Abstract: An engine mount for an aircraft engine. The engine mount includes a rigid structure forming a box closed at its forward end by a forward closure rib, and a mounting system including a forward engine attachment having an attachment body fixedly mounted on the rigid structure. The attachment body lies against a forward surface, and the engine mount includes at least one shear pin passing at least in part through the attachment body and forward closure rib.

Abstract: A crash attenuation system for an aircraft, the system having an airbag carried by the aircraft and inflatable generally adjacent an exterior of the aircraft. The airbag has at least one vent for releasing gas from the interior of the airbag. A first gas source is in fluid communication with the interior of the airbag for inflating the airbag with gas generated provided by the first gas source. A vent valve is provided for controlling a flow of gas through each vent, each vent valve being selectively configurable between an open state, in which gas can pass through the associated vent from the interior of the airbag, and a closed state, in which gas is retained within the interior of the airbag. A second gas source is provided for at least partially re-inflating the airbag after venting of gas through the at least one vent.

Abstract: A refueling apparatus for interconnecting a tanker aircraft (11) with a receiver aircraft in flight comprising a boom (21) joined to said tanker aircraft (11) by means of a mechanical articulation (41) having control means including a central computer station, an inner fuel conduit, a refueling nozzle (27) at its distal end and, and a smart tip assembly comprising a first module (83) having load sensing means, a second module (85) having load alleviation means and a third module (87), joined to the nozzle (27), having a mechanical fuse (99) for allowing the safe separation of tanker and receiver aircraft in the event of overloads. The invention also comprises a method of load alleviation for minimizing the loads on the boom (21).

Abstract: The invention relates to a material for absorbing noise in aircraft, comprising at least one barrier layer and at least one absorptive layer. The barrier layer is provided with an elastomeric material having a minimum specific density of 1 and a mass per unit area of 1.3 kg/m2 or less while the absorptive layer is equipped with a porous and/or open-cell material having a weight per volume of 4 to 50 kg/m3, preferably 10 to 40 kg/m3, more preferably 15 to 35 kg/m3 even more preferably 20 to 30 kg/m3. The mass per unit area of the sound-absorbing material amounts to 2 kg/m2 or less.

Abstract: A method and apparatus for transferring fuel onto or off of an aircraft. A refueling transfer duct is deployed from an aft station of the aircraft being serviced while the aircraft is flying, wherein the transfer apparatus comprises a hose with a controllable drogue attached to its free end. The refueling duct is positioned through control signals sent by a tanker aircraft to the controllable drogue to form a favorably positioned refueling duct capable of a finite final docking maneuver. The positioned refueling duct is connected to the tanker aircraft positioned behind the aircraft to form a connection. The fuel is transferred through the connection to a fuel tank or fuel storage system located within the aircraft.

Abstract: A low-wing, low-span canard aircraft with a protected pusher-style propeller is designed to transition simply between use in the air and use on the ground, without any mechanical effort on the part of the pilot. The vehicle may include deformable aerodynamic bumpers, embedded road-safety vehicle lighting and license plates, a protected propeller, and an integrated RFID airport access system. The vehicle may be designed for potential certification by the Federal Aviation Administration as a Light Sport Aircraft.

Abstract: An apparatus and method for blending fluids and applying the blended fluid to a surface of an aircraft during deicing and anti-icing operations having a first tank, second tank, blend tank, pumps, conduits, heaters, controllers, and a delivery device. In operation, a controller compares the composition of the blended fluid in the blend tank to the composition of a target fluid that is determined by current ambient temperature of the environment, and advances first and second fluids from the first and second tanks, respectively, into the blend tank to achieve and maintain the target fluid composition in the blend tank.

Abstract: A flight control system and method which determines an expected power required data in response to a flight control command of the at least one model following control law and utilizes the expected power required data to perform at least one action to control an engine speed.

Abstract: A device for protection against icing for aircraft engines including at least one sensor, sensitive to an amount of accumulated ice, arranged in the air intake of an aircraft engine, a system for measuring the amount and comparing the amount to be predetermined threshold and a triggering system for launching a response to the detection of the crossing of the predetermined threshold, the response may be an alarm, an increase in the engine power delayed by the engine control system or the return of hot air upstream of the engine.

Abstract: An ejection delay system, apparatus and/or method including an electronic ejection delay system having an ignition device; a power source connected to the ignition device; and, a flight parameter sensor switch electrically connected to the power source to initiate the provision of power from the power source to the ignition device; the electronic ejection delay system being disposed in some implementations in a housing system including a housing; a forward closure for closing the top end of the housing; and, an aft closure for closing the aft end of the housing. Also disclosed is a method for ejecting a rocket recovery system in flight; including sensing a parameter associated with flight; and, initiating deployment of a recovery system.

Abstract: An aircraft having counter-rotating, ring-type wing rotors that are driven by engines located at the wing tips is disclosed. The aircraft incorporates large span, high aspect ratio wings that are configured in a joined-tip design to improve the structural characteristics of the wings. One of the wings counter-rotates inside the other wing to enable vertical take-off and landing. The wings may comprise elliptical shapes, each having upper and lower sections that are separated from each other.

Abstract: A system and methods for airborne launch and recovery of aircraft. In one embodiment the system comprises a flexible tether configured to be towed behind an airborne mother ship. A drag device is secured to a distal end of the flexible tether to generate drag and maintain tension in the flexible tether. A reel associated with the mother ship anchors a proximal portion of the flexible tether and selectively lets out and takes up the flexible tether to adjust a length of the flexible tether. A capture mechanism associated with the aircraft engages the flexible tether to enable the aircraft to translate along the flexible tether. In embodiments of the present methods, a flexible tether is deployed from an airborne mother ship. An aircraft translates forward and rearward along the flexible tether. Prior to launch, the weight of the aircraft is transferred from the flexible tether to the wings. During recovery, the weight of the aircraft is transferred from the wings to the flexible tether.

Abstract: A roll steering method subdivides the direction of an aircraft control surface into two elements and, during a roll control operation using ailerons, steers an upper element of the control surface in the roll direction and a lower element in the opposite direction.

Abstract: The invention is directed to a pressure sensor device for sensing decompression in a compartment, such as an aircraft cockpit, and causing a compartment door to be free to open substantially simultaneously in response to the decompression. The pressure sensor comprises a first pressure port and a second pressure port where both pressure ports are open to the compartment, and the second pressure port has a greater flow restriction than the first pressure port, When the pressure sensor is actuated by a difference in pressure between the first pressure port and the second pressure port caused by decompression in the compartment, the pressure sensor sends a signal either via direct wired in series or to a controller to enable movement of a compartment door in response to the decompression.

Abstract: A system allowing for the controlled propulsion of aircraft, especially buoyant and semi-buoyant airships designed as a symmetric body of revolution, without the need for or use of aerodynamic control surfaces, comprised of a plurality of ducted fan thrusters placed both fore and aft, designed to ingest air flowing at less than free stream velocity. Fans are arranged such that when at standard orientation, the thrust from each is directed tangentially to an arc drawn along the hull from bow to stem. By defining multiple sets of thrusters based upon their location, differential thrust may be applied based upon set membership in order to affect translational and rotational maneuvering of the aircraft.

Abstract: The present invention discloses an apparatus for emergency landing comprising: an extraction vehicle (10), a first adjustable tower and a second adjustable tower (11), a first gearbox (4) wherein said gearbox is mounted on top of said first adjustable tower, a second gearbox wherein said second gearbox is mounted on the top of said second adjustable tower, a third gearbox wherein said third gearbox is mounted on lower right side of said chassis, a fourth gearbox unit wherein said unit is mounted on the lower left side of chassis, a first rubber restrainer (8) wrapped around said first gearbox unit and extended to said third gearbox unit wherein said rubber restrainer is wrapped around said third gearbox unit, a second rubber restrainer wrapped around said second gearbox unit and extended to said fourth gearbox unit, wherein said rubber restrainer is wrapped around said fourth gearbox unit, wherein said first and said second rubber restrainer stabilize said aircraft and reduce initial impact by said aircraft.

Abstract: Passive removal of suction air for producing a laminar flow, and associated systems and methods are disclosed. One such method includes forming a laminar flow region over an external surface of an aircraft by drawing air through the external surface and into a plenum. The method can further include passively directing the air from the plenum overboard the aircraft. For example, the air can be passively directed to a region external to the aircraft having a static pressure lower than a static pressure in the plenum, as a result of the motion of the aircraft. Flows from different sections of the external surface can be combined in a common plenum, and the corresponding massflow rates can be controlled by the local porosity of the external surface.

Abstract: An unmanned aerial vehicle mounts a payload section to an air delivery vehicle. The air delivery vehicle includes deployable wings and tail fins for gliding or powered flight. A set of propeller blades are provided for powered flight. The propeller blades are mounted for movement from a stowed position to deployed position extending radially from the fuselage for powered flight.

Abstract: Sealing system for the gap (2) between the fuselage (3) and the elevator (4) of the orientable horizontal stabiliser (5) of an aircraft, extended with an aerodynamic fairing (8) for sealing of the opening (24) between the fuselage (3) and said orientable horizontal stabiliser (5) which comprises a main body (1) and an aerodynamic fairing (8) which is extended from the main body (1) in continuity with the latter, and a plurality of first elastic sealing profiles (9) between the first surface (11) of the main body (1) including the aerodynamic fairing (8) and the outer surface of the fuselage (3) and making contact with them, and a plurality of second elastic sealing profiles (13) between the second surface (12) of the main body (1) and the first end of the elevator (15) and making contact with them, in such a way that the sealing takes place of the gap (2) and the opening (24) and an aerodynamic continuity is produced between the orientable horizontal stabiliser (5), the fuselage (3) and the elevator (4) when

Abstract: Embodiments of the present invention relate a wing arrangement for an aerial vehicle configured to adjust the vehicles aspect ratio in response to flight mission parameters. The wing arrangement may include a pair of wing assemblies capable of deploying to a first winged position defining a first aspect ratio. Each wing assembly may have a forward inboard wing pivotally connected to the fuselage and an aft inboard wing pivotally connected to the carriage. The forward inboard wing and aft inboard wing of each assembly may be connected, forming a bi-plane configuration. Additionally, the each assembly may include a set of outboard wings configured to telescope from the inboard wings to an extended winged position defining a second aspect ratio greater than the first aspect ratio.