Abstract: An aircraft (10) comprises a wing (12) having an upper surface (16) and a lower surface (18) and at least one turbofan gas turbine engine (20) mounted on the wing (12). The axis (34) of the at least one turbofan gas turbine engine (20) is arranged substantially in the plane (14) of the wing (12) of the aircraft (10). The at least one turbofan gas turbine engine (20) has an intake, the intake comprising a hollow member (44) rotatably mounted coaxially with the at least one turbofan gas turbine engine (20) such that in use the hollow member (44) is rotatable between a first position, a low-speed condition, in which air flowing over and/or above the upper surface (16) of the wing (12) flows into the intake of the at least one turbofan gas turbine engine (20) and a second position, a high-speed condition, in which air flowing along and/or below the lower surface (18) of the wing flows into the intake of the at least one turbofan gas turbine engine.

Abstract: Known drinking troughs with drinking valves (21), which are assigned to a water-supply line (20), and water-collecting bowls (24) assigned to said drinking valves are problematic when it comes to supplying young chicks automatically with water. Known drinking troughs have proven unsuitable for young turkey chicks. The invention proposes a drinking trough which is also suitable for young turkey chicks. This drinking trough is distinguished in that valve pins for opening the drinking valves (21) are assigned elongate, tubular actuating levers (25). The actuating levers (25) facilitate the opening of the drinking valves (21). Moreover, by way of the tubular actuating levers (25) extending into the water-collecting bowls (24), the water passing out of the drinking valves (21) is directed specifically into he water-collecting bowls (24), as a result of which splashing of water is avoided.

Abstract: The piloting system (1) for generating orders for piloting the aircraft according to at least one piloting axis, for example the pitch axis, the roll axis, the yaw axis or the engine thrust control axis, comprises at least two piloting means (2, 3), each of which is capable of calculating the derivative with respect to time of the function which represents the corresponding piloting law and which takes into account the current values of parameters of the aircraft, first means (4) for intercomparing the derivatives calculated by the piloting means (2, 3) and for selecting a derivative; and second means (10) for integrating a selected derivative in such a way as to obtain said piloting order according to said piloting axis.

Abstract: A force sensor rod for an aircraft actuator system. The force sensor rod is constructed from a tube and a force sensing transducer. The force sensing transducer has a body containing a force responsive primary element and electronic circuitry. The force sensing transducer is provided with a protruding end composed of a material relatively harder than the tube material. The threads on the protruding end terminate in a plurality of axially spaced grooves adjacent to the force sensing transducer body and normal to the axis of the force sensing transducer. The tube is threaded onto the protruding end of the force sensing transducer and swaged onto the protruding end by causing the tube material to flow into the grooves.

Abstract: A vertical take-off and landing (VTOL) aircraft includes separate axial and vertical propulsion sources. The vertical propulsion source includes pulsejet engines located in separate augmentor bays having apertured walls to equalize pulsejet thrust. The pulsejet engine structure is integrated with aircraft structure such that aircraft structural loads are partially carried by each pulsejet engine. Each pulsejet engine produces an aircraft vertical thrust component throttled or exhaust restricted to control aircraft ascent or descent separate from the axial propulsion source. One or more inlet cowls isolate the pulsejet engine bays. One or more outlet cowls at the exhaust bays assist in controlling pulsejet engine thrust.

Abstract: A propeller related vehicle in accordance with one embodiment of the present invention is described as a helicopter having an airframe housing a pneumatic motor mechanism for powering a main propeller attached to a main drive shaft. The helicopter further includes a horizontal stabilizing means attached between the main propeller and the main drive shaft, which permits the main propeller to freely pivot about the main drive shaft independently from the airframe. As such when the main propeller is rotating and the main propeller begins to pitch, the rotating main propeller has a centrifugal force created by the rotation thereof and will tend to pivot about the horizontal stabilizing means in a manner that offsets the pitch such that the helicopter remains in a substantially horizontal position.

Abstract: An inlet ice protection system, and methods for making and using ice protection systems. In one embodiment, the inlet includes a tapered acoustic liner positioned forward of the inlet throat and has a perforated face sheet, a perforated back sheet, and an acoustic core between the face sheet and the back sheet. The perforations through the face sheet are sized to allow acoustic energy to be transmitted to and dissipated in the acoustic core, and the perforations in the back sheet are sized to transmit hot gas through the acoustic liner to the surface of the inlet to heat the inlet and prevent and/or restrict ice formation on the inlet. The face sheet can have a higher porosity than the back sheet, and both the sheets and the core can be formed from titanium to withstand high gas temperatures.

Abstract: Boundary layer control of a structural element in fluid stream is achieved by the following operations: providing in such structural element at least one region equipped with micro porous structure by an electroforming technique; having a fluid stream flow through the external surface of the at least one region, inwards or outwards with respect to the environment in which that element is placed.

Abstract: A fuselage comprising a skin assembly including an outer, laminate skin bonded to an inner, aluminum doubler. The fuselage also includes a support structure comprising a plurality of longitudinal stringer members and a plurality of annular frame members that are attached to, and cooperate to support, the skin assembly. The aluminum doubler provides additional structural support for the fuselage, and in particular, for the outer laminate skin of the skin assembly. The additional structural strength added by the aluminum doubler allows the use of an improved range of fasteners, such as knife-edge, countersink rivets and further allows the use of the laminate layer even in areas with a large number of cutouts, such as the window track of the fuselage. The members of the support structure may interconnected via a plurality of integral flanges, which, when combined with the skin, provide improved structural strength for the entire fuselage.

Abstract: A spacecraft protected by a coating includes a spacecraft such as a communications satellite has an external surface and a coating on the external surface of the spacecraft. The coating is formed of a binder, and a plurality of pyroelectric/ferroelectric pigment particles, preferably ferroelectric particles, bound together by the binder. Each ferroelectric pigment particle includes a ferroelectric pigment material having a ferroelectric/paraelectric transition. The coating may also include active secondary particles and/or inert particles. The coating may operate in a passive mode or an active mode with the application of a bias voltage to the coating.

Abstract: Anchoring systems for aircraft arresting nets utilize frangible anchor links around lower horizontal straps of each net element of a composite arresting net. Each anchor link may be formed from flexible plastic sheet material, with openings through which an anchor cable passes and is secured to a runway surface by an anchor retainer. The anchor links provide ease of anchoring system assembly in the field and retain the bottom of the arresting net in proper position prior to engagement of the arresting net by an aircraft overrunning the runway. When an aircraft engages the net, the anchor links break to permit the net to conform to and safely stop the aircraft. Each anchor link may be perforated in its central portion or otherwise formed or specified to provide suitable frangibility in an arresting incident.

Abstract: An aircraft is disclosed. The aircraft has a canard control surface 25 and an aft control surface 10. The canard control surface comprises an integral aerofoil which in its entirety pivots about a first axis of rotation 28. The canard control surface has a center of lift p which is rearward of the first axis. The aft control surface is rearward of the canard control surface and comprises an integral aerofoil which in its entirety pivots about a second axis of rotation 13. The aft control surface having a center of lift P which is rearward of the first axis. The canard control surface and the aft control surface act in unison to produce a directional change in the aircraft.

Abstract: An airship for lifting and transporting loads, particularly heavy loads. The lifting ability of the airship is given by lighter than air gas contained in bags located between two parallel horizontal platforms constructed in lightweight geodesic fashion, the platform and bag assembly being raised and lowered by means of respectively injecting and exhausting the gas into and from the bags, the whole, together with the lifted object, being moved and steered through the atmosphere by the combined means of conventional powered propeller units and a curtain circumferential to and rotated about the platforms thus using the Magnus Effect.

Abstract: The systems and methods of the invention include systems and techniques for controlling a turbulent boundary layer flow with a transverse traveling wave, oscillating at certain selected frequencies, amplitudes and wavelengths, to provide substantial reductions of drag. To this end, the systems and processes can include a boundary layer control system having an object with at least one surface exposed to a medium flowing over the surface. A plurality of excitation elements may be arranged on the surface and these elements are capable of exciting a traveling wave force field in a span-wise direction that is substantially parallel to the surface and perpendicular to direction of the flow. A first component of the traveling wave force field in the span-wise direction is substantially greater than a second component of the traveling wave force field, that is substantially perpendicular to the span-wise direction.

Abstract: A rocket fairing mounted on a forward section of a rocket body included in a rocket comprises a first structure formed on the fairing-base side, and including a first side wall defining a first storage space for storing a first payload; and a second structure formed on the fairing-forward side, and including a second side wall defining a second storage space for storing a second payload. The first side wall has a plurality of first side wall segments capable of being separated from each other along a plane including the longitudinal axis of the fairing and of being turned away from the first payload when releasing the first payload from the first storage space. The second side wall has a plurality of second side wall segments capable of being separated from each other along a plane including the longitudinal axis of the fairing and of being turned away from the second payload when releasing the second payload from the second storage space.

Abstract: An animal waste management system and method thereof is disclosed. The system is designed for use in high flush waste removal systems, but obviates the need for anaerobic lagoons when coupled to an advanced waste treatment facility. The system uses a continuous recycle loop of the waste slurry to increase the total solids concentration of the waste slurry to a level required by advanced waste treatment facilities. In particular, coarse solids are separated and removed from the recycled waste slurry to prevent clogging of the system. Aeration and pH control of the waste slurry when necessary prevents deterioration of the air quality surrounding the system.