Abstract: A fixed wing flight vehicle has wing, a center-mounted propulsion unit and a pod that is moveable between a center of the wing and a displaced position at or near one end of the wing. When the pod is at or near the center of the wing, that is, having a center of mass at or near a thrust vector of the propulsion unit, the flight vehicle flies with the characteristics of a regular fixed wing aircraft. However, when the pod is translated to the position at or near an end of the wing, an overall center of mass of the flight vehicle is substantially offset from the thrust vector of the propulsion unit. This causes the flight vehicle to spin like a samara, e.g., a maple seed, so that the flight vehicle can take off or land in a very limited space, much like a helicopter.

Abstract: An aircraft (11) with at least an inflatable device (41) installed in a cavity (21) in its external surface which is equipped with a door (25) for opening/closing said cavity (21) is provided. The inflatable device (41), comprising a cushion (45) and a gas generator is configured for filling the cavity (21) with the cushion (45) when it is inflated with the gas supplied by said gas generator, without protruding from the cavity (21) for reducing the downstream air flow disturbances generated by said cavity (21) when the door (25) is open. The inflatable device (41) includes control means for inflating the cushion (45) in predetermined circumstances, being the door (25) open. The invention is particularly applicable to the cavities of the Main Landing Gear (31) for avoiding power losses to a Ram Air Turbine (51) placed behind it.

Abstract: A method to load stores on an aircraft, the method may be controlled by one or more controller and may include one or more acts of loading stores onto corresponding lift portions; determining a relative position of the aircraft; positioning the stores relative to the determined position of the aircraft; and securing the stores to corresponding hardpoints (HPs) of the aircraft.

Abstract: A cover for an empty rail missile launcher that can be used in flight. The cover is shaped to reflect radar signals transmitted by a radar transmitter away from the radar transmitter to reduce detectibility by radar. The cover may also be coated with radar absorbent material to reduce detectibility by radar. Hangers are used to mount the cover to the rail missile launcher. The cover is provided with a grounding mechanism to dissipate precipitation static. A restraint mechanism is provided to prevent the cover from inadvertently sliding off the rail missile launcher.

Abstract: An aircraft store ejector systems and subsystems thereof. Embodiments can include a two-reservoir re-pressurization system wherein a remote reservoir is used to maintain desired pressure in a local ejector reservoir. The system can include a release valve having a vent valve and valve piston. The release valve can control release of pressurized gas to a pitch control valve. The pitch control valve can be configured to distribute the pressurized gas between two or more ejector piston assemblies. One or more of the ejector piston assemblies can include multiple concentric piston stages and piston chambers, the piston chambers configured to contain a volume of gas. The ejector piston assemblies can be configured to compress the volume of gas within the piston chambers as the piston stages are extended out from the aircraft. Such compression can provide a return force to the piston stages.

Abstract: The present invention regards a pyrotechnic countermeasure (15, 25) dispensing system (1) comprising a set of contacting members (27, 27?) of a launching electronic circuitry (19). A first magazine (A) is mountable in said housing (23) in such way that a contacting body (41) of each pyrotechnic countermeasure (25) being in electrical communication with a dedicated contacting member (27) of the launching electronic circuitry (19), when the system (1) is ready to use. A central electronic unit (3) is associated with the launching electronic circuitry (19) for actuating of the pyrotechnic countermeasure (25) accommodated in the first magazine (A) in dependence upon a detected threat (29).

Abstract: The system comprises an outer container which is fixed, directly and fully, in the hold of the transport aeroplane (AC), and in which there is an inner container that can be moved longitudinally and brought from a first or carrying position in which it is situated fully inside the outer container into a second or off-loading position (P2) in which it is longitudinally offset towards the rear of the aircraft (AC) so that a part of the inner container is then situated outside the transport aeroplane (AC).

Abstract: The present disclosure relates to a system for carrying and dropping ammunition for a transport airplane. The system includes a container which contains at least one load, in particular ammunition, which is capable of being brought into a drop position, in which a portion is located outside the airplane, and from which a load can be dropped, usually by simply releasing the load.

Abstract: Certain exemplary embodiments can provide a system, machine, device, manufacture, circuit, composition of matter, and/or user interface adapted for and/or resulting from, and/or a method and/or machine-readable medium comprising machine-implementable instructions for, activities that can comprise and/or relate to, providing a guided descent from a release zone and toward an entry zone.

Abstract: An incendiary machine (10) comprises a feed and dispensing system (12), a priming system (20) and a control system. The feed and dispensing system (12) feeds a belt (14) of incendiary capsules (16) to a region at which individual capsules are separated from the belt and dispensed from the machine (10). The priming system (20) primes the capsule (16) prior to being dispensed from the machine (10) with a priming liquid which, when delivered into a capsule, facilitates an exothermic reaction. The control system controls the feed and dispensing system (12), and the priming system (20) independently of each other so that the belt (14) can be fed into and indeed thought the machine (10) with the priming liquid being injected into the capsules.

Abstract: A payload deployment system includes a mount for receiving one or more payload modules that each include one or more payloads to be deployed. The payload modules also each include a sleeve, with the one or more payloads are in one or more openings in the sleeve. The payloads may be contained in respective containers, such as hermetically-sealed containers, that are in the openings. The electrical coupling may be wireless coupling, for transferring electrical power to the payload module(s), and for communication, such as networked communication, between the mount and the one or more payload modules. The wireless coupling may be inductive coupling that involves overlap of inductive elements such as wire coils. The payload deployment system may also include one or more translators for translating commands and/or other communications between the one or more payload modules and a platform to which the payload deployment system is coupled.

Abstract: Attachable/detachable segmented ordnance dispenser systems and methods are presented. A control module targets, fuses, and releases ordnance, and at least one ordnance dispenser segment comprises a rack mount ordnance assembly and a segment enclosure. The rack mount ordnance assembly mounts and releases ordnance under control of the control module, and the segment enclosure comprises a segment door that opens under control of the control module. An aerodynamic shell aerodynamically enhances and protects the ordnance dispenser segment and the control module, and can be coupled to a vehicle.

Abstract: An apparatus for processing and dispensing incendiary capsules is provided. The apparatus includes a hollow tube which serves as a cylinder within which is located a reciprocal piston or a plurality of co-axially mounted pistons driven by a cam. When this coordinated cycle begins with the piston assembly in its full-down position, and the cam assembly is then rotated 360 degrees, the piston assembly will proceed to its full-up position and then back to its full-down position. During this cycle, the following occurs in order: (1) an incendiary is received and enclosed within the piston assembly, that incendiary is then (2) pierced by a needle, then (3) injected with reactant, then (4) the needle is withdrawn from the incendiary, and finally (5) the incendiary is expelled from the cylinder. The feeder is operatively connected with the cam-piston assembly and feeds each individual incendiary into the piston assembly.

Abstract: A bomb rack lock, as part of a bomb rack, comprising a plunger movable to engage a bomb rack linkage to be alternately secured and released and a solenoid body coupled to and operable to support the plunger. The plunger and the solenoid body are movable relative to each other and the bomb rack linkage and the solenoid body is movable between a first position and a second position. The bomb rack lock also includes a sensor to determine whether the solenoid body is in the first position. The plunger is movable to engage and disengage the bomb rack linkage with the solenoid body in the first position. In the second position, the solenoid body prevents engagement between the plunger and the bomb rack linkage.

Abstract: A mounting set for use in mounting an external stores to a mounting station of an aerospace vehicle includes a mounting bracket arrangement and a strap arrangement. The bracket arrangement is configured for selective reversible engagement with respect to the mounting station and for cooperating with the strap arrangement. The strap arrangement is configured for securing the bracket arrangement to the stores in load bearing abutment therewith to enable transfer of loads between the stores and the mounting station via said bracket arrangement, in operation of said mounting set. A mounting system is also provided for mounting an external stores to an aerospace vehicle having two or more mounting stations, including a mounting set for each mounting station. Mounting methods are also provided.

Abstract: A payload deployment system includes a mount for receiving one or more payload modules that each include one or more payloads to be deployed. The payload modules also each include a sleeve, with the one or more payloads are in one or more openings in the sleeve. The payloads may be contained in respective containers, such as hermetically-sealed containers, that are in the openings. The electrical coupling may be wireless coupling, for transferring electrical power to the payload module(s), and for communication, such as networked communication, between the mount and the one or more payload modules. The wireless coupling may be inductive coupling that involves overlap of inductive elements such as wire coils. The payload deployment system may also include one or more translators for translating commands and/or other communications between the one or more payload modules and a platform to which the payload deployment system is coupled.

Abstract: In order to allow decoy projectiles (6) to be launched with optimal quality of flight, the projectiles respectively comprise external cylindrical bodies (80) which are dimensionally identical, housed in said tube and each having a deployable-fins (9) aerodynamic stabilization device, that adopt a folded position inside the body when the projectile is in the tube, and a deployed position outside of the tube. To achieve that, said system comprises a projectile ejection system (8), with axial passage (12), arranged fixedly in the continuation of the tube, at the opposite end to the advance mechanism, and containing, in succession, after the control mechanism, the projectile (6) that is to be ejected by a controllable ejection device (25) connected to said module.

Abstract: An apparatus and method for dispensing incendiary projectiles is provided. The apparatus includes an injector for injecting the projectiles with a reactant at a dispensing rate, and a controller operable to control the dispensing rate. The controller is operable to control solenoids of a dispenser gate and a shuttle motor, and to prevent jam conditions of the apparatus. The apparatus can detect and automatically correct jam conditions that do occur. The apparatus can count the number of incendiary projectiles dispensed during a current operation and during the lifetime of the apparatus. The apparatus is dimensioned to minimize the number of incendiary projectiles purged from the apparatus after an operator has indicated to stop dispensing.

Abstract: A quick release illumination flare mounting arrangement particularly adapted for use in an aircraft. Includes a base plate mounted to the aircraft's deck, and an aperture in sealed contact with an upper end of a flare discharge tube coupled to a discharge aperture in the fuselage. A coupling assembly which includes a second aperture is easily coupled to and removed from the base plate by coupling pins. The coupling assembly further includes an upper plate adapted for secure, sealed, easily removable mounting to the lower end of a flare receiving tube.

Abstract: A dispenser unit including a plurality of compartments, each being adapted for storing and launching a payload and including an opening through which the payload is launched by a control unit/. A door is associated with the opening and is driven by a driver. The dispenser unit includes one common door being arranged in such way that it is drivable to cover the openings of the compartments from which the payloads have been launched.

Abstract: A decoy material dispenser. An elongated decoy material package includes an elongated strip-shaped container including a plurality of depressions receiving decoy material. A cover covers and hermitically seals the container. A gripping portion cooperates with a feeder including a gripper. A housing includes a storage section that stores the package. An outlet releases the decoy material. A waste collection section collects empty packages. A feeder device feeds the package from the storage section to the outlet and to the waste collection section. The feeder device includes a feeder and a driver. The feeder includes a gripper that cooperates with the gripping portion. The package is oriented in the dispenser such that the cover is directed towards the outlet and the container is directed away from the outlet. A force applicator applies pressure to the container. A package opener opens, cuts or perforates the package to release the decoy material.

Abstract: A countermeasure arrangement including a countermeasure dispenser. An envelope at least partly encloses the countermeasure dispenser. A first control module is configured to control the countermeasure dispenser. A suspension module is arranged on the envelope for suspending the envelope on an aircraft. The suspension module has a form and a design that substantially correspond to the form and design of a suspension rail of a missile, so that the suspension module mates to a hard point on the aircraft, which is adapted to the missile.

Abstract: An incendiary dispensing system (10) comprises a casing (12), a supply (16) of incendiary capsules (18), an apparatus (14) for initiating and dispensing the incendiary capsules (18), and a loading mechanism (20). The casing (12) can be opened and closed to enable loading of the supply (16) of incendiary capsules (18). The casing (12) is provided with an aperture (22) to allow the dispensing of initiated capsules (18). The capsules (18) are formed as series connected belts (24). The loading mechanism (20) sequentially feeds the belts (24) to the apparatus (14) which initiates each incendiary and dispense the incendiary from the opening (22). The casing (12) is arranged for external mounting on an aircraft and may be ejected in the event of a malfunction.

Abstract: A bomb rack lock, as part of a bomb rack, comprising a plunger movable to engage a bomb rack linkage to be alternately secured and released and a solenoid body coupled to and operable to support the plunger. The plunger and the solenoid body are movable relative to each other and the bomb rack linkage and the solenoid body is movable between a first position and a second position. The bomb rack lock also includes a sensor to determine whether the solenoid body is in the first position. The plunger is movable to engage and disengage the bomb rack linkage with the solenoid body in the first position. In the second position, the solenoid body prevents engagement between the plunger and the bomb rack linkage.

Abstract: An arrangement for storing and launching payloads. An elongate body includes at least one launch opening. The elongate body is configured to store the payloads in compartments. The compartments include openings. The arrangement is configured to be mounted on a vehicle with a longitudinal direction of the elongate body essentially coinciding with a direction of motion of the vehicle. The elongate body includes deflectors configured to act on an air stream and to permanently create an air covering layer across and over the compartment openings during use.

Abstract: In one embodiment there is provided a radar signature and induced aerodynamic drag minimizing, externally mountable, internally configurable pod structure optimized for internal placement of one or more deployable stores through configuration and optimal kinematic operation of a pod door assembly. The pod structure has an externally mountable pod housing, a predetermined pod housing cross-sectional configuration optimized to provide a configurable interior volume accommodating multiple different store configurations, and a predetermined pod housing configuration having a cross-sectional configuration optimized to minimize a radar signature and an induced aerodynamic drag. The pod structure further has a pod door assembly integral with the pod housing and having a plurality of pod doors and one or more seal door mechanism assemblies. The pod structure is optimized in kinematic operational combination of the pod doors and seal door mechanism assemblies controlling ejection launch envelopes.

Abstract: A method for launching counter-measures from a launch opening of a dispenser mounted on an aeroplane. The counter-measures are launched in a direction obliquely forwards and downwards relative to the aeroplane. In order to facilitate launching of counter-measures, a low dynamic pressure is created permanently across the launch opening of the dispenser by a fixed element acting on the air stream. An arrangement for storing and launching counter-measures including an elongate body provided with at least one launch opening used for storing the counter-measures in compartments. The arrangement is designed to be mounted on an aeroplane with the longitudinal direction of the elongate body essentially coinciding with the flight direction of the aeroplane. The counter-measures are connected to a firing control unit for feeding firing signals to the counter-measures. The arrangement is designed to be mounted under the aeroplane.

Abstract: A mounting set for use in mounting an external stores to a mounting station of an aerospace vehicle includes a mounting bracket arrangement and a strap arrangement. The bracket arrangement is configured for selective reversible engagement with respect to the mounting station and for cooperating with the strap arrangement. The strap arrangement is configured for securing the bracket arrangement to the stores in load bearing abutment therewith to enable transfer of loads between the stores and the mounting station via said bracket arrangement, in operation of said mounting set. A mounting system is also provided for mounting an external stores to an aerospace vehicle having two or more mounting stations, including a mounting set for each mounting station. Mounting methods are also provided.

Abstract: An incendiary machine (10) comprises a feed and dispensing system (12), a priming system (20) and a control system. The feed and dispensing system (12) feeds a belt (14) of incendiary capsules (16) to a region at which individual capsules are separated from the belt and dispensed from the machine (10). The priming system (20) primes the capsule (16) prior to being dispensed from the machine (10) with a priming liquid which, when delivered into a capsule, facilitates an exothermic reaction. The control system controls the feed and dispensing system (12), and the priming system (20) independently of each other so that the belt (14) can be fed into and indeed thought the machine (10) with the priming liquid being injected into the capsules.

Abstract: An apparatus and method for launching incendiary projectiles is provided. The apparatus includes a support adapted to being mounted to a vehicle, a pneumatic launcher connected to the support and operable to launch a projectile that has been delivered to the launcher, a gas delivery system operable to deliver a volume of pressurized gas to the launcher for launching the projectile, a projectile delivery system operable to deliver projectiles to the launcher, an injector cooperating operable to receive projectiles from the projectile delivery system and to inject the projectiles with an amount of reactant suitable to produce a delayed exothermic reaction with the incendiary material to prime the projectile, and thereafter convey the primed projectile to the launcher; and a controller operable to operable to regulate the launching of the projectiles.

Abstract: Apparatuses, vehicles, and methods to reduce loads applied to a store when the store is launched from the vehicle are disclosed. A particular apparatus includes a launch chamber and a flap. The launch chamber has a first portion configured to receive a store. A second portion is configured to be positioned over an opening in a hull of a vehicle. The chamber has a forward end and an aft end. The flap is positioned a distance from the aft end of the launch chamber. The flap has a first end rotatably mounted proximate to the first portion of the launch chamber and has a second end extending toward the second portion of the launch chamber. The flap is configured to rotate about the first end when the store impacts the flap due to the forces applied to the store by the fluid when the store is launched.

Abstract: A system and method for launching countermeasures, such as flares and chaff, from an aircraft under attack by a missile. A plurality of countermeasure launchers are mounted preferably on the two sides and tail and nose of the aircraft and communicate with a missile detection and warning system mounted in the aircraft. Based upon the circumstances reported by the warning system, the appropriate countermeasure weapon or weapons are selected and dispensed. The circumstances reported are based upon the angle of elevation and azimuth angle of the approaching missile in relation to the aircraft and distance of the missile from the aircraft. Also, the speed and altitude of the aircraft are utilized in determining the countermeasures applied. The various responses are distinguished by the number and types of countermeasures dispensed, the dispense time of the countermeasures and the particular launcher or launchers used, based upon the type of aircraft being protected.

Abstract: An arrangement for storing and launching payloads. An elongate body includes at least one launch opening. The elongate body is configured to store the payloads in compartments. The compartments include openings. The arrangement is configured to be mounted on a vehicle with a longitudinal direction of the elongate body essentially coinciding with a direction of motion of the vehicle. The elongate body includes deflectors configured to act on an air stream and to permanently create an air covering layer across and over the compartment openings during use.

Abstract: Apparatuses, vehicles, and methods to reduce loads applied to a store when the store is launched from the vehicle are disclosed. A particular apparatus includes a launch chamber and a flap. The launch chamber has a first portion configured to receive a store. A second portion is configured to be positioned over an opening in a hull of a vehicle. The chamber has a forward end and an aft end. The flap is positioned a distance from the aft end of the launch chamber. The flap has a first end rotatably mounted proximate to the first portion of the launch chamber and has a second end extending toward the second portion of the launch chamber. The flap is configured to rotate about the first end when the store impacts the flap due to the forces applied to the store by the fluid when the store is launched.

Abstract: In accordance with the present invention, there is provided a deployment device that is operative to deploy Special Material (SM) to protect the vehicle when an enemy infrared (IR) threat is present. The deployment device constructed in accordance with the present invention comprises at least one, and preferably a pair of canisters which are each filled or loaded with SM, then factory sealed to prevent oxidation or contamination. Each of the canisters included in the deployment device includes an input shaft which, when rotated, is operative to transmit the rotary motion to each of four threaded rods. The rods have two primary functions, which are to advance a piston thereby preloading the SM within the canister toward the open end thereof, and to turn rotary metering devices which are located at the open end of the canister. The advancing piston maintains consistent compression in the SM stack within the canister.

Abstract: Systems and methods for launching munitions are provided. In some embodiments, the system may include a cover for use with a munitions launcher including a housing with a face. The cover may include a lid, a defined passage through the lid, and an actuator. The lid may be configured to mount to the face of the munitions launcher. The defined passage through the lid may be sized to allow a munition to pass through the lid when launched by the launcher and to substantially cover any other munitions disposed at least partially within the munitions launcher. The actuator may be configured to operate the lid in a manner that moves the defined passage in relation to the face of the munitions launcher. Movement of the defined passage in relation to the face of the munitions launcher may uncover at least one munition that was substantially covered prior to the movement of the defined passage and substantially cover any other munitions disposed at least partially within the munitions launcher.

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 pylon 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 dispenser for a platform, configured to be mounted to the platform and connected to power- and control-systems of the platform. The dispenser includes a magazine for a plurality of pyrotechnic countermeasure cartridges. The magazine is configured for removable fixation to the dispenser by one single fixing bolt in a central location thereof for securing the magazine to the dispenser in an operative mode. A first lock associated with the dispenser and a second lock associated with the magazine are configured to arrest the fixing bolt in interlocking engagement with the first lock and preventing the fixing bolt from coming loose due to environmental influence.

Abstract: A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead having destructive elements. The weapon also includes a folding lug switch assembly that provides a mechanism to attach the weapon to a delivery vehicle and is configured to close after launching from the delivery vehicle, thereby satisfying a criterion to arm the warhead. The weapon still further includes a guidance section including an antenna configured to receive mission data before launching from the delivery vehicle and further configured to receive instructions after launching from the delivery vehicle to guide the weapon to a target.

Abstract: Stores launch tubes and vehicles equipped with stores launch tubes are disclosed. According to a particular illustrative example, a stores launch tube includes a tube member and a flexible seal. The flexible seal couples an exterior of the tube member to a hull. The flexible seal acts as a pressure barrier against an ambient environment.

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: An incendiary dispensing system (10) comprises a casing (12), a supply (16) of incendiary capsules (18), an apparatus (14) for initiating and dispensing the incendiary capsules (18), and a loading mechanism (20). The casing (12) can be opened and closed to enable loading of the supply (16) of incendiary capsules (18). The casing (12) is provided with an aperture (22) to allow the dispensing of initiated capsules (18). The capsules (18) are formed as series connected belts (24). The loading mechanism (20) sequentially feeds the belts (24) to the apparatus (14) which initiates each incendiary and dispense the incendiary from the opening (22). The casing (12) is arranged for external mounting on an aircraft and may be ejected in the event of a malfunction.

Abstract: According to one embodiment, a chaff pod includes at least two dispensers disposed within a chaff pod housing. Each of the dispensers has a surface defining an opening through which a number of countermeasures may be dispensed. The dispensers are configured to be coupled to the aircraft. The first dispenser directs countermeasures in a first direction, and the second dispenser directs countermeasures in a second direction. The difference between the first direction and the second direction form a relative angle.

Abstract: The object of the inventive method and device for controlling and/or extinguishing fires is to extend the range of means for transporting devices to a fire site, substantially reduce the time for the operating preparation thereof and to exclude a fragmentation field caused by the device explosion which ensures the momentary conversion of a fire-extinguishing composition into a fine cloud associated with a simultaneous airblast effect produced to a fire area and a maximum distribution of said fire-extinguishing composition through the fire volume. Said method for controlling and/or putting out a fire consists in effecting the fire area by an airblast and the high-speed flow of the air-dispersed mixture of the fire-extinguishing composition (7) produced by the explosion of a fire-suppressing device (2) which comprises a dispersing charge (8) and a container (6) with the fire-extinguishing composition (7).

Abstract: An apparatus and method for dispensing incendiary projectiles is provided. The apparatus includes an injector for injecting the projectiles with a reactant at a dispensing rate, and a controller operable to control the dispensing rate. The controller is operable to control solenoids of a dispenser gate and a shuttle motor, and to prevent jam conditions of the apparatus. The apparatus can detect and automatically correct jam conditions that do occur. The apparatus can count the number of incendiary projectiles dispensed during a current operation and during the lifetime of the apparatus. The apparatus is dimensioned to minimize the number of incendiary projectiles purged from the apparatus after an operator has indicated to stop dispensing.

Abstract: Stores launch tubes and vehicles equipped with stores launch tubes are disclosed. According to a particular illustrative example, a stores launch tube includes a tube member and a flexible seal. The flexible seal couples an exterior of the tube member to a hull. The flexible seal acts as a pressure barrier against an ambient environment.

Abstract: The present invention provides an unpowered low-cost “smart” micromunition unit for a weapon system for defense against an asymmetric attack upon ships and sea or land based facilities. A plurality of air dropped micromunition units are each capable of detecting and tracking a plurality of maneuvering targets and of establishing a fast acting local area wireless communication network among themselves to create a distributed database stored in each deployed micromunition unit for sharing target and micromunition unit data. Each micromunition unit autonomously applies stored algorithms to data from the distributed database to select a single target for intercept and to follow an intercept trajectory to the selected target. It is emphasized that this abstract is provided to comply with the rules requiring an abstract that will allow a searcher or other reader to quickly ascertain the subject matter of the technical disclosure.

Abstract: A carriage and release system for stores (armaments such as rockets and bombs) on an aircraft includes a bracket adapted for attachment to the aircraft. A pylon is mounted on the bracket for movement in a pitch direction relative to the aircraft. A mechanism is provided to power the pitch movement and position it at a predetermined angle relative to the aircraft. A variety of stores carriers may be employed with the pylon. Subcarriages may also be mounted to the pylon for attaching additional stores carriers.

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: 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.