Abstract: The invention concerns a free lighter-than-air aerostat comprising a structure (1, 3, 4, 5) symmetrical relative to a main axis (2), at least one main sealed pressurized chamber (16), one or several particle emitting thrusters (8), adapted to drive the aerostat in rotation in one direction about the main axis (2), one or several moving flaps (9) adapted to be set either in an active state wherein they brake the aerostat rotation, or in an inoperative state wherein they offer no substantial resistance to the aerostat rotation, and on-board control means (19) adapted to control the thrusters (8) and the flaps (9) to drive the aerostat in permanent rotation about the main axis (2), and in translation perpendicular to the main axis (2).

Abstract: An aircraft having a cabin within a wing of the aircraft includes an access opening in an aft end of the cabin adjacent a trailing edge of the wing, and a trailing edge portion of the wing juxtaposed with the access opening and including at least one pivotable panel which is pivotable into an open position so as to form a passage in the trailing edge portion for entry therethrough and through the access opening into the cabin. The trailing edge portion in one embodiment comprises upper and lower panels which are normally in converging relation such that the passage to the access opening of the cabin is normally closed, but which are pivotable relative to each other for creating the passage. The lower panel preferably is pivotable into a generally horizontal position so that it serves as a ramp for loading and unloading persons and cargo into and from the cabin. The upper and/or lower panel in another embodiment may be pivoted during flight so as to serve as a control surface for the aircraft.

Abstract: The development of polymer composite liquid oxygen (LOX) tanks is a critical step in creating the next generation of launch vehicles. A composite LOX tank will weigh significantly less than conventional metal tanks. This benefit of reduced weight is critical to enable future launch vehicles to meet required mass ractions. The high strength and low weight of a composite tank allows for a lighter weight craft and/or higher payload capacity which results in lower costs per pound to place an object in orbit. The unique, nontraditional idea described here is to use resin-based composite materials to make such a composite tank or other oxygen carrying component such as a feedline. Polymer composites have traditionally been regarded as being more flammable than metals and therefore deemed not oxygen compatible. However, a hybrid composite material may provide the optimal balance of oxygen compatibility and mechanical performance that would make composite oxygen tanks feasible.

Abstract: An active noise suppression apparatus and method for reducing jet engine noise and buffeting. A plurality of resonant cavities are formed in a structural member disposed on or adjacent to a jet engine exhaust nozzle. Each resonant cavity opens toward an output slot. A compressed air chamber is used to supply a pressurized, supersonic jetstream airflow through the inlet port into the interior area of the resonant cavity. This causes a high frequency, pulsed, excitation airstream to be generated outwardly from the cavity, out of the output slot and into the developing shear layer of the exhaust airflow. This high frequency, pulsed, excitation airstream induces modifications in the shear layer, which leads to a major reduction in the noise and buffeting generated by the developing shear layer. In an alternative embodiment, the resonant cavities are formed within one wall of a slot, where the slot is disposed along the leading edge of a cavity of the aircraft.

Abstract: The present embodiments and associated methods provide for a progressive 3-axis multi-variable propulsion vectoring aerial and spaceborne vehicle. One embodiment of the vehicle is comprised of top and side air intakes, a curved sphenoid air accumulator, a compressor section, a diffuser, a plurality of fuel burner cans, a turbine section, a gas plenum, top, side, and bottom exhaust ports, propellant burner cans, gas plenum iris, an onboard flight control computer, and top, side, and bottom exhaust port doors. Combustion gasses are produced which are directed by the gas plenum to the exhaust ports which provide thrust and lift to the vehicle. By selectively opening and closing the exhaust port doors, the vehicle may be made to rise, hover, and accelerate in any direction. Such an embodiment provides a vehicle that can directly ascend through the atmosphere into space.

Abstract: An aerodynamic component such as a helicopter rotor blade has an aerodynamic flow profile, a free end and a mounting end forming a blade root for attachment to a rotor mast. A blade section between the root and the free end has a leading edge and a trailing edge as viewed in the flow or chord direction. The blade is enclosed on its suction side and its pressure side with a respective skin. A nose flap or leading edge flap is secured to the leading edge by a bearing or hinge. The blade tilting angle is adjustable by piezo-drive elements arranged in at least one pair forming an actuator for each nose flap. The piezo-elements of a pair are arranged in the chord direction one behind the other and the pair is secured to the body of the blade by a fixed point positioned between the elements of a pair. The expansion and contraction from the piezo-element closer to the trailing edge is transmitted to the flap by a push rod.

Abstract: The present invention provides a system and method for actively manipulating and controlling aerodynamic or hydrodynamic fluid flow over a surface. More specifically, the present invention provides a system and method to control aerodynamic or hydrodynamic fluid flow behavior of a ducted fluid flow using very-small-scale effectors. The system and method for actively manipulating and controlling fluid flow over a surface includes the placement of arrays of very-small-scale effectors on ducted surfaces bounding the ducted fluid flow. These very-small-scale effectors actively manipulated the boundary layer manipulated to control the flow behavior of the ducted fluid flow and suppress or prevent flow separation within the primary fluid flow.

Abstract: An amphibious airplane having an engine assembly mounted at a top center location in the fuselage, and a tail assembly having a horizontal fin in an elevated position so as to be in the propeller air stream. A lift augmenting aerodynamic surface is positioned at the top middle portion of the aircraft fuselage, with the propeller being at the concavely curved rear end of the lift augmenting surface. A pair of platforms are positioned on opposite sides of the fuselage at lower locations adjacent to a passenger section of the aircraft. These platforms are aerodynamically aligned and also have strakes extending forwardly therefrom along opposite sides of the fuselage. In cruise mode, the increased velocity imparted to the propeller air stream acts on the horizontal fin to exert a downward force, with the various forces of the airplane balancing each other.

Abstract: A compound exhaust system including two or more stages, preferably three, uses the force of exhaust gases traveling from a thrust generating source through the exhaust system to maximize thrust and minimize wasted energy consumption. In particular, the compound exhaust system for a thrust generating source comprises at least a first stage exhaust and a smaller, second stage exhaust. Various reflections of high speed traveling gases are provided and the resultant pressures induced during this travel supplement the thrust provided by the thrust generating source, which can be a jet engine. The invention also relates to a novel airframe that uses multiple engines having the inventive compound exhaust system.

Abstract: A convertiplane having a wing in turn having two halfwings, each defined by a fixed portion adjacent to the fuselage, and by a movable portion rotating, with respect to the fixed portion, about a beam element extending the full length of the wing; the beam element supports, integrally, rotors located at respective ends of the wing, and engines connected to the rotors by a transmission, and is rotated about a respective axis by actuators to change the position of the rotors from a vertical-axis position wherein the convertiplane operates in helicopter mode, to a horizontal-axis position wherein the convertiplane operates in airplane mode.

Abstract: An improved aerobatic aircraft design having a first engine located in the nose portion of the fuselage and a second engine located in the tail portion of the fuselage. The thrust components of both the first and second engines are coaxial along the long axis of the fuselage. Both engines can individually provide sufficient power for the aircraft to takeoff, maintain altitude, and/or land.

Abstract: An arrangement of an airfoil, such as a main wing of an aircraft, includes a close-mounted engine on a short pylon connected to the airfoil, an inboard slat arranged inboard from the engine pylon along the leading edge of the airfoil, and an auxiliary high lift device. An open cut-out space is formed between the outboard edge of the inboard slat, the engine pylon, and the leading edge of the airfoil when the inboard slat is extended. The auxiliary high lift device is configured and arranged to be extendable into an extended position in which it aerodynamically covers or closes the cut-out space. The auxiliary high lift device is a movable high lift component that can be retracted into a retracted position in which it is recessed and integrated into the outer contour of the engine nacelle and/or the pylon. Thereby, the structural arrangement and mechanisms necessary for extending and retracting the auxiliary high lift device are simplified, and the weight and costs are reduced.

Abstract: A power plant and transmission arrangement for a helicopter wherein the helicopter engine is integrated to the helicopter transmission to form therewith a single unit rigidly mounted to the helicopter frame. By so integrating the engine to the helicopter transmission the center of gravity of the engine can be placed closer to the rotor mast of the helicopter, thereby enhancing the stability and the handling characteristics of the helicopter.

Abstract: A system for supplying a space station or satellite comprises a low cost expendable single-stage to orbit launch vehicle having a moderate reliability in the range of about 0.5 to 0.8 for launching a payload of consumable items to low earth orbit. For propulsion, the launch vehicle includes a pressure-fed rocket engine, preferably with a nozzle for aiming products of combustion in a direction away from the launch vehicle and having a fixed orientation relative to the launch vehicle. A pressurant tank contains an inert pressurant gas under pressure. A conduit system serves to introduce the inert pressurant gas from the pressurant tank to a fuel tank and thence to the rocket engine and also to introduce the inert pressurant gas from the pressurant tank to an oxidizer tank and thence to the rocket engine for combustion with the fuel.

Abstract: A system and method for docking a space object to a space travel vehicle is disclosed. The space travel vehicle includes a frame assembly which may be deployed into an at least generally funnel-shaped profile at the desired time. A web of sorts is attached to the frame assembly and is disposed into an at least generally funnel-profile by the deployment of the frame assembly as well. In one embodiment the web is in the form of a plurality of Velcro tape members. A space object contacting the web is detachably adhered thereto by including suitable fasteners on the space object as well. Retraction of the frame assembly directs the space object into a space object receptacle of the space travel vehicle, detaches the tapes from the captured space object, and retains the captured space object within the space object receptacle. After the captured space object has been retrieved, the frame assembly may thereafter be deployed to capture another space object in the above-described manner.

Abstract: A configurable space launch system of multiple different vehicle configurations that use a common reusable spaceplane and cost effective external tanks is presented. Each vehicle configuration in the system incorporates one or more reusable spaceplanes and most or all ascent propellant in multiple releasable external tanks. The flight trajectory of each vehicle has multiple in-flight staging points to increase vehicle performance efficiency. The system is governed and configured by a unique set of eight prescripts that together minimize launch costs.

Abstract: Apparatuses and methods for controlling an object spinning at a first rate in a first direction. The apparatus includes a swash plate, a rotor, a spin actuator, a roll actuator, and a pitch actuator. The rotor is coupled to the swash plate. The spin actuator is coupled to the rotor and is configured to spin the rotor in a second direction opposite the first direction at a second rate. The roll actuator is coupled to the rotor and is configured to displace the swash plate along a longitudinal axis. The pitch actuator is coupled to the rotor and is configured to tilt the swash plate in a tilt direction about the longitudinal axis, the tilt direction being adjustable by adjusting the second rate relative to the first rate. The roll actuator may be coupled to the pitch actuator so that the pitch actuator keeps a substantially identical orientation with the swash plate as the swash plate is displaced along the longitudinal axis by the roll actuator.

Abstract: An aircraft landing gear brake arrangement wherein a landing gear stub axle and brake pressure plate are integrated. Each of the integrated assemblies is attached to a support fitting which pivots on the truck axle thereby causing the torque links to be unaffected by steering operations.

Abstract: The present invention relates to a fully androgynous, reconfigurable closed loop feedback controlled low impact docking system with load sensing electromagnetic capture ring. The docking system of the present invention preferably comprises two docking assemblies, each docking assembly comprising a load sensing ring having an outer face, one of more electromagnets, one or more load cells coupled to said load sensing ring. The docking assembly further comprises a plurality of actuator arms coupled to said load sensing ring and capable of dynamically adjusting the orientation of said load sensing ring and a reconfigurable closed loop control system capable of analyzing signals originating from said plurality of load cells and of outputting real time control for each of the actuators. The docking assembly of the present invention incorporates an active load sensing system to automatically dynamically adjust the load sensing ring during capture instead of requiring significant force to push and realign the ring.

Abstract: An improved anti-icing system for a nose cowl of an aircraft jet engine. An improved injection nozzle is provided to passively enhance the injection of hot, pressure gas from the engine into the ambient air within the nose cowl to entrain such air and cause the entrained mass to rotate within the nose cowl in swirling rotational motion and thereby cause the temperature of the skin of the nose cowl to rise sufficiently to preclude the formation of ice thereon during flight. A plurality of spaced circumferentially arranged tab members, that are preferably triangularly shaped, are canted inwardly slightly to create large scale longitudinal vortices and transverse stirring during the introduction of hot gas and thereby enhance its mixture with the ambient air within the nose cowl and thereby preclude any tendency for the formation of an area of elevated temperature in the skin of the nose cowl downstream of the position of the injection nozzle under certain severe design conditions.