Abstract: A hollow cylinder has an electromagnet to hold back a canister and either an induction heating linear actuator or a firing pin to ignite the primer-containing combustive material inside the canister to eject a locked piston from the cylinder. There is a motor-included turbogenerator around the cylinder, which converts the energy of the post-combustion gases into electricity to get stored and to power an integrated or separate annular stator assembly to give the ejected piston a rotatory motion for stability in projectile motion. Another device has a helically arranged, multi-pole permanent magnet assembly annularly integrated around the cylinder to give the ejected piston a rotatory motion for stability in projectile motion. In other forms, an annular stator assembly around the cylinder is supplied with switched, externally generated electric power without either a turbogenerator or the motor-included turbogenerator to respectively produce electricity or to provide gyroscopic stability to the cylinder.

Abstract: The invention generally relates to a pod based countermeasure dispensing system for external mounting on wide variety of manned aircraft. The pod based system is readily configurable for dispensing different types of infrared countermeasure (IRCM) devices and different types of radio frequency countermeasure (RFCM) devices at a rapid rate. The primary use of the rapidly dispensed IRCMs and RFCMs is to protect the host aircraft while ingress and egress maneuvers are performed in a hostile area. A secondary use of the pod based countermeasure dispensing system is for use in defending commercial aircraft from missile threats.

Abstract: The invention generally relates to a method of using a pod to rapidly deploy defensive countermeasures from a wide variety of manned aircraft. The method includes using a configurable pod for dispensing different types of infrared countermeasure (IRCM) devices and different types of radio frequency countermeasure (RFCM) devices at a rapid rate. The primary purpose of this method is to rapidly dispense IRCMs and RFCMs is to protect the host aircraft while ingress and egress maneuvers are performed in a hostile area. A secondary use of the method is for use in defending commercial aircraft from missile threats.

Abstract: The pylon of the present invention provides damping of vibrations transferred in both directions between the aircraft and the payload. That is, the pylon of the present invention damps the effects of aircraft vibrations on the payload as well as the effects of payload vibrations on the aircraft. This is accomplished in the present invention by substantially eliminating any rigid connection between the aircraft and the payload under normal operational conditions. Support of the payload is provided by a plurality of resilient suspension elements that are attached to both a base element and a payload interface element. The attachment is such that the payload element is suspended below the base element. Thus configured, the resilient suspension elements dampen the transmission of vibrations between the payload interface element and the base element.

Abstract: A store ejection system for an aircraft includes a store ejector, and a power source for the store ejector. The power source has a fuel supply of a flowable combustible fuel, an oxidizer supply of a flowable oxidizer, a combustion chamber that controllably receives the combustible fuel from the fuel supply and the oxidizer from the oxidizer supply and forms a combustible mixture thereof, an igniter that controllably ignites the combustible mixture in the combustion chamber, and a combustion-gas line extending from the power source to the store ejector.

Abstract: An apparatus (10) for initiating and dispensing an incendiary comprises a feed mechanism (12) for advancing a line of series connected incendiaries to a dispensing location D; an injection device (14); and a cutter (16). The injection device (14) injects a substance such as glycol into the incendiary as it is moved toward, but prior to reaching, the dispensing location D. The glycol reacts exothermically with another substance such as potassium permanganate in the incendiary. The cutter (16) cuts the incendiary into which the glycol has been injected from the line of series connected incendiary. After the incendiary has been injected with the glycol and cut by the cutter (16) from the line, the feed mechanism (12) advances the incendiary to the dispensing location D where it is dispensed by the action of gravity from the apparatus (10).

Abstract: An exemplary stores launch tube includes an outer tube and an inner tube. The inner tube is disposed interior the outer tube and is configured to reduce load as a store exits therefrom. The inner tube may be made of a flexible material. At least one load-reducing device may be disposed between the inner tube and the outer tube. The inner tube may be received within a canister that has an outer casing that is attachable to the outer tube. Alternately, the inner tube may be attached directly to the outer tube. The inner tube may include more than one tube section. If desired, filler material, such as foam, may be disposed between the inner tube and the outer tube. The outer tube may have a substantially circular cross-section, or an oval cross-section, or any cross-section as desired to accommodate structural considerations.

Abstract: A decoy device and system for anti-missile protection and an associated method are provided. The decoy device includes a propellant and a tank containing the propellant. The decoy device also includes an outlet defined in the tank, and a catalyst contained within the tank and capable of exothermically reacting with the propellant to emit a gas having a heat and pressure. The heat generated by the reaction is radiated by the decoy device is capable of attracting a missile, while the gas is expelled through the outlet to provide thrust to the decoy device.

Abstract: A device for launching unmanned missiles from an aircraft with a pallet, on which at least one container is provided to receive a missile. The container has an upper container section that has a pylori for the suspended, detachable support of the missile. The container has a lower container section that is embodied as a support area for the missile.

Abstract: A pneumatic sonobuoy launcher adapted for simultaneously storing, and sequentially and independently launching, at least two sonobuoys includes a barrel with a closed back end, an expulsion end opposite the back end and an interior sonobuoy-guiding channel extending between the opposed ends. The channel is adapted for storing a series of sonobuoys including rearwardmost and forwardmost sonobuoys stored, respectively, closest to the back end of the barrel and closest to the expulsion end of the barrel. Each stored sonobuoy occupies a distinct region of the channel separated by an interval from at least one other region.

Abstract: An incendiary 10 includes a plurality of containers 12 each containing a volume of a first substance such as potassium permanganate which, when mixed with a second substance such as glycol which is injected at a later time, reacts exothermically to generate a flame. Frangible couplings in the form of tabs 16 couple or connect adjacent containers 12 together. Thus the incendiary 10 is in the form of a flexible belt having a plurality of containers 12 which are mutually held together until separated by a dispensing/initiating machine. Each container 12 includes a flat surface 22 and a receptacle 18 having an opening 20 which opens onto the flat surface 22. A seal 24 extends across and closes the opening 20.

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: 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: 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: 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: The present invention relates to a method and an arrangement for launching counter-measures, such as flares and chaff. According to the invention, the counter-measures are launched in a direction obliquely forwards and upwards relative to the aircraft and a low dynamic pressure is created across the dispenser's launch openings. The arrangement comprises compartments for counter-measures which are provided with openings and are intended for launching the counter-measures in a direction obliquely forwards and upwards relative to the aircraft. The invention increases the possibilities of releasing a target and reduces the noise levels of the sounds which can occur in emptied compartments.

Abstract: The present invention relates to a dropping device, preferably borne by a carrier aircraft, for distributing interference medium and especially electronic raspberry. The device according to the invention represents in principle an improvement to the device known through SE 8302508-0 and it is characterized firstly in that it has been provided with separately rotatable accelerator shafts (14, 15), which have the dual function firstly of acting as locks for an unwanted feed-out of interference medium packs (4) and secondly, when a feed-out has been activated, of executing this and giving the fed-out interference medium pack (4′) an increased feed-out speed, partly due to the device having been provided with a totally new, specially configured indexing mechanism.

Abstract: A method for making a degradable practice mine including the steps of covering a flat work surface with a polyethylene sheet to serve as a release film, weighing out the materials in a ratio of 10 parts sand to 1 part polyvinyl alcohol (PVA), mixing 1 part PVA with 10 parts sand making a sand/PVA mixture, filling a mold with the sand/PVA mixture, consolidating the sand/PVA mixture to make a consolidated form in the shape of a mine, and heating the consolidated form to make a hardened mine form mimicking the shape and launching characteristics of a tactical mine.

Abstract: A cruise missile, such as the Tomahawk cruise missile, is adapted to deploy decoys in an area as the missile progresses along its preprogrammed course. Each decoy is shaped to be compatible with and ejected from the Tomahawk and has a preprogrammed control unit operating a transmitter connected to an extendible antenna. False beacon signals and/or false message signals are transmitted from each of the decoys to deceive and confuse defensive forces, such as enemy searchers looking for a downed airman.

Abstract: A set of inert mines are loaded into a canister, where each of the inert mines includes a locating feature for a dispersion strap. A breech includes a reusable slider housing. A closure cap covers another end of the canister. An obturator is inserted into a breech end of the canister and connected as an interface between the canister and a breech. The dispersing strap is anchored to the breech where the dispersing strap is woven around the inert mines within the canister such that the strap traverses the locating feature of at least some of the inert mines so as to disperse the mines in a simulated mine dispersion pattern when the canister is fired.

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: An explosive countermeasure device is designed to negate an electro-optical seeker system of a missile at least temporarily so that it loses lock on a target aircraft. The device has a central explosive charge with a detonator and a container surrounding the charge for holding a noble gas under pressure. When the charge is detonated, the resultant explosive shock wave will heat the gas to a temperature sufficient for it to emit a short, intense flash of light before the container disintegrates, blinding the electro-optical seeker system at least temporarily.

Abstract: An air-dropped ammunition includes an ammunition body having a rearward portion; a firing pin accommodated in the rearward portion; a stabilizing band being received in a folded state at least partially in the rearward portion of the ammunition body; and a device for securing the stabilizing band to the firing pin. The device includes a disk having an upturned rim. The disk engages face-to-face one of two overlapping ends of the stabilizing band, and the upturned rim is oriented away from the overlapping ends. The overlapping ends and the disk are firmly attached to the firing pin.

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.