Abstract: Technology is disclosed herein for a payload dispensing hinge assembly. The payload dispensing hinge assembly has a first hinge-half and a second hinge-half that are joined by a hinge pin. The first hinge-half may be connected to a payload that is to be dispensed at a target angle. The second hinge-half may be connected to a payload base. The first hinge-half may have a first mounting bracket and a rotatable arm that are shaped to form interlocks that serve to dis-engageably link these two components. A biasing mechanism rotates the rotatable arm and hence the first mounting bracket and payload about a hinge line. The second hinge-half has a hinge stop that stops the rotation of the rotatable arm at a target angle, whereby the first bracket dis-engages from the rotatable arm to dispense the payload at the target angle.

Abstract: A container suspension and release system provides at least one ejector assembly having a carry position and a deployed position. The ejector assembly includes an actuator configured to extend ejector assembly from the carry position to the deployed position, and a retention assembly. The retention assembly employs a bracket attached to the actuator and a fixed sway brace extending from the bracket. A left retention arm is pivotally attached to the bracket and a right retention arm is pivotally attached to the bracket, with the left and right retention arms configured to rotate in opposite directions. A rotation activation mechanism is provided to rotate the left and right retention arms in the deployed position. An energy source connected to the actuator to provides energy to actuate the at least one ejector assembly.

Abstract: A configurable spacecraft attachment and deployment system and a method of constructing a configurable spacecraft attachment and deployment system are provided herein. In one embodiment, the configurable spacecraft attachment and deployment system includes: (1) a connecting structure configured to secure at least one spacecraft to a launch interface, (2) an actuating assembly configured to constrain the spacecraft to the connecting structure before deployment thereof and release the spacecraft from the connecting structure when deployed, and (3) a deploying mechanism coupled to the connecting structure and configured to eject the spacecraft from the attaching structure, wherein the connecting structure, the actuating assembly, and the deploying mechanism are modular components and the connecting structure and deploying mechanism are selected to form the system based on parameters of the spacecraft.

Abstract: A cargo hook assembly for a helicopter is provided. The cargo hook assembly comprises a support structure having a forward end portion and a rearward end portion, and an attachment mechanism attached to the rearward end portion. The attachment mechanism is configured to engage a cargo hook mount on the underside of the fuselage of the helicopter. The cargo hook assembly further comprises first and second struts extending from respective opposing sides of the forward end portion. Each of the first and second struts is configured to engage a respective side mount on the fuselage of the helicopter. The cargo hook assembly also comprises a cargo hook suspended from the support structure.

Abstract: The invention refers to a pyrotechnic latch retraction mechanism that can be applied to various types of flying devices. The main structure of this mechanism includes piston-cylinder assembly, electric ignition assembly and guide assembly. The solution described in this invention not only makes the exploitation, use and preservation of equipment more convenient, reduces difficulties, prevents risks and saves costs, but also ensures safety and security, reliability during device operation.

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: A carrier of a spacecraft can include multiple latch assemblies that are linked together and held in place by one notched bolt or main shaft, which is out of the main load path. The latch assemblies secure the payload (e.g., CubeSat device) within a carrier by interfacing with pin assemblies on the payload. To deploy the payload, the shape memory alloy actuator is fired which causes a series of springs and preload forces to rotate latches of the latch assemblies out of the path of the pin assemblies. Once the latches are out of the way, the payload is deployed by a spring-loaded pusher assembly and guided through deployment using rollers. Each latch assembly is preloaded in tension using a corresponding preload lug of a receiver assembly.

Abstract: A suspension lug arrangement for a store suitable for aerial deployment has an outer surface and includes at least one lug region including a lug disposed in a body of the store. The lug includes a base portion embedded within and joined to the body of the store and a head portion extending outward from the base portion to the outer surface of the store, the head portion including an outer surface aligned with an adjacent portion of the outer surface of the body. The at least one lug region further includes a well at least partially surrounding the lug, a compressible member disposed within the well, and a plug retained within the well and engaging the compressible member disposed therein.

Abstract: A store ejector rack including a first hook member and a second hook member, a split sleeve guide member, and a pair of split sleeve members, including a first split sleeve member and a second split sleeve member, operatively coupled to the split sleeve guide member. The first split sleeve member is coupled to the first hook member and the second split sleeve member is coupled to the second hook member. A valve control assembly is operatively coupled to the split sleeve guide member, wherein actuation of the split sleeve guide member causes actuation of the first hook member, the second hook member, and the valve control assembly.

Abstract: A modular testable release mechanism for payloads incorporates a housing and a flyaway plate separably engaged to the housing. A plurality of symmetrically positioned ejection springs are compressed between the flyaway plate and housing in an engaged position. A bolt extends through a first bore in the flyaway plate and is releasably secured in an actuator mounted on the housing symmetrically surrounded by the ejection springs. The flyaway plate is held in the engaged position with the housing by the bolt.

Abstract: A method of providing apparatus comprising: providing a first store and a first payload on or in the first store, the first store being for mounting to the outside of an aircraft; acquiring aerodynamic properties, moments of inertia, and the mass distribution of the first store and first payload; providing a second store and a second payload, the second payload being on or in the second store, the second store being for mounting to the outside of the aircraft, the second payload being different to the first, the second payload comprising a sensor and/or a projecting means; and configuring the second store and the second payload such that the aerodynamic properties, moments of inertia, and mass distribution of the second store and the second payload are substantially the same as those of the first store and first payload.

Abstract: A fastener device (10) provided with attachment means (20) for attaching an external load (5) and with fastener means (30) provided with a support beam (40) and with anchor means (50) for anchoring said support beam (40). A first mechanical coupling (60) connects said support beam (40) to the anchor means (50) so as to enable the support beam (40) to pivot about a first pivot axis (AX1). In addition, coupling means (70) are hinged to the support beam (40) so as to make pivoting possible about a second pivot axis (AX2), the attachment means (20) being hinged to the coupling means (70) to make pivoting possible about a third pivot axis (AX3). This fastener device (10) includes automatic folding means (100).

Abstract: An extendable sway brace for a rack for an airborne payload. The sway brace is extendable. A mechanism for extending the sway brace includes means for preventing extension of the sway brace when the pressure exerted by the brace on a payload reaches a predetermined pressure. The means for preventing extension of the brace may include, for example, one or more pre-loaded springs. In this case, extension of the brace is prevented when the springs are compressed by a predetermined amount. The invention also provides a rack for an airborne payload comprising a sway brace of the invention.

Abstract: A rapid air transportation system for humans, animals, materials or facilities, comprises of rapid coupling of a carriage on land to the tether of a hovering aircraft using quick coupling methods and rapid de-coupling of the same at the end of transportation and landing of the carriage, without landing the aircraft.

Abstract: A suspension lug for releasably suspends loads under aircraft. The suspension lug has a lug eye and a threaded base and a rotation mechanism is inserted into the threaded portion. When the suspension lug is threaded into a compatible well in the load and the load is released from the aircraft, the rotation mechanism causes the suspension lug to rotate by ninety degrees from an initial orientation in which the face of the lug eye is pointed in the direction of flight to a final orientation in which the edge of the lug eye is pointed in the direction of flight. The rotation of the lug eye significantly reduces the drag on the load. Also described are methods of manufacturing and using the suspension lug of the invention.

Abstract: A system for releasing an article such as a munition or store from an aircraft employs a sway brace or cradle built into the structure of a bomb rack from lateral or pitching motion before it is released. A claw mechanism is driven out of the sway braces into the article to hold the article in place on the sway braces. The claws retain the article in the sway braces until the article is no longer influenced by the sway braces.

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

Abstract: An electronically controlled arming unit including a logic circuit that is driven by the pre-existing weapons system signals to control a lanyard locking unit, thus removing the need for an external force to operate the arming unit. The electronically controlled arming unit can be retrofitted to the existing equipment.

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

Abstract: A pin puller combines an actuator with an anti-friction release mechanism, according to a bilaterally symmetric geometry. The anti-friction tension release mechanism ensures that only negligible friction forces need to be overcome to operate the tension release mechanism. Thus, the actuator is isolated from the large tension force that bears on the tension release mechanism. The bilateral symmetric aspect of the structure provides for mechanical redundancy, so that, in the event that one half of the pin puller fails, it is sufficient that the other half operate properly for the tension to be successfully released. This pin puller avoids premature release because it is not susceptible to static electricity or electromagnetic radiation. The pin puller also avoids generation of large shock waves due to its slow speed of operation and because of the gradual release interaction of mechanical parts within the anti-friction release mechanism.