Abstract: A surveillance vehicle (10) comprising a vessel (11) and a parasail (12). The vehicle (10) is loaded, in a pre-launch condition, into a mortar tube for projection therefrom towards an area of interest. In this pre-launch condition, the vessel (11) resembles a conventional mortar round and the parasail (12) is stowed within the vessel (11). Upon arrival at the area of interest, the parasail (12) is deployed from the vessel (11) and instrumentation collects survey data.

Abstract: A method and apparatus for an airfoil, a flexible skin, and a shape control system. The flexible skin forms a control surface of the airfoil. The shape control system is capable of changing a shape of the control surface formed by the flexible skin between a plurality of shapes, wherein a gap does not occur during a changing of the shape of the control surface.

Abstract: A metamaterial has a magnetic permeability response at frequencies sufficient to generate a repulsive force between a fluid and a surface to which the metamaterial may be applied. The metamaterial may be nanofabricated such that an absolute value of the magnetic permeability of the metamaterial is substantially greater than an absolute value of an electric permittivity of the metamaterial. The metamaterial may generate a repulsive force between the surface and the fluid moving relative to the surface and thereby reduce viscous drag of the fluid on the surface. A method of reducing the viscous drag of the fluid moving past the surface includes producing relative motion between the surface and the fluid and generating the repulsive force between the surface and the fluid.

Abstract: Disclosed herein, in certain embodiments, is a method of altering the stability of unstable space debris. In some embodiments, the method further comprises changing the orbit of the unstable space debris.

Abstract: Systems and methods for controlling air vehicle boundary layer airflow are disclosed. Representative methods can include applying electrical energy bursts and/or other energy bursts in nanosecond pulses in the boundary layer along a surface of an air vehicle. In a particular embodiment, electrical energy is discharged into the boundary layer to reduce the tendency for the boundary layer to separate and/or to reduce the tendency for the boundary layer to transition from laminar flow to turbulent flow. In other embodiments, energy can be discharged via pulses having a pulse width of about 100 nanoseconds or less, and an amplitude of about 10,000 volts or more. Actuators discharging the energy can be arranged in a two-dimensional ray of individually addressable actuators. Energy can be delivered to the boundary layer via a laser emitter, and energy can be received in a receiver after having transited over at least a portion of the airflow surface.

Abstract: An aircraft including a fuselage including a cabin to accommodate persons and/or a load, and a propulsion system. The propulsion system includes at least one tank and/or one combustion chamber, wherein part of the propulsion system can be used as an extension of the cabin to accommodate persons and/or a load, the part of the propulsion system lying adjacent the cabin and separated from the cabin by a partition.

Abstract: In the field of avionics, it is difficult to justify initiation of new aircraft programmes for replacement of small numbers of niche aircraft. Instead, in many cases, retrofitting existing aircraft is preferred for economic reasons. In this respect, upgrading existing braking systems to accommodate replacement of existing brake units employing sintered friction materials with brake units employing carbon-carbon composite friction materials is desirable. However, when upgrading the braking systems it is necessary to ensure that the integrity of the existing airframe is not compromised by the use of the new brake assemblies employing the carbon-carbon composite friction materials. Consequently, the present invention replaces existing pressure control valves of existing braking systems with an electronic control unit (126) coupled to a pressure control servovalve (128) thereby ensuring proper application of hydraulic pressure to brake assemblies (122).

Abstract: A support structure for an aircraft, includes one or several bar elements and one or several junction elements. At least one bar element includes a transition region which can be made to engage at least one junction element. When the transition region of the bar element engages at least one junction element, centric force transmission takes place between the bar element and the junction element.

Abstract: An active vortex control system (AVOCS) includes a set of primary injectors that inject gas into a cavity to generate a vortex in front of and possibly around components inside the cavity. The vortex interferes with an external flow field in an opening to the cavity to protect the components from the external environment. Sets of secondary injectors may inject gas at a reduced mass flow into the cavity to compensate for energy losses to maintain the coherence of the vortex. The AVOCS is well suited for use in windowless endo- and exo-atmospheric interceptors to protect the electro-optical imagers and optical components from Earth atmosphere.

Abstract: In example embodiments described herein, techniques are described for launching flying structures such as a plank wings or a gliders, canards, or any other flying structures. In some example embodiments, a rotational arrangement facilitates such launches. In operation, a rotational arrangement couples with the flying structure and is configured to allow a user to impart rotational movement to the flying structure. In imparting the rotational movement, the rotational mechanism allows an automatic variation of a radius of the associated radius of curvature.

Abstract: Takeoff and landing modes are added to a flight control system of a Vertical Take-Off and Landing (VTOL) Unmanned Air Vehicle (UAV). The takeoff and landing modes use data available to the flight control system and the VTOL UAV's existing control surfaces and throttle control. As a result, the VTOL UAV can takeoff from and land on inclined surfaces without the use of landing gear mechanisms designed to level the UAV on the inclined surfaces.

Abstract: A landing gear for an aircraft, characterized by upper and lower pintle frame members (38, 40) being connected to a telescoping shock strut (14) in a non-rigid manner that tolerates twisting when reacting to torsional loads applied to the landing gear, and/or by a pitch trim actuator (30) that positions a landing gear truck (16) proportionally to the retraction angle of a shock strut (14) during retraction and extension.

Abstract: In a self-propelled wheel apparatus of an aircraft, a drive mechanism composed of a wave gear drive and a motor is coaxially linked to an axle of a wheel via a one-way clutch, and rotational force in the reverse direction of the aircraft is transmitted to the wheel axle via the one-way clutch. When the aircraft moves forward, the link between the wheel axle and an output shaft of the wave gear drive is cut off by the one-way clutch, and motor rotational force is transmitted to the wheel axle, causing the wheel to rotate, only when the aircraft moves backward.

Abstract: The invention relates to an aircraft wing including two members removably connected end to end by a coupling including: a male coupling part with spaced opposed upper and lower faces, a first face being planar while the second face has a longitudinal relief (9) with a V-shaped section, the first and second faces being mutually included towards each other at their free ends; a female coupling part with spaced upper and lower faces facing each other, a first face being planar while the second face has a longitudinal relief with a V-shaped section complementary to that of the relief, and the first and second faces being mutually inclined away from each other at their free ends; and a fastener for retaining the two parts coupled with their respective interacting faces in a mutual bearing relation.

Abstract: Winglets with recessed surfaces, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a wing having an inboard portion and an outboard portion, and further includes a winglet coupled to the wing at the outboard portion. The winglet can have a first surface facing at least partially inboard and a second surface facing at least partially outboard, with the first surface including a recessed region.

Abstract: The invention relates to an aircraft, and a method for operating an aircraft, the aircraft having a longitudinally unstable configuration and swept wings, the swept wings being based on aerofoils having a leading edge and configured for preventing attachment line transition in conditions of laminar flow over the swept wing for at least a predetermined first range of lift coefficients at a second range of Reynolds numbers. The invention also relates to an aerofoil, and to a method for providing an aerofoil, the airfoil being configured for a thick-sectioned subsonic/transonic swept wing, having a curved leading edge, a trailing edge, a thickness dimension and a chord dimension, wherein the leading edge comprises a leading edge curvature associated with a leading edge radius that is configured for preventing attachment line transition in conditions of laminar flow over the swept wing.

Abstract: The invention relates to a plasma based aircraft possessing a magnetic field, and a plasma vortex. The craft is tubular in shape. The craft has a vast array of capacitors. The craft also has a proton accelerator, plasma guns, and diversion devices. The craft will approach the speed of light, over time. The craft obtains fuel direct from an atmosphere or a radiation induced atmosphere in space, at no cost, similar to our Moon's radiation induced atmosphere of the noble gases. The craft can travel to a gk star, for only the cost of construction of craft. The craft has three on-board escape, exploratory craft. The craft produces plasma vortices within an electromagnetic field. The field is an inhomogeneous, diamagnetic, orbiting plasma field, with a magnetohydrodynamic electrically conducting plasma current. The craft possesses approximately seven uninsulated, tungsten bands, encircling craft.

Abstract: A lifting or stabilising component (11) for an aircraft comprising in the area of its trailing edge a rotary control element (13) rotating around an axis (61) with at least one slot (21) between the tip (15) of the component (11) and the control element (13), the edges of which are configured such that the distance therebetween, that is, the dimension of the slot (21), is constant for different angles of deflection of the control element (13), being located between them a seal (23) that assure the aerodynamic continuity of the component (11) when the control element (13) is at rest. In a preferred embodiment, the component (11) is a horizontal tail stabilizer and the control element (13) is a rudder.

Abstract: An inlet door assembly includes an inlet door rotatable about an axis of rotation.

Abstract: A flower support for long-stemmed flowers comprises an elongated support part as well as series of hook means in which the flower stems can be hooked, which series of hook means at both sides of the support part extend away from each other in an obliquely oriented fashion. The series of hook means are positioned obliquely with respect to each other. The oblique position of the series of hook means brings that a cavity is formed in which the stems of the hooked in flowers are well protected.