Abstract: The invention relates to means for the emergency abandonment of an aircraft and makes it possible to create a super-light and effective system for emergency abandonment which can be used in aircraft with a flight speed of 500-600 km/hour. This is achieved by at first catapulting a parachute pack (7) by means of an ejection mechanism (6) and then catapulting a member of the crew using an ejection mechanism (2). In order to ensure safety in the case of pair catapulting, the direction of catapulting of the parachute pack and the member of the crew is at an angle of 15-20.degree. relative to the plane of symmetry of the aircraft. Furthermore, the parachute pack is used as a means for breaking the transparency of the cockpit.

Abstract: A first rack is maintained in spatial relationship from a pinion so that the rack may be moved vertically with a pilot's seat, thereby accommodating height adjustments. An actuating handle is connected, via a cable, to a linkage which displaces the rack toward engagement with a pinion gear. A second rack is normally maintained in engagement with the same pinion gear and is driven by it. When the pinion gear is driven by the first rack, the second rack follows and it pulls upon a cable connected at an opposite end to a seat firing head.

Abstract: 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.

Abstract: A helmet mounted night vision device for a pilot that is automatically propelled away from the pilot before the pilot ejects from an aircraft, thereby preventing injury to the pilot caused by the night vision device striking the ejecting pilot. In a preferred embodiment, the present invention night vision device is a binocular device, having a right optical assembly and a left optical assembly that are viewed by the right and left eyes of the pilot, respectively. The right and left optical assemblies are each attached to elongated arm members. Each of the arm members, supporting the optical assemblies, are pivotably coupled to a common mounting plate that is removably attachable to the helmet of the pilot. Prior to ejection, the left and right optical assemblies are joined in front of the eyes of the pilot, thereby forming the binocular device.

Abstract: 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.

Abstract: 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.

Abstract: An electronic sequencer for an aircraft ejection seat comprising a plurality of sensors for air-speed, temperature, air pressure and acceleration. These sensors provide, via interface circuitry, signals in digital electronic form to a microprocessor which, when appropriate, initiates various functions of the ejection seat, such as the deployment of drogue and main parachutes and release of seat harness. The sensors and main components of the microprocessor are provided in triplicate and the microprocessor uses a polling procedure to obtain a high level of reliability of operation.

Abstract: A goggles emergency release apparatus is disclosed wherein an actuator, ptioned adjacent the goggles latching mechanism, drives a wedge into the mechanism to push a release pin into the open position and push the goggles away from the helmet. The actuator receives its initiation power when the ejection seat movement closes a microswitch.

Abstract: 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.

Abstract: An electro ballistic escape sequencing system is actuated only by the seat initiators. Current entering the system by any other means will see only open circuits. A pressure sensitive switch is provided in each circuit subject to outside interference and is normally in the open position. When ejection is required, pressure from one of the seat initiators activates the thermal battery and closes all circuits required for ejection.

Abstract: An escape device such as an ejection seat system (10) has a propulsion system (42) that accelerates and changes the angular orientation of the device. The system (10) includes sensors (54) for determining certain parameters associated with device altitude, attitude, and sink rate. A microprocessor (36), operatively connected to both the sensors (54) and the propulsion system (42), operates the propulsion system so that the device will move at desired acceleration levels and turn to a desired attitude.

Abstract: A self contained, self powered microprocessor controlled aircraft ejection seat escape parachute deployment sequencer which can handle problems caused by high altitudes into the stratosphere and by high speeds above Mach 1, and which will deploy the parachute, based on seat mounted pitot tube and ambient pressure readings plus stored data, when speed and altitude are at human physiologically acceptable levels. Many failsafes to cope with unusual conditions, and additional features are also included.

Abstract: A system and method for stabilizing an aircraft ejection seat and crew member after seat ejection and prior to main parachute inflation. The system also providing for delayed opening of the main chute until air speed and altitude have decreased to an acceptable parachute inflation range.

Abstract: A crewmember (12) is positioned within an ejection seat or other escape device (10). The escape device (10) is ejected from the aircraft or other flying vehicle when it is desired to effect an escape. At the start of ejection, the altitude, sink rate and roll angle of the escape device (10) are determined, by appropriate sensors (128, 132). A microprocessor (66) is used for dividing the altitude by the sink rate to obtain a first time value. The microprocessor (66) is used to divide the roll angle by a desired rate of roll angle correction, to obtain a second time value. The second time value is subtracted from the first time value to obtain a third time value, t.sub.c. In response to t.sub.c being larger than a predetermined value, the microprocessor (66) controls separation to subject the crewmember (12) to a relatively low injury risk level. In response to t.sub.

Abstract: A catapult seat ejection system for ejecting a pilot and seat from an aircraft is disclosed in which the thrust of the catapult is controlled to prevent injury to the pilot due to acceleration forces. The catapult comprises a main catapult tube; a piston within the tube driven by gas pressure from the burning of two solid propellants cartridges; and four shuttle vent valves powered by gas from a plurality of electrically ignited squibs controlled by an electronic control system. The catapult is initially driven by only one of the two solid propellant cartridges and the electronic controller continuously monitors acceleration. If acceleration is too great the controller fires squibs with a control signal to open the shuttle vent valves to vent the gasses from the catapult and thereby reduce the pressure and acceleration of the seat. If the acceleration is too low and the vent valves are closed, and the sensor fires the second cartridge with a second control signal.

Abstract: A programmable crewmember emergency ejection system is disclosed which will eject the crewmember expeditiously from a disabled aircraft, while at the same time assuring that the crewmember will not be subjected to forces that are beyond crewmember tolerance. This is accomplished by a control system involving sensors having signals that are processed and used to vary ejection thrust and acceleration onset rate. The system involves a two phase ejection: A catapult phase followed by a rocket phase, both phases cooperating to provide a substantially constant maximum thrust that is well within human tolerances such that a second jolt to the crewmember is substantially minimized.

Abstract: A dual redundant pitot-static sensing system for use in a system for deplng a parachute during ejection of an occupant from a disabled aircraft includes a pair of pressure-sensitive check valves to store peak dynamic airstream pressure for obviating difficulties experienced when the pitots are blocked by airborne debris.

Abstract: A capsule and rocket extraction system for providing an inflight escape system for the pilot of a damaged aircraft. The system comprises a capsule that is separable from the main fuselage of the aircraft and a rocket for extracting the pilot from the capsule. A control system is carried by the capsule for sensing the capsule's speed, altitude and attitude, and for actuating only the rocket to extract the pilot directly from the capsule when the speed, altitude and attitude are at predetermined conditions, and for sequentially actuating a capsule separation device to separate the capsule from the main fuselage and then actuating the rocket to extract the pilot from the separated capsule when the speed, altitude and attitude are at different predetermined conditions.

Abstract: An electronic system for selecting the proper mode sequence for deploying a ecovery parachute from an aircraft ejection seat. The system senses altitude, airspeed, and sink rate; and compares these to predetermined reference signals. The system also incorporates logic circuits and time delay circuits. The logic circuits are arranged to select one of four time delays depending on the status of the various parameters relative to the reference signals.

Abstract: An aircraft ejection seat system which incorporates means for permitting deployment of a main parachute at the end of a delay after ejection and a mode selector mechanism operable to permit such deployment at a shorter predetermined time after ejection if ejection takes place at low speed and low altitude. The mode selector mechanism incorporates a piston slidable along a bore to operate a firing pin to fire a cartridge and thus initiate the earlier deployment of the parachute. Means for sensing barometric pressure, air speed, and deceleration are arranged, if the sensed value indicates the longer delay period is required, to project respective plungers transversely into the bore to prevent the piston from striking the firing pin. A further plunger remains projected into the bore unless auxiliary sensing means positively senses low speed and altitude.

Abstract: A parachute deployment sequencer includes two sequencer systems in electromagnetic shielding housings. Each housing contains two bellows connected to pitot tubes, a third bellows for measuring ambient pressure and three switch contact sets connected in series, each contact set being operated by one of the bellows. Each housing also contains a battery actuated by seat ejection and a deployment firing circuit with a series switch circuit in between. After ejection, deployment is initiated when all three switches are closed.

Abstract: An aircraft ejection seat position and restraint system for protecting an rcrewman against back injuries during emergency escape. The ejection sequence is initiated by the aircrewman pulling a lower ejection handle or a face curtain handle with both hands to release or shatter the cockpit canopy. A torso harness suit is concommittantly tightened with inflation of a vest worn between the aircrewman and the suit, and catapult rockets are fired to propel the seat out of the cockpit. The harness suit draws the aircrewman's upper torso against the back of the seat while the inflated vest pushes his hips back and down into the seat pan for optimally positioning his spine before ejection thereby negating the effects of an aircrewman purposely or inadvertently flying with a loose harness. After ejection, the seat is separated from the aircrewman but the vest remains inflated inside the harness providing cushioning against the opening shock force of the parachute which is attached to the harness suit.

Abstract: A line cutter or discharge valve responsive to aircraft attitude is posited on an aircraft ejection seat to interrupt the gas initiated sustainer rocket system. During inverted ejections, the cutter or valve will either sever or discharge pressure from a tube which leads from the firing squib to the sustainer rocket. Preventing sustainer rocket ignition enhances inverted ejection survivability by reducing crew member velocity toward the ground, thereby lengthening the time available for parachute deployment.

Abstract: A collision avoidance system having a seat parachute deployment system secured to the pilot's seat. The seat parachute deployment system has a flap member secured to the survival kit on the side remote from the pilot. The flap member drops down to prevent entanglement of the seat parachute or suspension lines with the pilot's legs. The seat parachute is stowed in an elongated sleeve on the flap and is drawn from the sleeve during seat separation. The suspension lines are stowed in a conventional manner. A connecting line, connected between the suspension lines and seat attachment lines, is stowed in elongated sleeves on the flap.

Abstract: A latch for use on an aircraft ejection seat and the like to permit the optional selection, prior to ejection, as to retention of a survival kit. The latch includes a housing for receiving a bolt which is retained in position by a detent spring, and a two-position toggle having a lever extending therefrom and maintained in position by a toggle detent. In one position, the toggle retains the bolt fixed in the housing and a lanyard passing through a hole in the bolt has one end attached to the survival kit and the other end to the ejection seat through a cord cutter. In this position the cutter is activated and the survival kit separates from the seat structure. With the toggle in the other position, the bolt slips out of the detent spring upon ejection and the lanyard with the bolt attached secures the survival kit to the ejection seat.

Abstract: An ejection sequencing system used particularly in an ejection seat operation includes continuous sensing of both airspeed and altitude. The continuous airspeed sensing is accomplished by continuously measuring the airstream temperature and then determining the optimum instant for parachute deployment from the measured temperature, thus making the deployment event temperature-responsive. When the sensed airspeed is within a predetermined acceptable limits, a first signal is generated. Continuous altitude sensing is accomplished by an aneroid barometer and when the sensed altitude is within predetermined acceptable limits, a second signal is generated. When these first and second signals are transmitted to the parachute container, they initiate parachute deployment. Redundant, failsafe system operation can be provided through the use of two or more interconnected airspeed sensing devices having fixed time delays for backup.