Abstract: A selectively rigidizable membrane for cargo management comprises a vacuum bladder, and a first architectural layer and a second architectural layer, each of the first and second architectural layers including a plurality of tiles interconnected by flexural elements, each of the tiles of the first and second architectural layers including at least one constraining element extending therefrom, wherein, when atmospheric pressure is present within the vacuum bladder, the first and second architectural layers are slidably moveable relative to one another and the membrane is flexible, and further wherein, when negative pressure is applied to the vacuum bladder, the first and second architectural layers are forced into engagement with one another, the constraining elements of the first and second architectural layers providing mechanical interference and preventing sliding movement of the first and second architectural layers relative to one another, causing the membrane to become substantially rigid.

Abstract: The disclosure relates to an airfoil body for an aircraft extending from an inner end to an outer end, and between a leading edge and a trailing edge. The airfoil body comprises an internal structure and a skin covering the internal structure. The skin has a pressure side and a suction side, and the suction side includes a light transmitting portion. The internal structure includes an array of solar cells configured to receive solar light through the light transmitting portion. The present disclosure further relates to wings and aerial vehicles.

Abstract: A structure adapted to traverse a fluid environment exerting an ambient fluid pressure is provided. The structure includes an elongate body extending from a root to a wingtip and encapsulating at least one interior volume containing an interior fluid exerting an interior fluid pressure that is different from the ambient fluid pressure. A method of retrofitting a structure adapted to traverse a fluid environment exerting an ambient fluid pressure, the structure comprising an elongate body extending from a root to a wingtip and having at least one interior volume is also provided. The method includes sealing the elongate body to encapsulate the at least one interior volume containing an interior fluid; associating at least one valve with the at least one interior volume; and modifying interior fluid content via the at least one valve to produce an interior fluid pressure that is different from the ambient fluid pressure.

Abstract: A fluidfoil includes a selectively fluid chargeable capillary and a flexible body adjacent the capillary, the shape of the flexible body being adjustable in use via controlling the degree to which the capillary is charged and therefore the forces that the capillary exerts on the flexible body.

Abstract: An apparatus for deceleration of a body may include a plurality of inflatable portions. The plurality of inflatable portions may be coupled together such that, when inflated, the plurality of inflatable portions defines a deceleration structure configured to decelerate the body. Each inflatable portion may include a first wall element, a second wall element opposite the first wall element, and a plurality of stitch members extending between and coupled to each of the first wall element and the second wall element.

Abstract: A solar power assembly is provided. The assembly includes means for nonplanar generation of solar power, wherein the solar power comprises sunlight converted into electrical energy; means for transmission of the solar power to a means for storage of electrical energy in a vehicle; and means for attachment of the means for nonplanar generation of solar power to a sunlight-exposed surface the vehicle. The assembly is capable of capturing sunlight from multiple angles and producing solar power for the vehicle's use.

Abstract: The invention relates to a method for producing a fiber composite workpiece. In the method according to the invention, cross-linking silicone is used with the aid of a volatile diluent for infiltrating individual mats of a mat composite. A further object of the present invention is a device for performing the method according to the invention.

Abstract: A method and apparatus for deploying an aircraft. An inflation system is activated to generate a gas. A fuselage of the aircraft is inflated with the gas. The fuselage comprises a frame for the aircraft and a number of flexible layers associated with the frame in which the number of flexible layers are configured to define a volume for at least a portion of the aircraft when the number of flexible layers are in an inflated configuration.

Abstract: Methods and apparatus for an adaptable solar airframe are provided herein. In some embodiments, an adaptable solar airframe includes a solar PV system having at least one solar tracking system and being able to follow the sun position in order to increase sunlight collection and power output; and an expandable body having an aerodynamic cross-section that minimizes parasitic air drag at any given thickness of the body, further being at least partially transparent to sunlight, further enclosing the solar PV system, and further being able to change its shape in response to changes in the positions of the solar PV system.

Abstract: A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

Abstract: A wing includes a spar, and a pair of flexible skins that are attached to the spar. The spar is at the leading edge of the wing, and the skins extend toward the trailing edge of the wing. The wing deploys from a stowed condition, in which the skins are curved in the same direction around a fuselage of an aircraft, to a deployed condition, in which the skins provide the wing with an airfoil cross-sectional shape, for example with the skins curve in opposite direction. A lock is used to maintain the skins in the deployed state, with the lock for example located at the trailing edge of the wing. The lock may be a mechanical mechanism that automatically locks the wing in the deployed state, preventing the wing from returning to the stowed state.

Abstract: A foldable wing for use with a very high altitude aircraft capable of operating at an altitude at or above 85,000 feet is disclosed. The foldable wing may employ a spiral fold deployment, wherein a hinge between each segment of the foldable wing is slightly offset from the perpendicular. Successively positioned wing segments fold over one another. Alternatively, the hinges are substantially perpendicular so that each respective wing segment folds linearly against the next wing segment. An inflatable rib, with inflatable arms, can be inflated to provide a force against two adjacent arms, thereby deploying the wing segments through a full 180° of rotation.

Abstract: A reinforced inflatable structure includes an inflatable member having a longitudinal axis. The member includes a bladder and a braided restraint layer mounted to the bladder. A plurality of spaced supports is mounted on the member and extends outwardly therefrom. A plurality of spaced bracing cables are connected at each end to a respective one of the plurality of supports. The cables are oriented generally parallel to the longitudinal axis of the member and are held at a generally fixed distance from the member by the supports. The inflatable member tensions the bracing cables rendering them capable of resisting bending.

Abstract: An apparatus may comprise an inflatable control surface for an aircraft and an end of the inflatable control surface configured for attachment to a fuselage of the aircraft. The end of the inflatable control surface may be configured to be rotated about an axis to control movement of the aircraft during flight.

Abstract: A foldable wing for use with a very high altitude aircraft capable of operating at an altitude at or above 85,000 feet is disclosed. The foldable wing may employ a spiral fold deployment, wherein a hinge between each segment of the foldable wing is slightly offset from the perpendicular. Successively positioned wing segments fold over one another. Alternatively, the hinges are substantially perpendicular so that each respective wing segment folds linearly against the next wing segment. An inflatable rib, with inflatable arms, can be inflated to provide a force against two adjacent arms, thereby deploying the wing segments through a full 180° of rotation.

Abstract: A method and apparatus for an adaptive aerostructure is presented that relies on certified aerospace materials and can therefore be applied in conventional passenger aircraft. This structure consists of a honeycomb material which cells extend over a significant length perpendicular to the plane of the cells. Each of the cells contains an inelastic pouch (or bladder) that forms a circular tube when the cell forms a perfect hexagon. By changing the cell differential pressure (CDP) the stiffness of the honeycomb can be altered. Using an external force or the elastic force within the honeycomb material, the honeycomb can be deformed such that the cells deviate from their perfect-hexagonal shape. It can be shown that by increasing the CDP, the structure eventually returns to a perfect hexagon. By doing so, a fully embedded pneumatic actuator is created that can perform work and substitute conventional low-bandwidth flight control actuators.

Abstract: A detachable inflation system for use with an air vehicle having at least one inflatable structure. The detachable inflation system comprises a pallet structure. The detachable inflation system further comprises an initial inflation system, attached to the pallet structure, that provides one or more compressed fluids. The initial inflation system is connected to an inflation distribution system in the air vehicle for distributing the one or more compressed fluids into the inflatable structure to inflate the inflatable structure. The detachable inflation system further comprises a detachable parachute.

Abstract: An apparatus may comprise an inflatable control surface for an aircraft and an end of the inflatable control surface configured for attachment to a fuselage of the aircraft. The end of the inflatable control surface may be configured to be rotated about an axis to control movement of the aircraft during flight.

Abstract: The present invention provides novel inflatable and rigidizable support elements, and methods of manufacture and use thereof. In particular, the present invention provides inflatable and rigidizable support elements which find use in rapidly deploying and supporting the wing of an aerial vehicle.

Abstract: Apparatus and methods provide for the use of retractable aircraft wing tips to increase the wingspan of an aircraft to decrease drag and increase fuel efficiency. According to various embodiments, a flexible lifting envelope is attached to an outboard end of an aircraft wing. Upon receiving pressurized air, the flexible lifting envelope extends outward to a lift-producing configuration that extends the span of the aircraft wing to which it is attached. When deflated, the flexible lifting envelope retracts into a stowed configuration to decrease the wingspan of the aircraft to allow for parking at airport gates or to alleviate flight loads. Various implementations provide for a telescoping wing tip and for a rolled wing tip.

Abstract: A multi-celled ram-air parachute possessing one or more internal one-way valved air passages between at least two parachute cells to maintain positive air pressure within the parachute for the purpose of maintaining shape and rigidity when less than optimal airspeed is present thereby increasing a user's control and safety.

Abstract: An inflatable structure is augmented with transverse frames and bracing cables to make a truss-like structure. This feature is adaptable for adding strength to a plain inflatable structure and to an inflatable structure forming a structural arch. It can also be incorporated into an inflatable wing.

Abstract: The invention relates to a curved pneumatic support comprising an inflatable sleeve which has a web that traverses said sleeve along its length under operating pressure, said web comprising in turn a pressure member and a tension member. The curvature of the support is predefined by the application and is generated as a function of the model of the sleeve and the web.

Abstract: An aircraft comprising an elongated framework provided with propelling means and direction-control planes. The framework is coupled to a pneumatic chamber suited to be filled with lighter-than-air gas and comprising two tubular branches joined to form a V-shaped profile, with an aerodinamic-lift surface extending therebetween.

Abstract: A reinforced inflatable wing improves the tolerance of the OML and reinforces the wing in at least the high load areas. This approach provides fitment constrained air vehicles with wings having increased surface area to improve flight endurance or aerodynamic control. A wing box forms a first portion of the wing. A skin having a plurality of rigid plates affixed thereto is inflated to form a second portion of the wing to either increase the chord length or lengthen the wing span. The skin is suitably inflated with foam to form a solid wing.

Abstract: A flight control system for an airfoil comprises a control surface, a chamber connecting the control surface to the airfoil, and a pneumatic mechanism fluidly connected to the chamber. The chamber may be comprised of at least two cells that may be fluidly separated by a membrane. The pneumatic mechanism is configured to provide differential pressure to the cells in order to alternately increase volume/pressure of the cells to cause deflection of the control surface. The cells may have a stretchable outer surface to allow for changes in the length of the outer surface in response to inflation/deflation of the cells. The outer surface of the cells may be substantially continuous with outer mold lines of the airfoil and of the control surface.

Abstract: Disclosed is a telescoping wing locking system for use in aircraft having wings that collapse and expand in a telescoping fashion, such as aircraft designed for use on roadways. Companion wing segments are locked in place when gas is supplied to inflate a bladder located between overlapping sections of the wing segments. Wing segments are unlocked when gas is removed from the bladder so that it deflates and allows the wing segments to be moved relative to each other. The wing segments may be locked in any position relative to each other in which a section of one segment overlaps a section of the neighboring segment with the bladder between.

Abstract: An airfoil wing system for releasing air from an airfoil wing for an inflatable airfoil is provided. The airfoil wing is secured to the inflatable airfoil. The airfoil wing system comprises at least two wing panels connected together and an opening formed between the two wing panels wherein the opening automatically moves from a closed position to an open position to release air from beneath the airfoil wing thereby allowing takedown of the inflatable airfoil.

Abstract: A reinforced inflatable wing improves the tolerance of the OML and reinforces the wing in at least the high load areas. This approach provides fitment constrained air vehicles with wings having increased surface area to improve flight endurance or aerodynamic control. A wing box forms a first portion of the wing. A skin having a plurality of rigid plates affixed thereto is inflated to form a second portion of the wing to either increase the chord length or lengthen the wing span. The skin is suitably inflated with foam to form a solid wing.

Abstract: A foldable wing for use with a very high altitude aircraft capable of operating at an altitude at or above 85,000 feet is disclosed. The foldable wing may employ a spiral fold deployment, wherein a hinge between each segment of the foldable wing is slightly offset from the perpendicular. Successively positioned wing segments fold over one another. Alternatively, the hinges are substantially perpendicular so that each respective wing segment folds linearly against the next wing segment. An inflatable rib, with inflatable arms, can be inflated to provide a force against two adjacent arms, thereby deploying the wing segments through a full 180° of rotation.

Abstract: An airbeam is augmented with transverse frames and bracing cables to make a truss-like structure. This feature is adaptable for adding strength to a plain airbeam and to an airbeam forming a structural arch. It can also be incorporated into an inflatable wing.

Abstract: The high-altitude balloon has a skin made of nearly evacuated electrostatically inflated cells which provide thermal insulation to minimize heat loss from the gas in the balloon, while transmitting heat from the sun to heat the gas. The lower surface of the balloon is reflective to microwave or laser beams. A stable array of the balloons is maintained at a high altitude and is used to facilitate communications in a world-wide communications system. Ascent of the balloon is well controlled and weight is minimized by starting with lighter-than-air gases in liquid form, releasing a lifting gas into the craft, and then using the empty containers to store the remaining gas when the balloon is aloft.

Abstract: An inflatable endurance unmanned vehicle includes an inflatable hull with at least one inflatable wing extending therefrom. The inflatable wing has at least one spar movable between an extended position and a retracted position. Photovoltaic arrays are used to power the vehicle during daytime operation and power an electrolyzer. A fuel cell powers the vehicle during nighttime operation.

Abstract: An inflatable structure constructed of flexible material that can occupy a minimal volume when in a deflated and stored condition as compared to its fully inflated and deployed configuration, has sufficient structural rigidity to function as a wing when deployed. The wing includes an array of inflatable chambers with generally circular cross-sections. The chambers are spaced a particular distance between their centers and held in that spacing by an outer wing skin. For equal cross-sectional diameter chambers this distance is less than the diameter. When the chambers are inflated the close spacing causes tension in the opposing surfaces to create a rigid structure.

Abstract: An aerodynamic fairing system for an airship having a substantially spherical balloon portion includes an inflatable fairing that is attachable to the balloon portion, and a fairing actuation mechanism that selectively inflates and deploys the fairing after lift-off, and deflates and retracts the fairing before landing. The actuation mechanism includes an inflation/deflation mechanism and a deployment/retraction mechanism that cooperate to deploy and inflate the fairing, and to deflate and retract the fairing. The fairing includes a substantially conical, inflatable tail section tapering from a wide forward end to a narrow aft end, and a collapsible annular collar connecting the forward end of the tail section to the balloon portion. The inflation/deflation mechanism includes a fan system in the tail section, and the deployment/retraction mechanism includes a plurality of cables attached between the tail section and a plurality of winches mounted on the balloon portion.

Abstract: In one aspect, a hybrid airship including an outer shell, a plurality of helium filled gas envelopes, and an all-electric propulsion system can have a high-aspect ratio wing shape. In some embodiments, the hybrid airship may be launched using buoyancy lift alone and aerodynamic lift may be provided by the all-electric propulsion system. In one aspect, a photovoltaic array and a high energy density power storage system may be combined to power the propulsion system making the propulsion system regenerative. The high-aspect ratio wing shape provides low drag, and can allow the hybrid airship to fly at an altitude of at least about 100,000 ft. By continuously recharging the power storage system, the hybrid airship in accordance with some embodiments can stay aloft for months or even years. The hybrid airship may function as a military intelligence, surveillance, and reconnaissance and communications relay platform.

Abstract: A cellular actuator device suitable for a control surface of an aircraft or space craft has a number of elementary cells which are combined to a common arrangement and are formed by pressure-tight chambers. The elementary cells can be acted upon by a pressure medium and, when acted upon by the pressure medium, can be deformed in at least one work direction while changing their length. The elementary cells are coupled for combining their length changes in the at least one working direction to an overall movement of the elementary cell arrangement. The actuator device is particularly suitable for actuating a control surface of an aircraft or spacecraft.