Abstract: A propeller assembly including a shaft having a rotational axis; a plurality of propellers connected to the shaft; means for deploying the plurality of propellers using a centrifugal force generated from a rotation of the shaft, so as to provide vertical thrust during a vertical take-off and landing of the aircraft; and means for restoring the propellers into a stowed configuration.

Abstract: A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.

Abstract: A flow body for an aircraft includes a torsion box with spars and/or ribs and at least two skin portions for enveloping the spars and/or ribs, wherein at least one inner cell is formed in the torsion box. It is provided that a gas tank with a gas tank shell is arranged in the at least one inner cell, and that the gas tank includes fastening elements coupled to retaining elements in the relevant inner cell in order to hold the gas tank such that the gas tank shell is supported at a distance from the spars and/or ribs and the skin portions and is supported in three spatial directions.

Abstract: Fuel used as a coolant in an aircraft can be thermally conditioned for active thermal management of the airframe and engine. The fuel can be thermally conditioned using the residual cooling capacity of a power and thermal module (PTM), providing flexibility of thermal system design, or via a compact engine-mounted turbo cooler, to maximize system efficiency. The fuel can be stored in a thermal reserve tank to provide a missionized heat sink capable serviceable for periodic high heat flux equipment. The cooling and provision of cooled fuel to aircraft components can be intelligently controlled to provide efficient cooling and effectively unlimited ground hold times.

Abstract: A spacecraft sunshade is provided. The sunshade includes a surface that is maintained in a sun facing orientation. Adjustments to a position of the sunshade are made in a plane that is transverse to a line of sight to the sun, in order to block sunlight from being directly incident on an instrument associated with the spacecraft. The sunshade can include photovoltaic elements on the sun-facing surface of the sunshade. In addition, the sunshade can be formed from an opaque material, and further from a material that absorbs heat from the sun and reradiate that heat to the instrument. The sunshade can perform stray light blocking, electrical power generation, and radiational heating functions.

Abstract: Coupler assemblies are described that removably couple sides of an auxiliary fuel tank in a cargo area of an aircraft. In one embodiment, a first coupler of the coupler assemblies includes a first attachment member that supports a body with a hollow channel having a centerline disposed longitudinally in the fuselage between a first end and a second end, and a slot between an outer surface of the body and the hollow channel. A second coupler of the coupler assemblies includes an engagement member, a second attachment member, and an arm extending between the engagement member and the second attachment member. The engagement member is slidably received within the hollow channel from the first end, and fits slidably within the hollow channel to engage with the body of the first coupler, with the arm extending through the slot.

Abstract: This fuel tank dam closes a gap between a first structural component fixed to the inside surface of the outer plate of a fuel tank and a second structural component provided with a cutout part into which the first structural component is inserted. This fuel tank dam includes: a first portion that can be fixed to the first structural component; a second portion that has a surface extending in a direction intersecting with the first portion and can be fixed to the second structural component; and a third portion that has a bellows and is disposed between the first portion and the second portion. This fuel tank dam is configured such that the first portion, the second portion, and the third portion are integrated, the bellows has a thickness of 0.381 to 1.524 mm, and the second portion has a thickness of 0.762 to 7.620 mm.

Abstract: An aircraft usable as a passenger aircraft and a fire fighter aircraft. The passenger aircraft includes a passenger area with passenger seats and a permanently installed fire extinguishing medium tank for storing fire extinguishing medium such as water, as well as a fire extinguishing medium nozzle for discharging the fire extinguishing medium. The passenger aircraft may be a type from an aircraft series also including a long-haul aircraft having a center tank for range extension. In the passenger aircraft, a center tank may be used as an extinguishing medium tank.

Abstract: Assemblies and methods for facilitating the assembly of aircraft wings to a fuselage are disclosed. In some embodiments, a wing unit includes features that are configured to define one of more parts of a pressure vessel that is partially defined by the fuselage portion. In some embodiments, the aircraft assemblies disclosed herein comprise one or more first structural interfaces that permit positional adjustment between the wing unit and the fuselage portion so that one or more second structural interfaces may be finished only after such positional adjustment. In some embodiments, the aircraft assemblies disclosed herein comprise one or more structural interfaces that are disposed outside of the wing unit in order to eliminate or reduce the need for assembly personnel to access the interior of the wing unit to carry out the structural assembly of the wing unit to the fuselage portion.

Abstract: Hybrid multirotor vehicles and related methods are disclosed herein. An example aircraft includes a battery, a rotor coupled to a wing, a motor operatively coupled to the rotor, and a processor operatively coupled to the motor. The processor to is cause the motor to operate in a first motor operational state. The rotor is to operate in a first rotor operational state when the motor is operating in the first motor operational state. The processor is to cause the motor to switch from operating in the first motor operational state to a second motor operational state. The rotor is to operate in a second rotor operational state when the motor is in the second motor operational state. The motor is to provide electrical energy to the battery in the second motor operational state and the rotor is to autorotate in the second rotor operational state.

Abstract: One variation of a system for generating thrust at an aerial vehicle includes: a primary electric motor; a rotor coupled to the motor; an internal-combustion engine; a clutch interposed between the motor and an output shaft of the internal-combustion engine; an engine shroud defining a shroud inlet between the rotor and the internal-combustion engine, extending over the internal-combustion engine, and defining a shroud outlet opposite the rotor; a cooling fan coupled and configured to displace air through the engine shroud; and a local controller configured to receive a rotor speed command specifying a target rotor speed, adjust a throttle setpoint of the internal-combustion engine according to the target rotor speed and a state of charge of a battery in the aerial vehicle, and drive the primary electric motor to selectively output torque to the rotor and to regeneratively brake the rotor according to the target rotor speed.

Abstract: An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.

Abstract: Spring-integrated rotors are disclosed. A disclosed example apparatus includes a bracket defining a first rotational axis and coupled to a motor for rotating the bracket about the first rotational axis, a pivot body defining a second rotational axis extending along a direction different than the first rotational axis, the pivot body coupled to the bracket for rotation about the second rotational axis, and at least one spring device positioned at the bracket, the at least one spring device urging the pivot body toward a central position when the bracket is rotating.

Abstract: An acoustic system for an Urban Air Mobility (UAM) vehicle may comprise a first shield configured to be disposed around a rotor of the UAM vehicle, the first shield having an annular shape, the first shield configured to be disposed radially outward from a blade tip of a rotary blade, the first shield configured to redirect sound waves from a substantially radial direction to a second direction, the second direction being orthogonal to the radial direction.

Abstract: A floor mounted aircraft seat seal frame includes a frame, displacing elements connecting the frame to the posterior of the seat, and fabric tensioning elements that keep a gap covering fabric connected to the posterior surface of the seat in tension around the frame. The frame displacing elements, which may be leaf springs, coil springs, or manually adjustable element, allow the frame to conform to a wall behind the seat, regardless of the tapering of the wall.

Abstract: A landing gear door system, including a landing gear bay including an opening and accommodating a landing gear in a retracted position, a landing gear door for opening and closing the opening, an actuator for operating the landing gear door between an open and a closed position, a lock located in the landing gear bay and latching the landing gear door in the closed position, a stop fitting located in the landing gear bay and configured to be in connection with the landing gear door at least in its latched position. The landing gear door system further includes an additional actuator configured to apply a force to the landing gear door in its closed position and to elastically deform the landing gear door towards the landing gear door bay.

Abstract: A compound helicopter includes a fuselage, a fixed wing, a rotary wing, and a barrier member. The fixed wing is fixed to the fuselage. The rotary wing is rotatably coupled to the fuselage. The barrier member is attached to a part, of the fuselage, that is above the fixed wing and is between the rotary wing and the fixed wing. The barrier member is configured to generate no lift upon forward flight.

Abstract: A vertical takeoff and landing aircraft system includes a gas turbine engine coupled to a variable pitch propeller. The gas turbine engine is also coupled to a power split device including a first motor generator, a second motor generator, and a planetary module therebetween. The planetary module includes a sun gear, a ring gear, and a planet carrier. The motor generators are coupled to inverters, a DC bus and a battery. The battery is configured to power balance fans disposed on wings and horizontal stabilizers of the aircraft system. The balance fans can be closed off after vertical lift has been achieved.

Abstract: Embodiments are directed to systems and methods for deploying an outboard rotor blade of proprotor pylon to act as an extended lifting surface. Blade control actuators may provide primary rotor flight control as well as providing fold linkage actuation when fold locks are disengaged. During cruise flight, the blade control actuator may provide feathering inputs to the extended rotor blade, wherein the amplitude and frequency of feathering inputs are tuned to mitigate undesirable wing and fuselage dynamic modes thereby enhancing aircraft stability. The deployed rotor blades also improve the total lifting area of the aircraft, which may increase aircraft range and efficiency.

Abstract: An orientation assembly includes a platform and a locking assembly engageable with the platform and positionable in a first state in which the platform is permitted to rotate about a lateral axis and inhibited from rotating about a longitudinal axis perpendicular to the lateral axis, and a second state in which the platform is permitted to rotate about the longitudinal axis and inhibited from rotating about the lateral axis.