Abstract: Countermeasure simulating structures may include (a) a base and (b) one or more separated combustible tracks fixed to the base's surface. The combustible tracks may include thermite and/or other combustible material. The combustible tracks may be shaped to simulate countermeasure flares deployed by a vehicle (e.g., a jet). The countermeasure simulating structure may be incorporated into a countermeasure simulating system that includes (a) an infrared and/or optical sensing system (e.g., like those included in missiles) and (b) a simulator mount holding the countermeasure simulating structure.

Abstract: Described are example systems and methods that utilize simulated and/or actual flight data to determine an aerial delivery time estimate between a source location and a delivery destination, based on current flight conditions. For example, multiple flight simulations along a flight path between a source location and a delivery destination may be performed based on various different flight conditions and the flight time determined from the simulations may be maintained in a data store, associated with the flight path and simulated flight conditions. When a request for item information is received, current flight conditions may be determined and used to determine an estimated flight time based on stored simulated flight data having similar flight conditions to the current flight conditions.

Abstract: An unmanned aerial vehicle (UAV) base station includes a housing and a UAV fixation system. The housing includes a top-plate configured for a UAV to land on the top-plate. The UAV fixation system is configured to direct the UAV present on the top-plate to a battery-exchange zone of the top-plate.

Abstract: A UAV delivery control system is disclosed. Sensors detect operation parameters associated with the UAV as the UAV maneuvers along an airborne delivery route. A UAV operation controller monitors UAV route parameters as the UAV maneuvers along the airborne delivery route. The UAV route parameters are indicative as to a current environment of the airborne delivery route that the UAV is encountering. The UAV operation controller automatically adjusts the operation of the UAV to maintain the operation of the UAV within an operation threshold based on the operation parameters and the UAV route parameters. The operation threshold is the operation of the UAV that is maintained within an overall airborne operation radius of the UAV from a return destination thereby enabling the UAV to execute the delivery of the package along the airborne delivery route and to return to the return destination.

Abstract: A ballistic armor system comprising a metal strike face plate, a laminate composite backing material secured to the metal strike face plate and an air space provided between the metal strike face plate and the laminate composite backing material. The metal strike face plate has a predetermined defined thickness and has a plurality of slotted holes set at an oblique angle relative to the vertical orientation or axis of the metal strike face plate. The plurality of slotted holes is sufficiently small to prevent the passage of a projectile or fragment therethrough. The laminate composite backing material comprises at least one material selected from an aramid fiber material, S-glass, E-glass and UHMWPE, and is provided in combination with a polymer-based resin material. The air space provided between the metal strike face plate and the composite backing material has a depth in the range between 0-10 inches.

Abstract: A modular refueling system for an aircraft includes a modular bay recessed within the aircraft. The modular bay includes a modular bay interface. The modular refueling system includes a plurality of payload modules each having a respective function and a payload interface adapted to connect to at least a portion of the modular bay interface. The plurality of payload modules includes an aerial refueling module. The payload modules are interchangeably insertable into the modular bay to enable the modular bay to support the functions of the payload modules. The aerial refueling module is insertable into the modular bay to enable the aircraft to provide fuel to recipient aircraft during flight.

Abstract: An ignition system and method of igniting the ignition system includes a main catalyst section in a staged relationship with a pilot-catalyst section to stage a decomposition though the pilot-catalyst section which preheats the main catalyst section.

Abstract: The present invention provides a device for shoulder-launching operation. Stability and convenience on operation are enhanced. Furthermore, production is improved and maintenance difficulty is reduced.

Abstract: A device for safe firing is provided. The device is used in a tube of a rocket, like a shoulder-launched anti-armor rocket. The present invention has simple structure and small size. A few safety designs are used in the present invention to improve safety of the rocket tube during transportation. Those designs also prevent the rocket from misfire owing to lack of training.

Abstract: An unmanned aerial vehicle (UAV) system provides for UAV deployment and remote, unattended operation with reduced logistics requirements. The system includes a launcher that can include one or more launch tubes, each launch tube configured to house a UAV in a canister and one or more gas generators operatively connected to each canister and configured to push the UAV out of the launch tube by releasing gas into the canister. A controller for activating the gas generators can sequentially, and with a predetermined time delay, expel the UAV with a desired velocity and acceleration. The system further includes a UAV recovery device, a power supply, a security subsystem, a command and control subsystem and a communications subsystem. Command, control and communications can be provided between a remote station and the UAV.

Abstract: The present invention relates to launching system, more particularly relates to mobile launching system for missiles. The mobile missile launch system comprising a vehicle (14) having a chassis structure adapted to carry the launch system; a mounting frame (16) comprising predetermined truss framework mounted onto the chassis structure; plurality of sliding mechanisms mounted at rear end of the mounting frame (16); plurality of canisters (43) mounted onto said beam (22) and plurality of missiles (11) ensconced within the canisters (43); plurality of containers (42) enclosing said canisters (43) and are connected to the saddles (32, 34) for linear movement; plurality of resting units (27) abutting to rear end of the canisters (43) and are adapted to move linearly to transfer reaction forces from said missiles (11) to ground.

Abstract: A technique for launching a missile that avoids some of the costs and disadvantages for doing so in the prior art. In particular, the illustrative embodiment of the present invention uses an electromagnetic catapult to throw the missile clear of the launch platform—with sufficient velocity to attain aerodynamic flight—before the missile's engine is ignited.

Abstract: An electromagnetic launch system including an electrothermal launcher, an inductive power supply (IPS), including a DC source (Vb) and a storage inductor (L), and an opening switch (OS), wherein at least a portion of at least one of the IPS and the OS is integrated in a projectile.

Abstract: A method for adjusting the flight path of an unguided projectile, which comprises the steps of: (a) Measuring the magnitude and direction of the jittering of a projectile launch tube, at an ejection time of a projectile from the launch tube; (b) Measuring a velocity deviation of the projectile from a nominal velocity; (c) Measuring an angular deviation of the sight of the launch tube, being equal to the angular deviation between a line coinciding with the direction of gravity and a line passing through the center of the launch tube and the center of the sight; (d) Determining a compensating impulse vector to be applied to the projectile during an initial flight path thereof based on the magnitude and direction of the jittering, velocity deviation and angular deviation; and (e) Applying the compensating impulse vector to the projectile by activating a flight correction unit, the thrust developed by the flight correction unit suitable for adjusting the flight path of the projectile by a magnitude and direction

Abstract: A method and apparatus for thrust vectoring a flight vehicle during homing are disclosed. The flight vehicle includes a body; a plurality of attitude control mechanisms on the body; a multi-pulse motor housed at least partially in the body; and a control unit housed in the body. The control unit generates signals controlling an actuation of the attitude control mechanisms and the multi-pulse motor to initiate a follow-on burn of the multi-pulse motor to effect a maneuver directed by the actuation of the attitude control mechanisms. The method includes conserving a second burn of a dual pulse motor until target acquisition; acquiring a target; actuating a attitude control mechanism for the flight vehicle to alter the flight vehicle's heading; and initiating the second burn.

Abstract: A system and method for the conversion of fuel tanks, detachably mountable on the exterior of an aerial vehicle, into high volume, high capacity, diverse functionality and aerodynamically efficient airborne stores is disclosed. A conventional external fuel drop tank is modified such that the exterior shape of the tank is substantially retained while the interior of the tank is suitable restructured to allow for the introduction of diverse airborne stores, associated airborne store mounting means, control and monitoring means and support means therein, which replace the fuel store. The airborne store is suitably interfaced to the stores control and management system of the aerial vehicle. The airborne store is integrated into a new external stores configuration The enhanced airborne store will have aerodynamic characteristics substantially similar to the original external fuel tank while its payload capacity is substantially improved.

Abstract: A launcher (10) is provided having a separation unit (15) and a launch tube (16) in fluid communication with the separation unit (15). The separation unit (15) has a pressure sensing chamber (23) for sensing the pressure within the separation unit (15), a separation chamber (24) in fluid communication with the pressure sensing chamber (23), and a combustion chamber (26) in fluid communication with the separation chamber (24). The combustion chamber (26) is in fluid communication with the launch tube (16) through opening (28). The rocket launcher (10) also includes a hydrogen separation circuit (21) and an ignition circuit (22). The hydrogen separation circuit (21) includes a battery pack (44) electrically coupled to a fuel cell (45) which when powered separates water into hydrogen gas and oxygen gas. The ignition circuit (22) includes a piezoelectric spark generator (61) for igniting the hydrogen gas produced by the fuel cell and contained within the combustion.

Abstract: A lightweight multiple missile launch assembly (10) adapted to carry newer heavier Maverick missiles (AGM-65D, E, F, G or K). The invention is illustrated with a BRU-33, 55 or 57 bomb rack (12) adapted to carry two LAU-117 missile launchers (24, 26). The missile launchers (24, 26) are secured to the bomb rack (12) with a suspension unit (20, 22) of unique and novel design. The suspension units (20, 22) allow for releasable engagement of the missile launchers (24, 26). This allows for different missile packages to be deployed in the field.

Abstract: A mounting system for a cylindrical object such as a spotting rifle is provided. First and second U-shaped brackets are coupled to a base such as a launching device. Each U-shaped bracket has first and second legs extending from a common base. The two U-shaped brackets are oriented such that the first and second legs of one U-shaped bracket are perpendicular to the first and second legs of the other U-shaped bracket. Each U-shaped bracket slidably receives a sleeve between its first and second legs. Each sleeve is attachable to the bracket's common base such that the position of the sleeve relative to the bracket's common base is adjustable. A locking mechanism is provided with each U-shaped bracket/sleeve combination to lock the sleeve laterally between the first and second legs of the U-shaped bracket. The two sleeves are coaxially aligned.

Abstract: A smart laser pointer is disclosed in this application that includes a laser coupled to a processor that can disable the laser from operating for a period of time (T) based on a disabling trigger. The smart laser pointer may also include an optical receiver coupled to the processor that detects received laser signals that are emitted from the laser after they are reflected off of a target and a memory storing position information threshold limits. The processor calculates measured position information based on the received laser signals detected by the optical receiver and compares them to the position information threshold limits. A disabling trigger occurs when the position information exceeds the position information threshold limits. The position information and threshold limits may include a distance or a velocity.