Abstract: In a method and apparatus for controlling the deployment of a towline connecting a mooring craft to an ejected object comprising the steps of monitoring velocity to determine when a point for optimum braking has been achieved and then engaging a brake system to retard deployment of the towline, a DC motor augments and controls the brake system. The DC motor further controls the retrieval of the object. A cutter mechanism uses a first blade to grip the towing cable to maintain tension thereon as a second blade cuts the cable. A spring biased boom in combination with spring biased fins on the ejected object rapidly deploys the object from its storage housing. A locking mechanism secures the deployment mechanism in a stable locked position upon the object reaching its fully extended position.

Abstract: A fall protection lanyard apparatus for use in transferring loads in an elevated environment. The fall protection lanyard apparatus includes first and second load-bearing lanyards, each terminating in a connectable free end. Each lanyard is preferably attached to a common point, such as a load bearing steel O-ring, which in turn is attached to a safety harness which secures the load. The first lanyard incorporates a quick-release mechanism, which, upon activation, results in the separation of the hook and free end portion thereof. The second lanyard incorporates a mechanism for activating the quick-release upon application of a predetermined force thereon.

Abstract: A system for launching, refuelling and recovering in flight an aircraft (10) such as an unmanned aerial vehicle (UAV) from a larger carrier aircraft (16) comprising a holder (22) on the carrier aircraft (16) to which the UAV (10) is detachably connectable and an extendable and retractable refuelling device (23, 24) on the carrier aircraft (16) detachably connectable to the UAV (10) whereby to launch the UAV it is disconnected from the holder (22), the refuelling device (23, 24) is extended with the UAV connected thereto to cause the UAV to trail behind the carrier aircraft and the UAV is then disconnected from the refuelling device.

Abstract: The two-payload decoy device has a square outer case, containing a manifold/delay body assembly, a round payload assembly, and a square payload assembly. The square outer case is closed with an end cap. The manifold/delay body assembly is attached to the round payload assembly, which rests against the square payload assembly. Firing a standard impulse cartridge ignites a booster pellet and delay element in the manifold/delay body assembly. Gases flow through openings in the manifold/delay body assembly and down the corner cavities between the round payload assembly and the square case, pushing the square piston against the square payload, which separates the end cap from the case and ejects the square payload. The delay element burns for a specific time, and then ignites a round payload expulsion charge, which creates gases that push the round piston against the round payload, which dislodges a retaining ring, and ejects the round payload.

Abstract: A hanger assembly for suspending an external store from an aircraft includes left and right side panels in hinged connection to a center panel, where the panels, in combination, form a band for substantially circumferentially surrounding the external store. The center panel includes an interface for engagement with an attachment pod on an aircraft, and the side panels are fastened in tension to each other diametrically opposite the interface. The length, thickness and material strength of the band are selected to minimize the bending moment, which is induced in the hanger assembly based on loading experienced during operational use, at a region of the band at which an interface is established with the aircraft.

Abstract: There is provided a store ejection system and method for mounting and ejecting a jettisonable store. The system uses a pressurized non-pyrotechnic fluid from a fluid source as the source of energy and the transfer mechanism. An actuation system includes an accumulator for receiving and storing the fluid from the pressure source, a poppet valve for controlling a flow of the fluid from the accumulator, and a controller for actuating the poppet valve to an open position in response to a control signal to jettison the store. A pneumatically-driven jettison mechanism for releasably retaining the store is fluidly connected to the poppet valve such that actuating the poppet valve to the open position releases the pressurized fluid in the accumulator to flow to the jettison mechanism, thereby actuating the jettison mechanism to jettison the store.

Abstract: A stores ejection system for retaining stores on the underside of an aircraft and forcibly jettisoning the stores away from the aircraft is disclosed. The ejection system includes a plurality of ejector mechanisms for releasably holding and jettisoning the stores away from the aircraft, a plurality of storage devices for storing pressurized gas to actuate the ejector mechanisms, and a central control system for maintaining the pressure of the gas, and actuating the release of the gas. The central control system monitors the pressure of the storage devices and heats only those storage devices that have a pressure below the operating pressure.

Abstract: There is provided a store ejection system and method that use a pressurized non-pyrotechnic gas as the source of energy and transfer mechanism for jettisoning a store from an aircraft. The ejection system includes an on-board pressure vessel for holding the pressurized gas, a releasable seal configured to hermetically seal the pressure vessel, and a pressure regulator fluidly connected to the releasable seal and configured to control a flow of the gas from the pressure vessel when the releasable seal is configured in an open position. The pressure vessel is releasably connected to the pressure regulator and the releasable seal is configured to be released after the pressure vessel is connected to the pressure regulator so that the releasable seal hermetically seals the pressure vessel before the pressure vessel is connected to the pressure regulator. The ejection system also includes at least one actuation system and at least one pneumatically-driven jettison mechanism for releasably retaining the store.

Abstract: A method of ejecting or jettisoning stores from an aircraft is disclosed that pertains essentially to the over-pressurizing of an on-board gas storage system such that the pressure of the gas stored therein remains at or above the proper pneumatic actuation pressure during all foreseeable temperature ranges. When a control signal to release a store is provided, the pressure of the gas is reduced to be within the desired pneumatic actuation pressure and the gas is then used to release the store. The present invention eliminates many of the concerns associated with prior art ejection systems by providing a method of supplying proper pneumatic actuating pressures during store release without the need for on-board compressors or heating elements.

Abstract: There is provided a store ejection system and method that use a pressurized non-pyrotechnic gas as the source of energy and transfer mechanism for jettisoning a store from an aircraft. The ejection system includes an on-board pressure vessel for holding the pressurized gas, a releasable seal configured to hermetically seal the pressure vessel, and a pressure regulator fluidly connected to the releasable seal and configured to control a flow of the gas from the pressure vessel when the releasable seal is configured in an open position. The pressure vessel is releasably connected to the pressure regulator and the releasable seal is configured to be released after the pressure vessel is connected to the pressure regulator so that the releasable seal hermetically seals the pressure vessel before the pressure vessel is connected to the pressure regulator. The ejection system also includes at least one actuation system and at least one pneumatically-driven jettison mechanism for releasably retaining the store.

Abstract: Safety apparatus (352, 356, 358, 350) for a cargo platform (310) for releasable securement in an aircraft fitted with an complementary type securement system having one ore more retractable catches (22) for engaging the cargo platform, wherein the safety apparatus comprising means to ensure the or each catch (22) of the securement system is moved from a deployed to a retracted position prior to extraction of the platform the aircraft.

Abstract: The invention is a sensor pod for mounting on the top surface of the fuselage of an aircraft. The pod it supported by right and left front supports and right and left rear supports that attach to the fuselage on either side of the longitudinal axis of the aircraft. A fifth structural support, aligned with the longitudinal axis of the aircraft, has a first end attached to the fuselage of the aircraft a second end attached to the sensor pod the aircraft.

Abstract: A stores ejection system for retaining stores on the underside of an aircraft and forcibly jettisoning the stores away from the aircraft is disclosed. The ejection system includes a plurality of ejector mechanisms for releasably holding and jettisoning the stores away from the aircraft, a plurality of storage devices for storing pressurized gas to actuate the ejector mechanisms, and a central control system for maintaining the pressure of the gas, and actuating the release of the gas. The central control system monitors the pressure of the storage devices and heats only those storage devices that have a pressure below the operatingpressure.

Abstract: A system for launching, refuelling and recovering in flight an aircraft (10) such as an unmanned aerial vehicle (UAV) from a larger carrier aircraft (16) comprising a holder (22) on the carrier aircraft (16) to which the UAV (10) is detachably connectable and an extendable and retractable refuelling device (23, 24) on the carrier aircraft (16) detachably connectable to the UAV (10) whereby to launch the UAV it is disconnected from the holder (22), the refuelling device (23, 24) is extended with the UAV connected thereto to cause the UAV to trail behind the carrier aircraft and the UAV is then disconnected from the refuelling device.

Abstract: An embodiment of the present invention provides a loading system for loading a stores item onto a release unit attachable to an aircraft structure, the release unit having a release actuation assembly including an actuator arm. The loading system comprises at least one hook pivotably mountable to the release actuation assembly. The hook has a pivot pin passage formed therethrough, a stores engagement portion and an actuation portion. The stores engagement portion is configured for engaging a lifting structure of the stores item. The actuation portion is configured for engagement by the actuator arm of the release actuation assembly to pivot the at least one hook and disengage the stores engagement portion from the lifting structure of the stores item. The loading system further comprises a pivot pin configured for insertion into the pivot pin passage. The pivot pin is removably mountable to the release actuation assembly for pivotably mounting the at least one hook thereto.

Abstract: A fall protection lanyard apparatus incorporating an automatic emergency release is disclosed. Competing concerns of fall protection (for the load) and on-demand emergency release (for the aerial lift) are each enabled by providing the first lanyard with a quick release mechanism and the second lanyard with a release triggering mechanism. The lanyard apparatus is adapted for attachment to a human or non-human load. The first lanyard incorporates a quick-release mechanism, which, upon activation, results in the separation of the connectable end portion thereof. The second lanyard incorporates a mechanism for activating the quick-release upon application of a predetermined force thereon. The lanyard apparatus provides total fall protection during the transfer of a load to a structure in any elevated environment while providing an on-demand quick-release in emergency situations.

Abstract: A munition rack comprises a center strongback with an aircraft attachment hookup structure thereon, a first munition deployment structure, including a first munition deployer, affixed to a first outboard end of the center strongback, and a second munition deployment structure, including a second munition deployer, affixed to a second outboard end of the center strongback. The center strongback, the first munition deployment structure, and the second munition deployment structure are preferably dimensioned such that the distance between a first munition deployer transverse midpoint and a second munition deployer transverse midpoint is at least about 19 inches. There is at least one additional munition deployment structure selectively affixed to the bottom of the center strongback at an inboard location intermediate between the first outboard end and the second outboard end.

Abstract: There is provided a store ejection system and method that use a pressurized non-pyrotechnic gas as the source of energy and transfer mechanism for jettisoning a store from an aircraft. The ejection system includes an on-board pressure vessel for holding the pressurized gas, a releasable seal configured to hermetically seal the pressure vessel, and a pressure regulator fluidly connected to the releasable seal and configured to control a flow of the gas from the pressure vessel when the releasable seal is configured in an open position. The pressure vessel is releasably connected to the pressure regulator and the releasable seal is configured to be released after the pressure vessel is connected to the pressure regulator so that the releasable seal hermetically seals the pressure vessel before the pressure vessel is connected to the pressure regulator. The ejection system also includes at least one actuation system and at least one pneumatically-driven jettison mechanism for releasably retaining the store.

Abstract: There is provided a store ejection system and method that use a pressurized non-pyrotechnic gas as the source of energy and transfer mechanism for jettisoning a store from an aircraft. The ejection system includes an on-board pressure vessel for holding the pressurized gas, a releasable seal configured to hermetically seal the pressure vessel, and a pressure regulator fluidly connected to the releasable seal and configured to control a flow of the gas from the pressure vessel when the releasable seal is configured in an open position. The pressure vessel is releasably connected to the pressure regulator and the releasable seal is configured to be released after the pressure vessel is connected to the pressure regulator so that the releasable seal hermetically seals the pressure vessel before the pressure vessel is connected to the pressure regulator. The ejection system also includes at least one actuation system and at least one pneumatically-driven jettison mechanism for releasably retaining the store.

Abstract: The passive dynamically disconnecting arm features an arm having two ends wherein attached to the first end is a housing having both a plunger and an electrical connector providing positive engagement force during shock or vibration. The second end of the arm features a trunnion and torsion spring. The arm features a slot wherein a rod is placed inside operatively coupled to both the plunger and trunnion. When an object is attached to the electrical connector, the spring-loaded plunger compresses preventing the rod from moving and causing the second end of the rod to couple with a divot within the trunnion. When the object moves a predetermined distance, the spring-loaded plunger decouples from the rod and the electrical connector detaches from the object. The arm, by means of a torsion spring attached to the arm's second end, translates and rotates out of the object's path without striking the object.

Abstract: A method of ejecting or jettisoning stores from an aircraft is disclosed that pertains essentially a method of supplying the gas storage system with compressed gas that has a pressure-to-temperature ratio that ensures proper jettisoning of stores under all design temperature specifications, without the need for on-board compressors, heating elements, or venting systems. The invention can be practiced by simply making a temperature measurement, during or before the step of supplying the gas storage system with compressed gas, and determining therefrom the necessary pressure of compressed gas to initially supply to the gas storage system. By so doing, the performance of the ejection system at various temperatures is automatically controlled, regardless of the temperature of the compressed gas immediately after such gas is supplied to the gas storage system.

Abstract: There is provided an aircraft which can minimize its radar signature emission. Such aircraft comprises a fuselage having a lower fuselage portion. An internal fuselage cavity is defined within the lower fuselage portion and contains all landing gears and bombs therein. Moreover, a cavity-enclosing door is engaged to the lower fuselage portion. This specific cavity-enclosing door may form a closed position relative to the internal fuselage cavity to enclose all of the landing gears and bombs therein. In this respect, enclosure of all of the landing gears and bombs solely through the cavity-enclosing door may minimize the radar signature emission from the fuselage.

Abstract: There is provided a store ejection system, store, and method for mounting a jettisonable store on an aircraft. The system uses a pressurized non-pyrotechnic fluid from a pressure vessel integral to the store and sealed by a releasable seal as the source of energy and the transfer mechanism. An actuation system includes an accumulator for receiving and storing the fluid from the pressure vessel, a dump valve for controlling a flow of the fluid from the accumulator, and a controller for actuating the dump valve to an open position in response to a control signal to jettison the store. The seal is configured to hermetically seal the pressure vessel before the actuation system is connected to the pressure vessel, and the actuation system is configured to be fluidly connected to the pressure vessel upon release of the releasable seal.

Abstract: The invention entails apparatus for mounting a payload, such as a warhead, to bulkheads carried by munitions. The apparatus comprises fore and aft bulkheads depending from the munitions, each of the bulkheads having a substantially centrally located opening; bulkhead attaching structure carried by the payload and engaging at least one of the bulkheads, and at least one fastener carried by the bulkhead attaching structure and engaging both the payload and the bulkhead attaching structure. In one embodiment, the bulkhead attaching structure is an annular ring element disposed about and secured to the aft end of said payload. The ring element includes a first annular portion of a first diameter, and a second aft portion of a second diameter, the first diameter of said first portion being smaller than the second diameter to accommodate annular portions of the aft bulkhead. In a second embodiment, the bulkhead attaching structure comprises a step element carried by the payload, which abuts the fore bulkhead.

Abstract: A fall protection lanyard apparatus for use in transferring loads in an elevated environment is disclosed. The fall protection lanyard may be connected to a load and used to safely transfer a human or nonhuman load in an elevated environment, such as from an airborne rotorcraft to an adjacent structure while providing fall protection for the load and emergency release capabilities for the aircraft. The lanyard apparatus provides total fall protection for the load throughout the transfer process without restricting or otherwise limiting available emergency flight options/maneuvers by incorporating an emergency release that automatically activates on demand. In a preferred embodiment, the fall protection lanyard apparatus includes first and second load-bearing lanyards, each terminating in a free end incorporating a connectable hook.

Abstract: An airborne store suspension and release arrangement includes two slender “Tee” hangers located one on either side of a vertical plane through the center of the store. Each hanger has a narrow strut portion mounted on the store by one end and an enlarged cross section portion at the other end of the narrow strut portion. The enlarged cross section portion of each hanger is clamped by releasable clamps mounted in a store carrying aircraft. The store and the aircraft are formed with surfaces which abut one another when the store is suspended from the aircraft and the enlarged cross section portions of the hangers are clamped by the clamps. The arrangement of the hangers, the clamps and the abutting surfaces establishes a couple in reaction to a rolling moment to which the store is subjected during maneuvering of the aircraft. Only one such a slender ‘Tee’ hanger is aligned with the geometrical center of the store in an alternative embodiment.

Abstract: Apparatus for separating aerodynamic objects from an aerodynamic vehicle includes a first element, aerodynamically configured to create nose-down pitching moment, mounted to the object surface, a second element mounted to the first element and projecting into an oncoming airstream such that when enabled, the passing air tears the apparatus from the surface which otherwise supports it. The first element is a body designed to be conformal with the object surface to which it is mounted, and includes a forward end projecting into the oncoming airstream and a rearward end, and is secured to said object surface at the rearward end thereof. A flexible gasket is interposed between the first element and the object surface. The second element comprises a forward end directed toward the oncoming airstream and a rearward end, with the second element being mounted to the first element at the rearward end of the second element.

Abstract: Improvements in rotorcraft external load operations are disclosed, including a method for transferring a load from an airborne rotorcraft to a structure while providing fall protection for the load and emergency release capabilities for the aircraft. A helicopter is adapted for carrying a load external to the aircraft fuselage which load may be restrained by an FAA approved safety restraint. The load is equipped with a safety harness and lanyard apparatus having first and second lanyards attached thereto. According to the method, a helicopter hovers next to a structure, and safe transfer is accomplished by: (1) attaching the free end of the first lanyard to the helicopter; (2) releasing any auxiliary safety restraint; (3) attaching the free end of the second lanyard to the structure; (4) detaching the first lanyard from the helicopter; and (5) effecting transfer of the load to the structure.

Abstract: Apparatus for separating aerodynamic objects from an aerodynamic vehicle includes a first element, aerodynamically configured to create nose-down pitching moment, mounted to the object surface, a second element mounted to the first element and projecting into an oncoming airstream such that when enabled, the passing air tears the apparatus from the surface which otherwise supports it. The first element is a body designed to be conformal with the object surface to which it is mounted, and includes a forward end projecting into the oncoming airstream and a rearward end, and is secured to said object surface at the rearward end thereof. A flexible gasket is interposed between the first element and the object surface. The second element comprises a forward end directed toward the oncoming airstream and a rearward end, with the second element being mounted to the first element at the rearward end of the second element.

Abstract: A reconnaissance pod for viewing a scene has a structural backbone extending generally parallel to a pod axis, a forward housing affixed to the backbone, and an aft housing affixed to the backbone. The aft housing is separated from the forward housing along the pod axis. A central housing is mounted between the forward housing and the aft housing along the pod axis. The central housing includes a central body, a window through the central body, and at least a portion of a sensor assembly supported within the central housing from the forward housing and/or the aft housing. A rotational drive assembly has a forward support rotationally supporting the central body from the forward housing, with a forward bearing oriented to permit rotation of the central housing about the pod axis. The rotational drive assembly also includes an aft support rotationally supporting the central body from the aft housing, with an aft bearing oriented to permit rotation of the central housing about the pod axis.

Abstract: A device for hanging a load on a helicopter has at least one load-bearing cable which has a first cable section, which is off-center in relation to a longitudinal axis of the helicopter, and a second off-center cable section located opposite. The load-bearing cable is connected to the helicopter, on the one hand, and to the load, on the other hand. Ends and of the load-bearing cable are fixedly attached to the helicopter, and the load-bearing cable is connected to the load in a manner in which it can be moved relative to the latter, such that the load can be displaced along the load-bearing cable.

Abstract: A sonar buoy adapted to be deployed by a cruise missile. This sonar buoy includes a flotation device for keeping a portion of the buoy afloat, a hydrophone, a transmitter for communicating contact and position information and releasable means for attaching the sonar buoy to the cruise missile. By means of this device, a means of monitoring littoral and other waters for enemy submarines and other threats is provided with a low degree of risk to friendly forces. A system for deploying this sonar buoy in a sonar buoy field is also disclosed.

Abstract: Improvements in rotorcraft external load operations are disclosed, including a method for transferring a load from an airborne rotorcraft to a structure while providing fall protection for the load and emergency release capabilities for the aircraft. A helicopter is adapted for carrying a load external to the aircraft fuselage which load may be restrained by an FAA approved safety restraint. The load is equipped with a safety harness and lanyard apparatus having first and second lanyards attached thereto. According to the method, a helicopter hovers next to a structure, and safe transfer is accomplished by: (1) attaching the free end of the first lanyard to the helicopter; (2) releasing any auxiliary safety restraint; (3) attaching the free end of the second lanyard to the structure; (4) detaching the first lanyard from the helicopter; and (5) effecting transfer of the load to the structure.

Abstract: A pneumatic actuator operable to carry a missile on an aircraft and to eject the missile from the aircraft in flight on demand, includes a differential area piston which is slidable in a closed chamber which is filed with air under pressure. The smaller diameter portion of the piston is slidably engaged in a cavity which is formed in an end wall of the closed chamber. An actuating rod extends co-axially from the smaller diameter piston portion out of the closed chamber. Initial movement of the piston to actuate ejection of the missile is effected under low force by the application of pressure to the end of the smaller diameter piston portion remote from the larger diameter piston portion until the smaller diameter portion is displaced from the cavity into the closed chamber which allows the largest possible force to be exerted on the piston by the action of the compressed air on the larger diameter piston portion.

Abstract: Remote activation mechanism for equipment regulated deployment or release, that includes a cylindrical housing (1), connected by means of a rod (10) with the external equipment to be deployed including the acting mechanism, and has adhered a fusible material band in its internal surface (11). Inside the housing a cylindrical frame (2) connected with the fixed part of the equipment is disposed. That frame is provided with means to perform the local and progressive fusion of the fusible material band. Additionally a cylindrical sealing piece (3) is disposed in between the fusible material band (11) and the frame (2).

Abstract: The present invention provides a WARren Portal IDentification and tunnel resident disgorger System (WARPIDS) comprising a jet engine, a marker medium and a base. In a preferred embodiment, the jet engine is configured to create an engine exhaust that is aimable into a first portal of a warren, perhaps having a plurality of interconnecting tunnels. The engine exhaust thereby creates an overpressure within the warren such that the engine exhaust escapes from a second tunnel portal. The marker medium is coupleable to, and configured to flow with, the engine exhaust from the first tunnel portal and through the second tunnel portal thereby marking the second tunnel portal. The base, coupled to and supporting the jet engine, is configured to be transported and located proximate the first tunnel portal by a conventional aircraft.

Abstract: A payload dispensing system for an aircraft is disclosed that includes a housing mounted to the aircraft. A hollow shaft is mounted to the housing having an open first end and a closed off second end with a hole therethrough. The payload includes an aperture having a first end on an external surface thereof and a second end in the interior therein. A wire cable releasably secures the payload to the housing such that the hollow shaft extends into the aperture of the payload. A compression spring is mounted at least partially within the hollow shaft, having a first end in contact with the second end of the hollow shaft and a second end in contact with the second end of the aperture within the payload, the spring having a compressed position when the hollow shaft is within the aperture in the payload and asserts a force tending to separate the payload from the aircraft.

Abstract: A system for an aerial land marking and surveying is disclosed. The system comprises an aircraft carrying a GPS receiver and a land marking device capable of physically marking a point on the ground identified by a computer program. A new method of an aerial land marking and surveying and a land-marking device for carrying out the method are also disclosed.

Abstract: A device for picking up and dropping loads by helicopter without help of ground personnel has a member connected to a load; a magnetic member adapted to attract the member connected to the load; a channel associated with the magnetic member so that the member connected to the load and attracted to the magnetic member slides through the channel to a predetermined portion of the channel; a gate in the portion and including a first gate forming element and a second gate forming element spaced from one another and alternatingly activatable by a pilot so that, by activating the first gate forming element the member connected to the load is introduced into said gate, wherein when the second gate element is activated the gate is opened and the member connected to the load leaves the channel so as to drop off the load.

Abstract: In one embodiment, an airborne store suspension and release arrangement includes two slender “Tee” hangers located one on either side of a vertical plane through the center of the store. Each hanger has a narrow strut portion which is mounted on the store by one end and an enlarged cross section portion at the other end of the narrow strut portion. The enlarged cross section portion of each hanger is clamped by releasable clamps mounted in a store carrying aircraft. The store and the aircraft are formed with surfaces which abut one another when the store is suspended from the aircraft and the enlarged cross section portions of the hangers are clamped by the clamps. The arrangement of the hangers, the clamps and the abutting surfaces establishes a couple in reaction to a rolling moment to which the store is subjected during manoeuvring of the aircraft.

Abstract: This is a relatively simple load-lifting apparatus, tongs-like in appearance with a larger lower portion for grabbing loads of various sizes. It has two embracing halves, pivoted at a selected distance from the apparatus' top. It is designed to safely and reliably hold a person between its lower portions, without injuring one who may be disabled. Sensors have been added to enable it to sense the distance of the apparatus' lower portions from the object to be scooped up. When in range of the object its lower portions automatically separate, in order not to make contact with it, while being lowered. In its descent the apparatus could sway under the influence of wind gusts, thus not being able to precisely straddle the object to be retrieved. A technique using air bursts from solenoid-operated valves, mounted selectively on the apparatus to reduce the effect of wind-gusts, is provided. Compressed-air tanks are provided to supply the air to the valves.

Abstract: An automatic and sequencing pneumatic actuation assembly is provided for use in an ejection system capable of unlocking and forcibly ejecting stores from racks mounted on an aircraft or similar weapon carrier. The actuation assembly including a primary valve and release ram for reciprocating movement along a common longitudinal axis between closed and open positions. A solenoid control valve initiates movement of the primary valve by creating a pressure imbalance across the primary valve. Pressurized gas is caused to vent to an environment having a pressure lower than the pressurized gas, allowing the primary valve to move the release ram into engagement with a mechanism capable of unlocking the hooks before moving ejector pistons to forcibly eject the unlocked stores. A bias member is provided for automatically returning the primary valve to the closed position after the stores have been released.

Abstract: A parachute recovery system which provides for the recovery of a payload such as a target drone without damage by allowing for a safe, non-destructive landing of the payload at a desired landing location. The parachute recovery system comprises a payload, a parachute or parasail and a guidance control electronics and servo system. The parachute, which is rectangular in shape, is connected by a plurality of control lines to the guidance control electronics and servo system, which is attached to the payload. The payload may be an air launch component such as a spacecraft, a target drone, unmanned air vehicle, camera film, or similar apparatus. The guidance control electronics and servo system is used to control glide path trajectory and provide for a safe non-destructive landing of the payload.

Abstract: A radio frequency receiver, in response to input command signals from some remote source, initiates electrical powering of an electronic firing circuit through which electric pulses are generated and fed through a power cable to impulse cartridges at the upper ends of storage tubes within a payload dispenser. The impulse cartridges in response to such pulses ignites the payloads stored therebelow within the storage tubes closed by retention caps that are ejected with the payload from the dispenser during ignition.

Abstract: A remotely controlled aircraft has a center member and a steering assembly. The steering assembly comprises a carriage, a remote control motor, a center member and a connecting arm. The carriage pivotably is attached to the center member. The remote control motor has a control arm and is disposed within the carriage. The center member arm has a first end and a second end. The first end of the center member arm is fixedly attached to the center member. The center member and the center member arm is arranged in a non-parallel manner. The connecting arm has a first end and a second end. The first end of the connecting arm is pivotably attached to the second end of the center member arm. The second end of the connecting arm is pivotably attached to the control arm of the remote control motor.

Abstract: A compact universal apparatus which is mountable within an optimally sized weapons bay of a conventional fighter aircraft, which includes an automatic scissors or trapeze type lowering linkage mechanism for a conventional or inventory bomb ejector rack unit (BRU) having automatic latching, release and forced ejection mechanisms for conventional inventory weapons, characterized by an adaptor designed for the fixed attachment of the bomb ejector rack unit to the linkage of the lowering mechanism of the apparatus. The ejector rack unit is one adapted to the forced ejection of large bombs, attached or latched directly thereto, and to the rail launching of missiles having launching rails attached or latched directly to the ejector rack unit, with conventional automatic latch up of the bail lugs of the bombs to the launch rack lugs of the ejector rack unit, for forced ejection of the bombs, and with conventional automatic latch up of launch rails of conventional missiles for rail launching of the missiles.

Abstract: A release fitting for releasably holding at least one line to at least one item, the release fitting having a first body part, a second body part, and a third body part, the first and second body parts pivotably secured to the third body part, a bolt with a first bolt portion connected to a first portion of the first body part and a second bolt portion connected to a first portion of the second body part, at least one pin suitable for attaching thereto the at least one line, the first body part having a recess for releasably receiving an end of the pin, the bolt initially holding apart the first portion of the first body part and the first portion of the second body part to thereby maintain a second pin end in the recess, the third body part connected to the at least one item, bolt cutter apparatus for selectively cutting the bolt to release the at least one line from the pin.

Abstract: A universal warhead adapter comprises a tubular sleeve configured to contain any of various warheads of different configurations, and an aft bulkhead designed to replicate the aft end of a standard warhead with which existing tail assemblies are compatible. A universal missile is made by disposing a selected warhead within the sleeve and fixing the warhead therein with fastening mechanisms, and attaching a tail assembly to the aft bulkhead and a nose assembly to the forward end of the sleeve. Control surfaces, rocket motors, and/or turbine engines can be attached directly to the sleeve. An umbilical can be routed internally from a tail assembly through the sleeve and can be connected to an aircraft electrical system via an integral connector attached to the sleeve.

Abstract: A method and apparatus for actively enhancing aircraft weapon separation by actively modifying the flowfield characteristics of an open, shallow weapons bay during flight is disclosed. The apparatus includes a source of high pressure gas in fluid communication with an injector located on the aircraft. A control valve controls the introduction of a flow of high pressure gas from the source into the injector. The injector is placed ahead of the nose of the weapon and directs the flow of the high pressure gas externally into the airstream of the aircraft in flight. The injection of the high pressure gas into the airstream initiates a flowfield in the open weapons bay similar to that which occurs in a deep bay, encouraging a flat, even weapons separation.

Abstract: A towed vehicle deployment and retrieval system for attachment to an aircraft. The system includes a pylon support that is designed to mount to an aircraft and project outward therefrom. A stores pylon is mounted to the pylon support. The stores pylon has at least one swaybrace reciprocally attached to it for removably engaging with a towed vehicle. The system also includes a winch that is configured for mounting within the aircraft. The winch controls the feeding and retrieval of a winch cable that is attached to the towed vehicle. A tow cable is removably attached to the aircraft and is engaged with the winch cable using a tow pole such that the tow cable fully supports the towed vehicle when the towed vehicle is in the towing position. A method is also disclosed for attaching a winch cable and towed vehicle to a tow cable.