and upon ejection, the gyros maintain this information for a sufficient period of time to control the ejection seat propulsion system in a manner achieving a vertically upward trajectory that will enable the pilot to clear a disabled aircraft and achieve the orientation necessary to deploy a parachute.

Ejection seat control using aircraft radio altimeter

An aviator harness fitting includes a releasable member secured to a buckle member by means of a movable bolt. A pressure inlet is provided to enable translational motion of the bolt in the manner of a piston. When actuated, the bolt moves to a release position to permit separation of the releasable and buckle members.

Fitting release utilizing bolt action

An ejected pilot's seat is provided with a drogue chute anchored to the seat by means of a bridle. The bridle includes a strap having redundant load cells parallel connected in redundant fashion. The load cells measure tension in the strap. Data from the load cell is conducted through the bridle to a microprocessor contained within the seat. The microprocessor includes look-up tables for correlating tensile load in the strap to forward velocity of the ejected pilot. Upon acquisition of a preselected optimum velocity, the drogue chute is released and a main chute is deployed to increase the likelihood of a safe descent to the ground.

Drogue chute speed mode selector

The harness of a pilot may be custom fitted in the field by temporarily fitting front and back vest panels. The vest includes strips pre-sewn thereon which serve as passageways for harness straps. The straps are tightened and temporarily secured to the vest so as to closely conform to the torso of the pilot. The vest is then removed so that the front and back panels may be sewn together as well as the temporarily secured straps. The result is a harness/vest combination which will conform securely to the torso of a pilot.

Custom-fitted harness for an aviator

A multi-purpose protective garment is provided for aviators and astronauts. The garment includes inflatable pads which selectively exert pressure on the chest and abdominal areas of the wearer to counteract the effects of high altitude and high G forces which have detrimental effects upon an aviator. The garment includes an integral harness for easily attaching a hollowed backpack frame which not only contains a stored parachute but serves as an oxygen bottle for inflation of the pads as well as providing an emergency oxygen supply for the wearer.

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Massapequa, NY, United States of America

Armand J Aronne