Abstract: The present invention concerns a method for launching a payload (3) by means of an arrangement (1), which is configured for storing and launching a payload (3). A launch compartment (5) of the arrangement (1) is configured to eject the payload (3) from the launch compartment (5) via a push-out chamber (7) to an airflow (AF), which during use of the arrangement (1) flows over an aerodynamic surface (9) of the arrangement (1). An air intake (13) is formed in the aerodynamic surface (9) and is coupled to the push-out chamber (7) and/or launch compartment (5) via an internal air transfer arrangement (17) comprising an openable closure member (11) configured to close and open the internal air transfer arrangement (17).

Abstract: There is provided an arming apparatus for a store, the apparatus comprising: a first attachment system and a second attachment system; a linking connector coupled with the first attachment system and the second attachment system; and an arming clip; wherein each of the first attachment system and the second attachment system comprises: a first frangible connector coupled with the arming unit and the linking connector; and a second frangible connector coupled with the linking connector and the store. The linking connector is coupled to the first attachment system via a first coupling arrangement and is coupled to the second attachment system via a second coupling arrangement, wherein the first coupling arrangement and the second coupling arrangement are different. Each of the first coupling arrangement and the second coupling arrangement are manually secure.

Abstract: There is provided an arming apparatus for a store, the apparatus comprising: a first attachment system and a second attachment system; a linking connector coupled with the first attachment system and the second attachment system; and an arming clip; wherein each of the first attachment system and the second attachment system comprises: a first frangible connector coupled with the arming unit and the linking connector; and a second frangible connector comprising a first end coupled with the linking connector and a second end comprising a clip, the second end being configured to pass through a lug of said store and then couple to the second frangible connector.

Abstract: A seat belt system for restraining an occupant of a vehicle. The system includes a webbing and a pretensioner. A cable connects the webbing to the pretensioner. The pretensioner includes a housing, a gas generator, and an outer cylinder connected to the housing. A gas generator provides gases into a pressure chamber in the outer cylinder to drive a piston, an inner cylinder and the cable in a pretensioning direction. A sealing ring is located between the outer cylinder and inner cylinder. The sealing ring is configured to provide a seal to prevent the gases provided by the gas generator from passing. A deflector shield is located between the outer cylinder and the inner cylinder and closer to the pressure chamber than the sealing ring, wherein the deflector shield is configured to deflect the gases away from the sealing ring.

Abstract: A sequencer for use with a countermeasure defense system includes an input signal indicative of firing an expendable, a circuit card that receives the input signal indicative of firing the expendable and an output analog signal from the circuit card that fires the expendable. The parameters of the output analog signal correspond to parameters of a digital waveform.

Abstract: A flow body for an aircraft includes a recess in a surface of the flow body, a first structural component with a porous material and may also include a second structural component with a porous material. The recess includes a front recess region and a rear recess region. The first structural component is arranged in, or on, the front recess region and the second structural component may be arranged in, or on, the rear recess region. An aircraft having the flow body, a weapons system having the flow body and a method for manufacturing a flow body for a vehicle are also described.

Abstract: A dispenser for storing and launching countermeasures, where the dispenser is adapted for storing the countermeasures in a magazine, where the dispenser is provided with at least one launch opening and where the dispenser is adapted to be mounted on an aircraft, where the dispenser includes a body, a bracket and a magazine housing, where the bracket is rotatable with respect to the body and where magazine housing is rotatable with respect to the bracket, where the magazine housing includes a storage space adapted to hold the magazine, and where the launch opening is arranged in the magazine housing. The invention also includes a method for rotating the magazine and launching a countermeasure. The advantage of the invention is that a countermeasure can be directed in a desired angle before it is launched.

Abstract: Provided is an unmanned aerial vehicle including a waterproof container including: a container main body having an opening in a bottom surface defined in a landed state of the unmanned surface aerial vehicle; a waterproof door mounted to the container main body so as to open outward and close the opening; an elastic seal, which is interposed between the container main body and the waterproof door, and is configured to close the waterproof door in a liquid-tight manner; a first door-closing mechanism configured to retain a first door-closing state of the waterproof door; and a second door-closing mechanism configured to prevent movement of the waterproof door in a door-opening direction in a second door-closing state in which the waterproof door has been pushed in a direction of resisting against an elastic force of the elastic seal from the first door-closing state.

Abstract: Systems, devices, and methods including a launch control box; a multi-pack launcher (MPL) box; and a cable connecting the launch control box and the MPL box, where the cable comprises: an outer jacket, a shielded braid, a first wire, a second wire, a third wire, and a fourth wire, where the first wire and the second wire are shielded by the shielded braid, where the third wire and the fourth wire are outside of the shielded braid, and where the third wire and the fourth wire act as an antenna.

Abstract: A lightweight energetic weapons pod 2 that integrates to unmanned aerial systems 1 that enables the operator the ability to engage targets without flight degradation. The device utilizes an energetic weapons pod 2 that may be reloaded to support sustained combat operations. The ability of the device to function as intended is based on explosive mitigation compression zones and recoilless configurations that allow drone survivability during detonation events.

Abstract: The present disclosure provides a release launching system that is operative to receive and retain a drone or other payload in a protected launcher. The launcher helps to reduce the drag of the payload and to protect the payload from environmental factors. The payload is launched when a force initially separates the payload from the launcher and exposes a force generating mechanism. The force generating mechanism may be within the body portion of the device and generate an additional force to assist in separating the payload from the launcher. The payload may be launched using a biasing and fastening mechanism, which may include detachably coupling bracket, to allow for the separation of the payload from the launcher.

Abstract: A projectile delivery module to be mounted on an aerial vehicle includes a projectile delivery system including a kinetic projectile and a base system. The kinetic projectile includes a projectile body, an RF receiver, and an onboard steering system including: a steering mechanism operable to change an attitude, orientation, and/or direction of flight of the kinetic projectile; and a steering actuator. The base system includes: an RF transmitter to communicate with the RF receiver; a projectile holder; a target tracking system; and a projectile guidance system including a projectile tracking system and a projectile control system.

Abstract: Disclosed are systems and methods for carrying an aeronautical or launch vehicle to altitude for release to independent flight. The system may comprise one or more mounting elements affixed to a carrier aircraft along a mounting axis and actuatable from a retention configuration to a release configuration. The retention configuration enables the mounting elements to secure the vehicle to the carrier aircraft. Actuation from retention configuration to release configuration releases the vehicle from the carrier aircraft. A detent element is configured to restrict movement of the vehicle rotationally about, and axially along, a roll axis of the vehicle with respect to the carrier aircraft when the vehicle is secured to the carrier aircraft. The system may include an adaptor beam to which each mounting element is fastened, and by which the affixing is achieved. The retention configuration may enable the mounting elements to secure the vehicle beneath the carrier aircraft.

Abstract: The present disclosure provides rolling release launching system that is operative to receive and retain a drone or other payload in a protected launcher. The launcher helps to reduce the drag of the payload and to protect the payload from environmental factors. The payload is launched when a rotating door opens to expose the payload in a bay area. The rotating door may be parallel or concentric to a longitudinal axis of the body portion of the device. The payload may be launched using a biasing and fastening mechanism, which may include detachably coupling bracket, to induce an angular moment and releasing force on the payload during launch.

Abstract: Package delivery systems and methods may include a bistable beam coupled to an aerial vehicle, a bistable hook coupled to an end of the bistable beam, and a package carried by the bistable hook. The bistable beam may move between a reeled position and an extended position, and the bistable hook may move between a closed position and an open position. In addition, the bistable beam may include frangible connections or portions. Further, release or disconnection of frangible connections or portions of the bistable beam, as well as operations of the bistable hook, may be effected by passive or active methods.

Abstract: A warhead includes a gas generator, a plurality of barrels, and a plurality of projectiles. The warhead is configured to selectively actuate the gas generator to generate a pressurized gas that energetically propels the projectiles through and out from the barrels to strike a target.

Abstract: Disclosed is a device and method to load stores on an aircraft. The device may include a controller configured to: assign one or more stores to the aircraft; and control at least one actuator to: control a position of the aircraft; load the one or more stores onto one or more corresponding lift portions; position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from at least one sensor; and secure the one or more stores to the aircraft.

Abstract: When the tension across the cord's 24 length reaches a predetermined threshold, an activation mechanism within the payload 16 and coupled to one of the cord's 24 ends is actuated in order to activate the payload 16. Activating the payload 16 may include deactivating a SAFU, activating a motor 32 disposed within the housing, or causing flight controls to extend from a housed position. Here, “within the payload 16” may mean part of the activation mechanism is disposed on the outer surface or housing of the payload 16.

Abstract: A restrain and release mechanism for an externally airborne load, includes at least one stiff support for suspending the load and an elastically deformable adaptive member designed to maintain the load at pressure contact against the support. The adaptive member is a three-dimensional monolithic metallic body obtained using an additive manufacturing method and having a flexural orthotropic behaviour.

Abstract: An improved toy vehicle playset contains a tower and multiple track portions coupled to the tower that provide a path for toy vehicles to descend from the top of the tower. The tower may include an elevator mechanism for transporting toy vehicles up the tower and an interactive feature that is configured to interact with descending toy vehicles along the track portions. The descent of the toy vehicles may trigger the interactive feature to also descend from the top of the tower, where the descending interactive feature may attempt to impede or stop the descending toy vehicles along the track portions. In some embodiments, the one or more towers may further include platforms configured to store and retain a plurality of toy vehicles, mechanisms that trigger one or more toy vehicles to be launched from the platforms, and mechanisms for diverting toy vehicles onto the platforms.

Abstract: A system and method palletize containers having electrical terminals for charging electronic devices packaged therein. First, a stacking pattern is determined on the basis of the sizes, shapes, and locations of electrical terminals on both the pallets and the containers to be stacked. These data may be read, for example, with a computer vision system that uses an articulating robotic arm, and may be encoded in a two-dimensional barcode on each pallet and/or container. Next, the robotic arm stacks the container so that its terminals make electrical contact with terminals on the pallet, or on a previously-stacked layer of containers. Then, the placement is tested to ensure that a good electrical connection exists vertically through the entire stack. Once the pallet is finalized, all electronic devices carried thereon may be simultaneously charged during transit or storage.

Abstract: There is provided an arming apparatus for a store, the apparatus comprising: a first attachment system and a second attachment system; a linking connector coupled with the first attachment system and the second attachment system; and an arming connector coupled with the linking connector and a first fuze input of the store; wherein each of the first attachment system and the second attachment system comprises: an arming unit; a first frangible connector coupled with the arming unit and the linking connector; and a second frangible connector coupled with the linking connector and the store.

Abstract: Aeronautical conveying and release device comprising a frame, an actuator releasing a device, a first and second hook holding the device, first and second locking toggles having a locking and unlocking position, first and second cams in contact with the first or second toggle in a first direction, movement of the first or second cam in a second direction causing the toggle to leave the locking position and the unlocking of the hook, a third cam actuated from and returns to an idle position, a fourth cam driven by the third cam into unlocking, the third cam unlocking the first cam, a fifth cam coupled to the first cam, a safety member with lever with a first position which blocks the unlocked cams, the first cam and the second cam being blocked unlocked, blocking the locked toggles, a second position where the lever is blocked by the fourth and/or the fifth cam, and a third position where the lever frees the cams.

Abstract: A container retention and release apparatus includes an actuator a swaybrace and retention assembly pivotally coupled to the actuator. The swaybrace and retention assembly pivot relative to the actuator between a first position to retain a container and a second position to release the container.

Abstract: A cavity system, comprising: a cavity (2) comprising a cavity opening; and an acoustically reflective structure (18, 20) located at least partially within the cavity (2), the acoustically reflective structure (18, 20) comprising one or more acoustically reflective surfaces (24, 26, 30, 32), each acoustically reflective surface (24, 26, 30, 32) being oblique to a plane of the cavity opening (27). The one or more acoustically reflective surfaces (24, 26, 30, 32) may be arranged to reflect incident acoustic waves out of the cavity opening while avoiding reflection into a region (48) at or proximate to a leading edge (14) of the cavity (2).

Abstract: A detonation system for a perforating gun assembly. The detonation system includes a tandem sub having a first end and a second opposing end. Each of the first and second ends is connected to a respective perforating gun. The tandem sub has an inner bore, and a switch housing residing within the inner bore. The tandem sub also has an addressable switch residing within the switch housing with the switch being configured to receive instruction signals from a surface by means of an electric line. The addressable switch is in communication with a signal transmission pin and a detonator pin. The detonator pin sends a detonation signal from the addressable switch to a detonator in an adjacent perforating gun. The wiring connections for the pins may be pre-assembled before the perforating guns are delivered to the field.

Abstract: Fast verification of data integrity of non-volatile memory cells is disclosed. In one aspect, an estimate is made of a bit error rate (BER) associated with the data to be verified without fully decoding the data. If the estimated BER is below a threshold, then the storage system reports that the data meets a data integrity criterion. If the estimated BER is above the threshold, the storage system may decode the data to determine a BER and report whether the data meets the data integrity criterion based on the determined BER. The estimate of the BER may be based on a syndrome weight of the data, a BER of an XOR codeword formed from multiple codewords of the data, or a BER of a sample of the data. Hence, considerable time and power are saved verifying data integrity, at least when the data is not fully decoded.

Abstract: A high transport efficiency aircraft apparatus for precisely delivering a payload at a target area without stopping is disclosed. An aircraft is adapted to fly at low speed and less than 10 feet above ground level over the target area, with a delivery trajectory including a steep descent toward the target area and a steep ascent away from the target area. The aircraft includes a payload bay constructed to contain the payload within the aircraft, and a payload release mechanism adapted to release the payload from the payload bay when the aircraft flies over the target area, allowing the payload to fall and arrive unharmed at the target area unaided by an aerodynamic deceleration device.

Abstract: A system is described and includes a first track assembly for connecting a top surface of a pallet supporting payload to an upper interior surface of a payload bay of an aircraft; a second track assembly for connecting a side surface of the pallet to a side interior surface of the payload bay; and a pallet actuator system for selectively moving the pallet along the first and second track assemblies between a first position in which the pallet is fully extended from the payload bay and a second position in which the pallet is fully retracted into the payload bay.

Abstract: Container retention and release apparatus are disclosed. An example container retention and release apparatus includes an actuator, a swaybrace coupled to the actuator, and a clamp pivotally coupled to the swaybrace. The clamp pivots between a clamping position to retain a container and a release position to release a container.

Abstract: An aerodynamic braking device for a payload casing intended to be ejected from a projectile on its trajectory including at least one parachute connected to the casing by hangers, the parachute and the parachute hangers being housed in a sleeve. The sleeve is wound around an axis of winding perpendicular to its longitudinal direction and attached to a cylindrical housing the axis of which is parallel to the axis of winding, which housing is itself secured to a shell base that closes off the projectile, the hangers being connected to the casing by an extension cable which is wound around the axis of the housing and attached thereto by at least three peripheral break lines which are uniformly angularly distributed.

Abstract: Disclosed in the embodiments of the present invention is a monitoring method applied to a vehicle. The method includes: determining a movement state of the vehicle as a target movement state, and broadcasting a target broadcast control channel signal; and after receiving an access request reported by a mobile terminal on the basis of the target broadcast control channel signal, initiating a monitoring apparatus of the vehicle to monitor an environment in which the vehicle is located. Further disclosed in the embodiments of the present invention are a monitoring device and a computer storage medium.

Abstract: A modular weapon carriage and deployment (MWCD) system includes a strongback structure mountable to an aircraft. Left and right guide struts have respective upper ends attached to the strongback structure in spaced lateral positions. Each guide strut extends downward in a parallel arrangement. Each guide strut comprising a vertically-extending first engaging surface. Left and right suspension modules are engageable to opposite lateral sides of a first airborne store. Each suspension module includes a vertical channel that receives the engaging surface of the corresponding one of the left and right guide struts for relative vertical translation. A locking mechanism controllably locks to first engaging surface of the corresponding one of the left and right guide struts.

Abstract: The present disclosure provides rolling release launching system that is operative to receive and retain a drone or other payload in a protected launcher. The launcher helps to reduce the drag of the payload and to protect the payload from environmental factors. The payload is launched when a rotating door opens to expose the payload in a bay area. The rotating door may be parallel or concentric to a longitudinal axis of the body portion of the device. The payload may be launched using a biasing and fastening mechanism, which may include detachably coupling bracket, to induce an angular moment and releasing force on the payload during launch.

Abstract: An unmanned aerial vehicle (UAV) jettison apparatus. The UAV jettison apparatus may comprise a payload bay, fairing, ejector plate, and releasable latch. The payload bay may be mounted beneath an aircraft and may have an inner space and a top plate attached therewith. The fairing may substantially cover the inner space of the payload bay and may have an opening positioned directly below the top plate. The ejector plate, which may be spring-loaded, may substantially cover the opening and may be used to mount the UAV. The releasable latch, which may be disposed between the top plate and the ejector plate, may releasably lock and hold the UAV in a stowed position and, upon release, may allow the ejector plate to move into a launch position, such that the UAV is released and jettisoned from a larger aircraft.

Abstract: Systems and techniques for sensor-derived object flight performance tracking are described herein. A set of magnetometer readings may be obtained from a magnetometer included with an object. A local rotation axis of the object may be determined at a time using the set of magnetometer readings. The local rotation axis may describe rotation of the object around a local magnetic target. A global rotation axis may be calculated based on an initial orientation of the object. The global rotation axis may describe a fixed rotation axis of the object during flight in a global coordinate frame, wherein an angle between the global rotation axis and magnetic north remains constant during the flight. An orientation of the object may be determined for the time using the global rotation axis and the local rotation axis of the object at the time.

Abstract: Disclosed is a device and method to load stores on an aircraft. The device may include a controller configured to: assign one or more stores to the aircraft; and control at least one actuator to: control a position of the aircraft; load the one or more stores onto one or more corresponding lift portions; position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from at least one sensor; and secure the one or more stores to the aircraft.

Abstract: A pneumatic launcher has a pressure transfer system, a pressure regulation device, a first coupler and a second coupler. The pressure transfer system has a body, a transfer channel and a valve. The transfer channel traverses through the body. The valve is integrated into the transfer channel. The pressure regulation device is connected to a first end of the transfer channel. The first coupler is connected to the pressure regulation device opposite to the first end of the transfer channel. The second coupler is connected to a second end of the transfer channel, opposite to the pressure regulation device. The first coupler is in fluid communication with the second coupler through the pressure regulation device, the transfer channel and the valve.

Abstract: Apparatus for releasing a payload from an air vehicle (14), the apparatus comprising a generally tubular holding device (10) mounted on, or formed integrally with, said air vehicle, said holding device (10) having an open end facing in a direction substantially opposite to the direction of travel (16) of said air vehicle (14), in use, the apparatus further comprising a container (18) for housing said payload and configured to be at least partially received within said holding device (10), at least one releasable retaining device (20) for releasably retaining said container (18) within said holding device (10), and an actuation device for selectively actuating said at least one releasable retaining device to release said container from said holding device, said container (18) having thereon at least one drag inducing device (22) configured to induce drag in a direction substantially opposite to that of said direction of travel (16) of said air vehicle, in use, so as to act to drag said container (18) from said

Abstract: Disclosed is a device and method to load stores on an aircraft. The device may include a controller configured to: assign one or more stores to the aircraft; and control at least one actuator to: control a position of the aircraft; load the one or more stores onto one or more corresponding lift portions; position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from at least one sensor; and secure the one or more stores to the aircraft.

Abstract: A hatch for closing an opening provided through an aircraft structure, related structure and method are provided. The hatch includes an inner sealing partition, intended to be mounted sealably on an aircraft structure and a locking assembly releasable from the inner partition on the structure. The hatch includes a valve for balancing pressure between an inner surface of the inner partition intended to be placed in an inner volume of the aircraft and an outer surface of the inner partition, intended to communicate with the outside of the aircraft. The valve is movable by a user between a closed sealing position and an open pressure balancing position. The releasable locking assembly is immobilized in its locking configuration when the valve is its closed sealing position.

Abstract: An aircraft has a wing and at least a portion of a hoist system disposed within the wing. A method of hoisting an item includes disposing at least a portion of a hoist system within a wing of an aircraft and extending a cable of the hoist system through an access hole of an exterior wall of the wing.

Abstract: A system for dropping a package from an aircraft, a related aircraft and a method are provided. The system includes a panel configured to form part of a skin of the aircraft, the panel defining a through opening emerging outside the aircraft; a removable hatch and a sleeve guiding the hatch through the panel. The guide sleeve defines the through opening. The hatch is configured to be maneuvered in the guide sleeve between a configuration closing the through opening and a configuration allowing the package to pass through the through opening.

Abstract: An apparatus for a network of electrical and/or electronic devices coupled to a data bus comprises a sensor coupled to the data bus and configured to capture information content communicated through the data bus in a form of electromagnetic emissions being at least one of differential mode electromagnetic emissions, common mode electromagnetic emissions, coupled radiated electromagnetic emissions, and data bit streams; one or more processors or logic devices, and a non-transitory computational medium comprising executable instructions. The apparatus measure a feature value in at least one region of a time domain or a frequency domain of the captured electromagnetic emissions, calculates a difference value between the measured feature value and one or more baseline feature values, and determines, based on the calculated value, a presence or an absence of anomalies indicative of at least one of cyber intrusion attempt, cyber attack, cyber-physical attacks, malware, etc.

Abstract: An aircraft comprises a weapons bay, the weapons bay comprising a cavity having an opening through which stores may be deployed, and a door assembly for exposing/closing the opening of the cavity. A first store is held in the cavity via a launcher and a first structure is disposed inside the cavity, for controlling the aero-acoustic environment. The first structure for controlling the aero-acoustic environment is removably mounted in the weapons bay, such that if the first store is exchanged for a second, different, store, the structure for controlling the aero-acoustic environment may be unmounted from the weapons bay and removed, to be exchanged for a second, different, structure for controlling the aero-acoustic environment.

Abstract: The invention relates to a pyrotechnic carrier structure made from profiles (1) that can be interconnected on the edges thereof and with relative rotational freedom in order to form a firing base (20), to be horizontally arranged on the ground or warped for the arched arrangement thereof on support elements (12) formed by pairs of housings (13 and 14, 15 and 16, 17 and 18). Furthermore, the longitudinal movement of the profiles is avoided.

Abstract: An aircraft weapons control system including a weapons stores processor panel for receiving input signals from a weapons input; a weapons interface for receiving fire signals from the weapons stores processor panel to control firing of aircraft weapons; and a flight management system in communication with the weapons stores processor panel and the weapons interface, the flight management system providing control signals to the weapons interface; wherein the weapons stores processor panel implements safety interlocks to prevent or enable firing of the aircraft weapons.

Abstract: An effector launch system includes a stowable effector launcher housing having a housing panel configured for coupling with a vehicle, and one or more receptacle brackets movably coupled with the housing panel. The one or more receptacle brackets include one or more effector launcher sockets. The launch system further includes one or more effector launchers. Each effector launcher includes an effector received within an adapter housing. The stowable effector launcher housing is movable between deployed and stowed configurations. In the deployed configuration the one or more receptacle brackets extend from the housing panel and the one or more effector launchers are received within the one or more effector launcher sockets. In the stowed configuration the one or more effector launchers are removed from the one or more effector launcher sockets and the one or more receptacle brackets are stowed along the housing panel.

Abstract: An aircraft door 18 which closes an opening of a storage space 16 for storing a RAT 13 as an accessory and which is opened in association with deployment of the RAT 13 from the storage space 16, the door including: a door body 20 that opens and closes the opening, and whose front surface faces an outside and whose rear surface faces the storage space 16 in a closed state; and a fence 24 that rises from the rear surface of the door body 20. In a traveling direction of the aircraft, the fence 24 is located anterior to a position where the RAT 13 is stored. The fence 24 prevents an airflow Air from passing through between the RAT 13 and the door body 20 in an initial stage where the door 18 starts to be opened, thereby suppressing the aerodynamic force in the closing direction acting on the door body 20.

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.