755results about "Military adjustment" patented technology

A VTOL vehicle comprising a fuselage having forward and aft propulsion units, each propulsion unit comprising a propeller located within an open-ended duct wall wherein a forward facing portion of the duct wall of at least the forward propulsion unit is comprised of at least one curved forward barrier mounted for horizontal sliding movement to open the forward facing portion to thereby permit air to flow into the forward facing portion when the VTOL vehicle is in forward flight.

A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, a pilot's compartment formed in the fuselage between the lift-producing propellers and substantially aligned with one side of the fuselage, a payload bay formed in the fuselage between the lift-producing propellers and opposite the pilot's compartment, and two pusher fans located at the rear of the vehicle. Many variations are described enabling the vehicle to be used not only as a VTOL vehicle, but also as a multi-function utility vehicle for performing many diverse functions including hovercraft and ATV functions. Also described is an Unmanned version of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles.

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.

A pressurized bulkhead or panel for an aircraft includes an energy absorbing skin that deforms in response to an object strike that imparts at least a threshold amount of impact energy to the skin. The skin may be configured as a dome or a lofted panel that is essentially free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristics of the skin. The skin may be formed from a monolithic one-piece material, such as metal of composites, and may include various integrally formed reinforcing features.

A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, and a body formed in the fuselage between the lift-producing propellers. Many variations are described enabling deflection and affection of flow streams and reduction of drag and momentum drag which improve speed and forward flight of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles.

The present invention is a device, system(s) and/or method(s) for disrupting, capturing, and/or disabling and unmanned aerial vehicle(s) in flight, on the ground, or preparing for flight that may or may not be under the control of the invention operator. In certain embodiments, the invention is supported and carried by an unmanned aerial vehicle that is controlled by a ground operator, a computer process and associate hardware, or any combination thereof. In other embodiments, the invention contains physical destruction devices such as projectiles, explosives, spikes, electric shock generators, etc. The invention is manipulated to track, intercept, capture, disrupt, disable and/or move a target unmanned aerial vehicle. In certain embodiments, the invention includes materials able to contain, at least in part, hazardous materials and/or conditions caused by the target unmanned aerial vehicle. In certain embodiments, the invention interfaces with external unmanned aerial vehicle detection/tracking systems. A unique design element in certain embodiments is the ability to limit the potential of the captured aerial vehicle escaping the device and/or falling to the ground. Another unique design element in certain embodiments is the ability of the invention to limit collateral damage caused by the captured unmanned aerial vehicle or apparatuses contained thereon. Another unique design element is the ability of the invention to interface with external unmanned aerial vehicle detection/tracking systems.

Modularized insulation blanket for thermal and/or acoustical insulation. The modularized insulation blanket has a cover formed of a distal layer and proximal layer in sealed mated relationship. The distal and proximal layers are sealed along longitudinal and latitudinal heat-sealed seams that define a plurality of modules. The heat-sealed seam may be creased so as to be foldable and/or perforated to provide a tear line. Within the modules are batting blocks. The blankets may be attached to surface structures such as the interior skin surface of an aircraft fuselage, pipes or other structures with retention systems. The blankets may be formed in an apparatus including a platen, heat seal rollers or heating sealing mechanisms, and edge sealers.

A mobile radar system including Electronic Support Measures (ESM) which is adapted to detect and decode Identify Friend or Foe (IFF) signals. The system includes means for decoding or decrypting received IFF signals. The system uses an Electronic Counter Measure (ECM) transmitter which is adapted to transmit IFF response and interrogation signals. The IFF signals to be transmitted can be encrypted. Integrating IFF means into the ESM and ECM components results in mass and volume savings due to shared use of the transmitting and receiving resources. As the IFF signals are transmitted using ESM antennas, they can be directed towards a particular aircraft, thereby reducing spurious transmissions.

A protective liner includes a base layer that can be affixed to an aircraft canopy or other substrate, a conductive polymeric interlayer positioned over the base layer, and a conductive top layer containing a reactive organic salt, or a hygroscopic salt, positioned over the conductive polymeric interlayer. The substrate can also be treated with a multilayer stack (including a substrate base coat layer, a metal layer positioned over the substrate base layer, a metal oxide layer positioned over the metal layer, and a tie layer positioned over the metal oxide layer). The protective liner can be affixed to a pretreated substrate by lamination or other means to form an enhanced, multilayer stack having beneficial properties.

An ordinance, such as a rocket propelled grenade, shield includes a net with hard points at select nodes of the net and cable guides on the side of the net. Cables under tension extend through the cable guides supporting the net typically in conjunction with a top cross bar, spaced top struts, and spaced bottom struts. This framis design facilitates entering and exiting the vehicle or structure.

A transfer of ordnance units (20) from a first aerial vehicle (10) to a second aerial vehicle (14) performed while both vehicles are airborne. The first aircraft (10) is used as an ordnance storage, ordnance delivery and ordnance supplier platform. The second aircraft (14) has the functionality and capability of delivering the received ordnance (20) to designated targets. The first aircraft (10) includes an ordnance storage apparatus, an ordnance transfer assembly (22), a computer-based highly accurate ordnance transfer control apparatus, and an ordnance transfer apparatus operating crew. The ordnance transfer assembly (22) establishes temporarily a transfer link between the aircraft and utilizes an ordnance conveyor mechanism for the delivery of the ordnance units (20). The second aircraft (14) includes a multi-use multi-purpose pylon (16) that receives the transferred ordnance (20) in the proper manner. The aircrafts can be uninhabited.

The design and attachment of an insulation package according to an exemplary embodiment, which may be installed near the fuselage structure, is believed protect the cabin region of an aircraft against fire whose flames act on the insulation package from outside the aircraft environment, thus clearly facilitating evacuation of the passengers from the vehicle. The insulation package arrangement may comprise several fuselage insulation packages of an elongated form. These packages may adjoin the aircraft fuselage structure in the direction of the longitudinal axis of the aircraft. They may longitudinally adjoin a support surface of the stringers which are attached to the aircraft fuselage, or longitudinally adjoin an inner area of a panel of outer skin and are attached to both longitudinal sides of the ribs. Furthermore, those insulation packages may be completely enclosed by a burn-through-proof foil which is arranged in a space enclosed by interior paneling and by the panels of the outer skin. The design of a fuselage insulation package may be implemented with burn-through-proof insulation of a larger cross section and/or a burn-through-proof barrier layer of a smaller cross section which are arranged within the fuselage insulation package either singly or in combination. In this arrangement, the insulation or the barrier layer extends near to or adjacent to an interior wall region of the foil wall. As an alternative only that insulation which on the longitudinal end of the fuselage insulation package continues outward with a flat insulation end section is attached outside of and adjacent to the foil circumference of the fuselage insulation package. Said end section of insulation is attached to a rib-attachment region which is arranged below the respective longitudinal sides of a rib and near the stringer by means of burn-through-proof attachment elements.

An aircraft forward pressure bulkhead as described herein includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristic of the dome. Practical embodiments of the bulkhead utilize fewer parts, are less heavy, and are less expensive than traditional bulkheads that utilize rigid stiffeners.

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.

A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that couple to outer wing sections and possibly other sections using hardpoints. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.