Abstract: Nosecone and tailfin designs for aerodynamic systems are disclosed. The designs increase the usable volume within the fuselage of the aerodynamic system while still maintaining the same length for the aerodynamic system. In an example, the nosecone is truncated and includes a blunted tip compared to standard nosecone designs, which allows for more useable space along the length of the aerodynamic system. A tailfin structure is fabricated as a separate piece (separate from the fuselage of the aerodynamic system) and slips over a portion of one end of the fuselage, thus allowing useable volume within the fuselage beneath the tailfin structure. The tailfin structure also includes a hollow cavity for holding componentry (e.g., an RF transmitter, receiver, or transceiver device) with wires that feed through the tailfin structure and into the fuselage of the aerodynamic system.

Abstract: A propellant storage system that utilizes an integrated internal lattice structure within the fuel storage tank(s) to provide additional strength and anti-slosh features. The internal lattice structure lends its additional strength properties to adapt the fuel storage tank to unconventional geometries to allow for better compaction and weight savings in deployment vehicles such as satellites.

Abstract: A wing tip device having a first wing tip device element for attaching at a first wing tip device element root to a tip of an aircraft wing, and a second wing tip device element extending from a second wing tip device element root to a second wing tip device element tip, the second wing tip device element root outboard, when viewed in the wing planform direction, of the first wing tip device element root; the first wing tip device element having a first wing tip device element leading edge and a first wing tip device element trailing edge, and the second wing tip device element having a second wing tip device element leading edge and a second wing tip device element trailing edge; and a fairing between the first and second wing tip device element which extends aft from the second wing tip device element trailing edge.

Abstract: Systems for insulating a space vehicle or space borne container from an external environment as well as cryogens from heat sources. Such systems also protect the vehicle from the high dynamic pressures, the high heat loads encountered in atmospheric flight, and provide storage capability that strongly limits, or effectively eliminates, cryogenic boil-off losses once in space. Such systems include an expandable structure having a plurality of contiguously adjacent expandable layers. The layers are connected by a plurality of tension connectors between successive layers. For launch and flight the layers can be restrained in a collapsed position. Whereupon exiting a free stream environment, the layers are expanded where they can lock into place or otherwise remain in an expanded state. The expansion creates separation between the layers with minimal conduction paths providing near theoretically perfect multi-layer insulation and extremely effective debris protection.

Abstract: An aircraft with a variety of control surfaces including but not limited to multiple winglet rudders. Each winglet can have multiple independently controlled rudders to improve the flight stability and maneuverability of the aircraft. Additionally, improved power supply systems can be implemented to allow for sustained flight.

Abstract: A flow control method is a flow control method of controlling flow around a blade of a rotary wing, a plasma actuator being disposed at the blade. The flow control method includes: determining a characteristic frequency ratio that is a characteristic value among frequency ratios, each of the frequency ratios being a ratio between an actuator driving frequency and an angle of attack changing frequency, the actuator driving frequency being a frequency of an applied voltage applied to the plasma actuator, the angle of attack changing frequency being a frequency at which an angle of attack of the blade changes in accordance with a rotation angle of the blade; setting the actuator driving frequency such that the frequency ratio becomes the characteristic frequency ratio; and applying a voltage of the set actuator driving frequency to the plasma actuator to control the flow around the blade.

Abstract: A vertical-takeoff-and-landing (“VTOL”) aircraft including a non-VTOL aircraft equipped for forward takeoff and flight and a modular boom system interoperably coupled to the non-VTOL aircraft. The modular boom system includes a first modular boom and a second modular boom. The first modular boom includes a first rocket-turbine engine. The first modular boom is mounted to a first wing of the non-VTOL aircraft. The second modular boom includes a second rocket-turbine engine. The second modular boom is mounted to a second wing of the non-VTOL aircraft.

Abstract: In a passenger seating arrangement in an aircraft cabin, the passenger seating arrangement has exactly two rows of seat units and exactly one aisle. A first row of seat units and a second row of seat units are separated by the aisle. The rows of seat units and the aisle all extend in a longitudinal direction parallel to a longitudinal axis of the aircraft cabin. Each seat unit includes a seat, an upper shell and a lower shell, the lower shell forming a footwell. The seats are arranged in parallel to each other in a seating direction. An upper shell of a first seat unit and a lower shell of a second seat unit, which, viewed in the longitudinal direction, is arranged behind the first seat unit, partially overlap in a vertical direction.

Abstract: An aircraft with an aircraft structure that comprises a radome cover opening kinematic and a radome cover shell that is adapted to enclose equipment in a nose region of the aircraft in a closed position. The radome cover opening kinematic may enable movements of the radome cover shell between the closed position and an opened position and vice versa. The radome cover opening kinematic may include a guiding rail that is attached to the radome cover shell, and at least three rollers that are attached to the aircraft structure, wherein a first and a second roller are arranged on opposing sides of the guiding rail, and wherein the second and a third roller are arranged on the same side of the guiding rail. The radome shell opening kinematic further comprises a radome cover shell rotation stopper that can stop movement of the radome cover shell at the completely opened position.

Abstract: Improved seating arrangements for a vehicle cabin of a passenger transport system, in particular of an aircraft are disclosed. Examples herein provide improved seating arrangements providing a high density of seats and increased PAX numbers while ensuring privacy, comfort and a direct aisle access to each passenger. For example, the seating arrangements provided herein are applicable to narrow body aircrafts and wide body aircrafts, in particular in view of business class solutions.

Abstract: An aircraft seat including: a seat chassis; a seat assembly including a seat pan and a seat back; the seat pan being mounted to the seat chassis by a first pivoting connection defining a seat pan pivot axis about which the seat pan pivots, the first pivoting connection being configured such that the seat pan can pivot about the seat pan pivot axis without undergoing a related translational movement; the second pivoting connection defining a seat back pivot axis about which the seat back pivots; at least one seat pan link for controlling pivoting of the seat pan about said seat pan pivot axis; wherein the at least one seat pan link is coupled to the seat pan in front of the seat pan pivot axis; and at least one recline link connected to the seat back and the at least one seat pan link.

Abstract: A separation device for a spacecraft or launcher comprising a nut divided into at least two nut portions locked to each other by a locking device in a locking position. A releasing device is arranged to switch the locking device from the locking position to a releasing position. The separation device comprises at least two bearing elements arranged between the locking device and the nut. The nut comprises an outer envelope surface which comprises as many indentations as the number of bearing elements and locking surfaces between the indentations. In the locked state each bearing element is jammed between the locking surface and an inner envelope surface of the locking device and in the released state each bearing element is positioned facing the indentations.

Abstract: A wing for an aircraft includes a first end, a second end, and a skin extending longitudinally from the first end to the second end. The wing also includes at least one channel positioned within the skin and extending longitudinally between the first and second ends. The at least one channel defines a longitudinal translation path for translating at least one electrical power source longitudinally between the first and second ends.

Abstract: A modular flying car includes a ground vehicle and a flight vehicle. The ground vehicle includes a chassis, a first cabin and a landing platform for landing the flight vehicle. The flight vehicle includes a second cabin and a flight driving device. The flight vehicle is capable of landing and taking off vertically on the landing platform and connected with the ground vehicle by interlocking. Users can choose to travel by the ground vehicle or the flight vehicle, and can transfer between the ground vehicle and the flight vehicle, to solve the traffic jam problem and make the realization of the flying car more feasible. A flying car system and a flying car sharing method are also disclosed.

Abstract: An aircraft with an aircraft structure that comprises a radome cover opening kinematic and a radome cover shell that is adapted to enclose equipment in a nose region of the aircraft in a closed position. The radome cover opening kinematic may enable movements of the radome cover shell between the closed position and an opened position and vice versa. The radome cover opening kinematic may include a guiding rail that is attached to the radome cover shell, and at least three rollers that are attached to the aircraft structure, wherein a first and a second roller are arranged on opposing sides of the guiding rail, and wherein the second and a third roller are arranged on the same side of the guiding rail.

Abstract: A modular hunting blind with individual components configured to be stored in the base with the top and roof serving as a container top to store and ship the modular hunting blind. The components may be readily assembled on site for placement on the ground or on a stand or platform with minimal tools.

Abstract: An anti-recoil assembly may include a housing, a shaft, and an energy attenuator. The housing generally defines a cavity, with the housing having a first end portion and a second end portion, according to various embodiments. The shaft may be at least partially disposed within the cavity, and the shaft may be configured to move within the cavity in a first direction from the first end portion to the second end portion. In various embodiments, the energy attenuator is disposed within the cavity at the second end portion. In response to movement of the shaft in the first direction, the energy attenuator is configured to inhibit the shaft from recoiling in a second direction opposite the first direction, according to various embodiments.

Abstract: An aircraft seat for an aircraft passenger compartment suite may include a primary section with an upper actuatable portion and a lower actuatable portion. The primary section may be configured to actuate between a primary upright position and a primary lie-flat position. The aircraft seat may include an auxiliary section including an auxiliary seatback portion coupled to a privacy shell element of the aircraft passenger compartment suite and an auxiliary seat base portion configured to actuate between an auxiliary upright position and an auxiliary lie-flat position. The auxiliary seatback portion may include an actuatable element. The actuatable element may be configured to actuate between an open position and a closed position. The actuatable element may be configured to provide access to a stowage compartment when the actuatable element is in the open position.

Abstract: A removable passive airflow oscillation device can be disposed within a pressurized wing structure utilized as a plenum. The passive airflow oscillation device can be a removable insert disposed into exterior vehicle surfaces with pressurization of a sealed chamber to provide the airflow. The device can include a cavity configured to receive the airflow from an ingress opening, direct the airflow therethrough to generate a predetermined oscillating airflow, and expel the oscillatory airflow from the egress opening. The removable passive airflow oscillation devices can provide quick and simple replacement and maintenance of damaged or clogged devices. The aft chamber of the flap seal can be sealed and pressurized to serve as a plenum providing the airflow to the actuators. The device can receive airflow, such as compressor air, and expel an oscillating airflow. Because each device is self-contained the number of devices and location thereof can vary by application.

Abstract: A flap support mechanism includes a track rotatably connected to an aft fitting of a wing. A forward roller and an aft roller extend laterally from a flap structure, the forward roller and aft roller constrained in a slot in the track. The slot has a profile configured to induce both translation and rotation in the flap, in concert with rotation of the track about the aft fitting, thereby passively mirroring motion of the flap induced by an actuator driven primary main flap support.