Abstract: The invention relates to a separation system that dispenses a satellite from a launch vehicle along a dispensing axis, with a first ring for mounting to the launch vehicle and a second ring for mounting to the satellite and a deployment means exerting a separating force on the first and the second ring.

Abstract: An air vehicle is provided including: a main lift generating wing arrangement having a port wing and a starboard wing, empennage and main propulsion system. The air vehicle further includes a distributed electrical propulsion (DEP) system having secondary electrical propulsion units coupled to each one of the port wing and the starboard wing. The main propulsion system is configured for providing sufficient thrust such as to enable powered aerodynamic flight of the air vehicle including at least: powered aerodynamic take off absent operation of the DEP system; and powered aerodynamic landing absent operation of the DEP system. The DEP system is configured for selectively providing at least augmented lift to the main lift generating wing arrangement in at least landing. A method for landing an air vehicle on a moving platform under separated wake conditions is also provided.

Abstract: A method of operating an electrically powered rotorcraft of the type having a fuselage and a set of N rotors driven by a set of electric motors and coupled to the fuselage, N?4, under a failure condition preventing ordinary operation of the rotorcraft. The method includes entering a failsafe mode of operation wherein autorotation of at least four of the rotors is enabled. The method also includes using electrical braking associated with a selected group of the rotors to control pitch, roll and yaw of the rotorcraft.

Abstract: A linear electromechanical servocontrol comprising a power rod that is able to move in translation. The servocontrol comprises a single linear electrical actuator provided with at least one electric motor connected by a mechanical link to the power rod, the servocontrol comprising an anchor secured to the electrical actuator, the at least one electric motor being controlled by a computer, the anchor having an anchoring rod that is able to move in translation, the anchor having an anchoring brake that is configured to immobilize the anchoring rod with respect to the electrical actuator in a normal operating mode or to allow the electrical actuator to move in relation to the anchoring rod in a safe operating mode at the request of the computer.

Abstract: In an air mobility vehicle, an engine operates as required to provide mechanical driving force or electric energy. A battery is charged with the electric energy from the engine. Main rotors operate using the electric energy of the battery and electric power generated by the engine to perform takeoff, landing, and cruising. Auxiliary rotors are disposed at or adjacent to the center of gravity of a vehicle body and mechanically connected to the engine via a clutch. The auxiliary rotors perform the takeoff, the landing, or the cruising by receiving the mechanical driving force from the engine when the clutch is in an engaged position. A controller monitors the states of the battery and the main rotors and controls the operations of the engine and the clutch.

Abstract: An aircraft can include a wing. The wing can include a tip. A winglet can be pivotably connected to the wing proximate the tip. A connecting member can be operatively connected to the wing and the winglet. The connecting member can include a flexible material with a super elastic material member operatively connected to the flexible material. Thus, the connecting member can allow passive movement of the winglet responsive to real-time operational forces acting upon the aircraft. In some arrangements, the flexible material can be a fabric, and the super elastic material member can be a wire. In some arrangements, the super elastic material member can be configured to exhibit a non-linear stiffness profile. The non-linear stiffness profile can include a region of quasi-zero stiffness. The stiffness profile of the super elastic material member can be selectively varied, such as by controlling a temperature of the super elastic material member.

Abstract: According to the present invention there is provided a method of taking a measurement using a sensor mounted on an aerial vehicle, the aerial vehicle having one or more propellers and one or more motors which are selectively operable to drive the one or more propellers to rotate to cause the vehicle to fly, and a sensor mounted on the aerial vehicle, the method comprising the steps of, operating the one or more motors to drive the one or more propellers to cause the vehicle to fly; at a first time instant, slowing down or turning off said one or more motors; while the one or more motors are slowed down or turned off, taking a measurement using said sensor; at a second time instant, which is after the measurement has been taken using the sensor, operating the one or more motors again to drive the one or more propellers to cause the vehicle to fly. There is further provided a corresponding aerial vehicle.

Abstract: A propulsive assembly, in particular for an aircraft, comprising a mast and a propulsion device comprising an engine and a nacelle, the engine comprising a propeller, the propulsive assembly comprising: A standby protection device comprising a first connecting member fixedly mounted to the mast and a second connecting member fixedly mounted to the propulsion device, the second connecting member being rotatably hinged with respect to the first connecting member in at least one degree of freedom, and at least one retaining member keeping the second connecting member fixed with respect to the first connecting member, and configured, in the presence of a predetermined unbalance force on the propeller, to release the standby protection device in order to protect the mast.

Abstract: A cabin module for an aircraft comprises a section which has an upward-facing surface in an installed state of the cabin module, wherein the upward-facing surface of the section comprises an integrated drainage channel. An aircraft furthermore comprises at least one such cabin module.

Abstract: Aircraft systems including a pressurized fuel tank containing a pressurized fuel, a turbo expander configured to receive the pressurized fuel from the fuel tank, the turbo expander configured to decrease a pressure of the pressurized fuel to generate low pressure fuel having pressure less than the pressurized fuel, a fuel-to-air heat exchanger configured to receive the low pressure fuel from the turbo expander as a first working fluid and air as a second working fluid, the heat exchanger configured to cool the air and warm the fuel, an aircraft cabin configured to receive the cooled air, and a fuel consumption system configured to consume the fuel to generate power.

Abstract: In an air mobility vehicle, an engine operates as required to provide mechanical driving force or electric energy. A battery is charged with the electric energy from the engine. Main rotors operate using the electric energy of the battery and electric power generated by the engine to perform takeoff, landing, and cruising. Auxiliary rotors are disposed at or adjacent to the center of gravity of a vehicle body and mechanically connected to the engine via a clutch. The auxiliary rotors perform the takeoff, the landing, or the cruising by receiving the mechanical driving force from the engine when the clutch is in an engaged position. A controller monitors the states of the battery and the main rotors and controls the operations of the engine and the clutch.

Abstract: A roller unit for moving a slat of an aircraft wing is provided. The roller unit is adjustable in height and axial position to adjust a gap between an idle roller and a guide rail integral with the slat. The idle roller is carried by an eccentric pin having a stem portion with a threaded portion and an axially grooved end portion. A threaded annular element cooperates with the threaded portion of the stem portion to define a desired axial position of the idle roller. An anti-rotation annular element, coupled in an axially slidable manner with the grooved end portion of the stem portion, may be coupled with the threaded annular element to prevent rotation thereof on the threaded portion of the stem portion. The threaded annular element and the anti-rotation annular element are tightened together between a pair of nuts.

Abstract: A system for automatic optimization of an ejection system for an aircraft includes the ejection system having a plurality of adjustable settings. The system further includes an input device configured to receive user input. The system further includes a controller coupled to the ejection system and to the input device and configured to adjust at least one of the plurality of the adjustable settings of the ejection system based on the user input.

Abstract: A simple-hinged flap assembly for a winged aircraft includes a simple-hinged flap having a leading airfoil section pivotably connected to a trailing airfoil section via a hinge, and an active flow control (AFC) actuator assembly. The assembly is connected to or integrally formed with the flap and includes upstream and downstream AFC actuators arranged in respective first and second rows, and collectively configured to provide first and second outlet mass flowrates. The downstream AFC actuators emit the second outlet mass flowrate at a rate that substantially exceeds the first outlet mass flowrate, such that the first outlet mass flowrate preconditions a boundary layer around the simple-hinged flap assembly. A winged aircraft includes a pneumatic power supply, fuselage, a wing connected to the fuselage, and the simple-hinged flap assembly.

Abstract: A parking tail rotor for a rotary wing aircraft stops rotating at a high forward aircraft speed when aircraft control surfaces have adequate control authority to balance main rotor torque without the rotating tail rotor. When stopped, the blades of the parking tail rotor move due to the force of the relative wind to a parked position in which the span of the blades extend in the aft direction, reducing air resistance to the forward motion of the aircraft.

Abstract: A floor system designed for use with an aircraft is provided. The aircraft comprises a cabin characterized by a first capacity defined by the number of personnel in a predetermined position which may be accommodated therein, and comprises an auxiliary fuel port. The floor system is configured to be detachably installed within the cabin and comprises one or more top panels constituting, when the floor system is installed in the aircraft, a floor of the cabin, and one or more fuel tanks disposed below the top panels and defining an internal space for containing liquid fuel there within. At least one of the fuel tanks is configured for connection to the auxiliary fuel port for supplying the fuel to the aircraft. The cabin with the floor system installed therein is characterized by a second capacity being equal to the first capacity.

Abstract: An aircraft cabin includes at least one seat able to receive at least one passenger; at least one table arranged opposite the seat; and a safety device able to be mounted on the table, below the table or received in the table. The safety device includes a deployable protection assembly including an airbag deployable from a retracted idle configuration to a deployed safety configuration, and a system for controlling the deployment of the or each airbag, able to trigger the deployment of the airbag beyond a threshold deceleration value of the aircraft.

Abstract: Reactive spoilers for aircraft and associated methods. In one embodiment, a wing of an aircraft includes a leading edge, a trailing edge, and an upper surface and a lower surface between the leading edge and the trailing edge. The wing further includes a reactive spoiler disposed on the upper surface between the leading edge and the trailing edge. The reactive spoiler comprises one or more turbines configured to raise in relation to the upper surface into an airflow passing over the upper surface, and to reduce lift of a wing section behind the turbines. The turbines are configured to convert kinetic energy from the airflow into electrical energy.

Abstract: An aircraft equipped with a distributed fan propulsion system and methods of operating such aircraft are provided. In one aspect, an aircraft includes a wing having a top surface and a bottom surface. The aircraft also has a distributed propulsion system that includes a suction fan array having one or more fans mounted to the wing and a pressure fan array having one or more fans mounted to the wing. The fans of the suction fan array are each positioned primarily above the top surface of the wing and the fans of the pressure fan array are each positioned primarily below the bottom surface of the wing. The fans of the suction fan array are controllable independent of the fans of the pressure fan array so that the air pressure above and/or below the wing can be locally controlled, allowing for adjustment of lift on the wing.

Abstract: A method of controlling a multi-engine aircraft includes receiving input for commanded thrust and modifying the commanded thrust using a model of an incumbent powerplant to generate a modified commanded thrust for matching aircraft performance with a new powerplant to the aircraft performance with the incumbent powerplant. The method includes applying the modified commanded thrust to the new powerplant.