Abstract: A magnetohydrodynamic (MHD) flow control mechanism is described which substantially improves the existing processes in that smaller magnetic fields, requiring far less mass, are placed away from the forebody of the spacecraft to produce Lorentz forces that augment the lift and the drag forces for guidance, navigation, and control of the spacecraft.

Abstract: An unmanned aerial vehicle according to the present invention may comprise: a rotor-blade for providing thrust according to generation of main stream; and a safety guard disposed to surround the rotor-blade. The safety guard may comprise: a guide member which is disposed coaxially with the rotor-blade while having a gap between the guard member and the end of the rotor-blade, so as to stabilize, when the rotor-blade rotates, a flow field suctioned by a negative pressure, and stably boost a discharge flow when the pressure is changed to a positive pressure; and a diffuser which is disposed coaxially with and radially spaced apart from the guide member, and generates a secondary flow toward the main stream to increase a flow rate.

Abstract: A fixed-wing or rotary-wing aircraft has a tail boom that contains a fuel tank. The fuel tank is configured to contain pressurized hydrogen. The pressurized hydrogen fuels a fuel cell stack to generate electricity to rotate one or more rotors or propellers. The fuel tank may define the structure of the tail boom and may support the empennage, tail rotor, propeller, convertible thruster, ducted fan or vectored thruster and associated drive systems with respect to the fuselage. The aircraft has adequate control authority for sustained coordinated flight when the fuel tank is filled with pressurized hydrogen and when the fuel tank is drained of pressurized hydrogen. The same aircraft may not have adequate control authority for coordinated flight if fuel tank was filled with a conventional liquid fuel.

Abstract: An embodiment of the present disclosure relates to an unmanned flying robotic object that contains a wheeled mechanism that encircles its spherical exoskeleton. This feature allows the flying spherical vehicle to readily transform into a ground maneuverable vehicle. A robotic motor with differential speed capability is used to operate each wheel to provide effective ground maneuverability. There are examples provided herein of wheel configurations suitable for use with an embodiment. One is the straight- (or parallel) wheel design, and another is tilted-wheel design as are illustrated and discussed hereinafter. One embodiment of an unmanned flying robotic object taught herein is foldable.

Abstract: A tethered aerial vehicle, connected to an anchorage system in the ground level through a cord, comprising a pair of fixed wings; and a drive assembly. The drive assembly comprises at least two actuators configured to tilt the axle of the propellers. The fixed wings define a center hole located close to a gravitational center of the aerial vehicle. Within the edges of the center hole located close to the gravitational center of the aerial vehicle is a gimbal anchored to the fixed wings' structure. The drive assembly is located within the edges of the center hole and attached to the gimbal in a manner that the gimbal interfaces the connection between the fixed wings and the drive assembly. The drive assembly comprises of at least two propellers mounted on the same axle (“coaxial propellers”) driven by a counter-rotating motor. The coaxial propellers are configured to rotate in opposite directions with respect to each other.

Abstract: An aircraft is provided. The aircraft includes fuselage, an aerodynamic element extending from the fuselage and including a main section and an adjustable section which is adjustable relative to the main section, a power distribution unit (PDU) configured to generate torque to drive an adjustment of the adjustable section, an actuator, torque tubes and elastomeric couplings. The PDU is disposed proximate to a fuselage-aerodynamic interface. The actuator is disposed along the aerodynamic element and is receptive of the torque for driving the adjustment of the adjustable section. The torque tubes transmit the torque from the PDU to the actuator and are arranged between the PDU and the actuator such that adjacent torque tubes define an obtuse angle. The elastomeric couplings are disposed at respective ends of each of the torque tubes to enable torque transmission between at least the adjacent torque tubes defining the obtuse angle.

Abstract: An aerial vehicle includes a fuselage, a wing, and a wing shift device. The wing shift device is configured to be coupled to the fuselage. The wing shift device comprises a plurality of apertures for coupling the wing to the aerial vehicle. The plurality of apertures are configured to permit the wing to be shifted in a forward or aft direction along the fuselage based on a center of gravity of the aerial vehicle.

Abstract: Three spinning ring rotors, functioning as concentric ring gyro motors, are angled at ninety degrees with respect to one another and are arranged in an orthogonal association inside a substantially spherical housing that includes a central hub with a plurality of spokes attached to the spherical housing with holes for the spokes and coils used for steering. The mass distribution for the rings is such that the rotating ring masses are maximized and the containing mass is minimized. There is minimum friction for the primary rotation of the spinning ring rotors with all other angular forces translated across the containment structures uniformly. These spinning masses remain equal, unless the influence of precisely controlled and oriented destabilizing steering coils are used to disrupt the stability of one or more rotors by placing a controllable and varying magnetic field, from weak to strong, parallel to the axis of the spinning rotors.

Abstract: A process and device for optimising the performance of an aircraft in the presence of a lateral dissymmetry is disclosed. The device (1) includes means (2, 3, 4, 5, 7, 9) for controlling, during a lateral dissymmetry, at least one rudder such as to generate an optimum sideslip for reducing the drag of the aircraft.

Abstract: A WIG (wing in ground effect) vessel includes a hull with wings attached. The WIG vessel includes means for propulsion as well as altitude and directional control. The lift of the wings in ground effect is augmented by partial aerostatic lift, achieved through interior gas holding envelopes containing a lighter-than-air gas. The wings have a high mean chord length, for example fourteen meters or more, allowing the vessel to fly in ground effect above water at an altitude where waves are of minimal concern. The vessel has a low wing loading, below 1.5 kg/m2, and the wings are of uniform thickness and have an aspect ratio of less than 1. The conical fore end of the hull forces air below the surface of the wings for ground effect. Weight transfer is used to alter the pitch of the vessel.

Abstract: An improvement and method for improved structural dynamic stability for 20 and 30 Series Learjets are disclosed. The improvement includes a redistribution of the elevator mass balance to uncouple the elevator rotational motion from the stabilizer translation motion for the higher order horizontal frequencies having node lines in the proximity of the mass outboard counterbalance weights. The original tail section includes a rudder, and a horizontal stabilizer supporting an elevator mounted adjacent the rudder. The elevator includes a proximal end adjacent the rudder and a distal end that includes a counterbalance portion. The improvement includes replacement of an original mass counterbalance weight from within the counterbalance portion with a new mass counterbalance weight of less mass, and the inclusion of additional mass counterbalance weights disposed within the elevator and interposed between the proximal end and the counterbalance portion.

Abstract: A method and apparatus for changing a flight path of an air platform. A change for the flight path of the air platform is identified. A weight system associated with the air platform is moved during flight of the air platform such that a center of mass of the air platform changes in a manner that causes the flight path of the air platform to change.

Abstract: An improvement and method for improved structural dynamic stability for 20 and 30 Series Learjets are disclosed. The improvement includes a redistribution of the elevator mass balance to uncouple the elevator rotational motion from the stabilizer translation motion for the higher order horizontal frequencies having node lines in the proximity of the mass outboard counterbalance weights. The original tail section includes a rudder, and a horizontal stabilizer supporting an elevator mounted adjacent the rudder. The elevator includes a proximal end adjacent the rudder and a distal end that includes a counterbalance portion. The improvement includes replacement of an original mass counterbalance weight from within the counterbalance portion with a new mass counterbalance weight of less mass, and the inclusion of additional mass counterbalance weights disposed within the elevator and interposed between the proximal end and the counterbalance portion.

Abstract: The invention relates to a mechanism to control the pitch and/or roll and/or center of gravity of a vehicle. The first embodiment is a track-based mass transfer system in which pathways are positioned along or radially terminate at a central horizontal plane of the vehicle to move one or more mass transfer devices to a desired location to control the pitch and/or roll and/or center of gravity of the vehicle. A second embodiment is a fluid mass distribution system in which one or more conduits selectively distribute a fluid to one or more tanks positioned near a central horizontal plane of the vehicle to control the pitch and/or roll and/or center of gravity of the vehicle.

Abstract: The invention is an unmanned flying helicopter aircraft platform (“aircraft platform”) that can be powered by either interchangeable electric motors or by fuel powered internal combustion engines. The aircraft platform is surrounded by a lightweight exoskeleton cage that protects the rotor blades from coming into contact with external objects. The aircraft platform uses a weight located on the bottom side of the aircraft platform that can be remotely moved to adjust the center of gravity in order to navigate in any direction. The aircraft platform has a place on its bottom side where attachments can be added or removed which allows the aircraft platform to be used for multiple different purposes. The aircraft platform can be flown and operated either remotely using a hand held control unit or it can be flown and operated by an onboard pilot located in the human carrying attachment.

Abstract: A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage.

Abstract: The invention relates to a mechanism to control the pitch and/or roll and/or center of gravity of a vehicle. The first embodiment is a track-based mass transfer system in which pathways are positioned along or radially terminate at a central horizontal plane of the vehicle to move one or more mass transfer devices to a desired location to control the pitch and/or roll and/or center of gravity of the vehicle. A second embodiment is a fluid mass distribution system in which one or more conduits selectively distribute a fluid to one or more tanks positioned near a central horizontal plane of the vehicle to control the pitch and/or roll and/or center of gravity of the vehicle.

Abstract: The invention relates to a mechanism to control the pitch and/or roll and/or center of gravity of a vehicle. The first embodiment is a track-based mass transfer system in which pathways are positioned along or radially terminate at a central horizontal plane of the vehicle to move one or more mass transfer devices to a desired location to control the pitch and/or roll and/or center of gravity of the vehicle. A second embodiment is a fluid mass distribution system in which one or more conduits selectively distribute a fluid to one or more tanks positioned near a central horizontal plane of the vehicle to control the pitch and/or roll and/or center of gravity of the vehicle.

Abstract: A supersonic aircraft comprises a wing, a fuselage, a plurality of fuel tanks contained within the wing and/or fuselage, and a fuel transfer system communicatively coupled to the plurality of fuel tanks and capable of transferring fuel among the plurality of fuel tanks. The aircraft further comprises at least one sensor capable of indicating a flight parameter and a controller. The controller is coupled to the one or more sensors and to the fuel transfer system. The controller can transfer fuel among the plurality of fuel tanks and adjust the aircraft center of gravity to reduce trim drag and increase aircraft range.

Abstract: An unmanned air vehicle includes a singular rear landing gear wheel on the aft end of the fuselage. Port and starboard wings with rear facing propellers are retractable to the aft of the fuselage. Upon retraction, the propellers may freewheel and a reversible motor-generator is provided to convert the freewheeling propeller energy into electric power. Photovoltaic cells also provide electric power to the unmanned air vehicle. Port and starboard nose fairings are control surfaces for the vehicle. The port and starboard nose fairings also include landing gear wheels. A method of flying an unmanned air vehicle includes retracting port and starboard wings to achieve a ballistic dive.

Abstract: The invention provides an aircraft having a flight control system (20) comprising an aerodynamic lift generator, and a control system in use the lift provided by the lift generator. The lift control system in one embodiment uses a concentrated mass mounted within a longitudinal body of the aircraft, the concentrated mass comprising at least one existing aircraft function and/or system mounted on a support in a confined area. Bearings permit relative movement between the support for the concentrated mass and at least a portion of the lift generator. An actuator is provided for causing such relative movement whereby in use the center of aerodynamic lift and the center of gravity of the aircraft may be moved relative to one another for effecting flight control.

Abstract: An adjustable weight ballast for lighter-than-air balloon with a predetermined lift is disclosed, comprising at least two individual weights. There is a first means on each individual weight for selectively attaching two or more weights to each other to form a composite weight having a total weight at least equal to the predetermined lift of the balloon, and a second means for tethering the lighter-than-air balloon to this composite weight, in which manner a ballast for a balloon can have its weight incrementally adjusted to an amount just greater than the balloon's predetermined lift to thus securely tether the balloon to a surface on which the composite weight is supported without significantly exceeding the lift of the balloon.

Abstract: The invention concerns a remote-controlled flying machine, in particular for surveillance and inspection, capable of hovering and comprising a spherical open-worked resistant shroud integral with a cylindrical fairing wherein rotates a propeller powered by an engine housed in a fuselage secured to the fairing with radial arms and straightening vanes.

Abstract: An airship (1) comprising gas envelope means for providing in use a hull (2) with a generally longitudinally extending longitudinal axis (20) and solar cell array means (3) arranged in use to be mounted on the outside of the hull (2). The solar array means (3) are arranged in use to extend around only a part of the circumference of the hull (2) and are turned about the longitudinal hull axis (20) to control the amount of incident solar radiation collected by the solar cell array means (3).

Abstract: The invention provides an aircraft having a flight control system (20) comprising aerodynamic lift generating means (14), and means for controlling in use the lift provided by the lift generating means, the lift control means comprising:

Abstract: A fordable ascending/descending wing stand for a flying apparatus is disclosed. The wind stand includes a base supported on a car by a number of supporting rods. A frame is mounted on the base, provided with four propellers capable of generating a required upward and forward force to the flying apparatus. The angle of the propellers are controllable by a number of hydraulic actuators mounted on the frame. A tail helm is arranged on the frame for controlling the frying orientation of the car during flying. The base is further provided with a leftward/rightward mass center adjusting mechanism and a forward/rearward mass center adjusting mechanism for adjusting the mass center of the car during flying.

Abstract: A dynamic balance mechanism for balance control of a gyro stabilized (spinning) satellite is disclosed. An elongated gear rack is attached to the spacecraft. A movable mass is mounted by guide rollers on the gear rack and translates along the gear rack according to requisite electronic commands. The movable mass includes a housing, a stepper motor, a rotary potentiometer, a cable reel, a pair of gear heads and a pinion gear. The pinion gear meshes with the rack and is driven by the stepper motor. The potentiometer measures the position of the movable mass on the gear rack. The cable reel saves space and minimizes harness jamming conditions. The invention secures better weight efficiency.

Abstract: A trim system for a submersible comprises a ball control system and a hydraulic control system. The ball control system includes a tubular ball transfer line 33 substantially through the length of the vessel, a plurality of high-density, solid balls 34 within the ball transfer line 33 which are moveable to alter the weight distribution, a coil 1 at each end of the ball transfer line 33 as a reservoir for the balls 34, brake device 3 for temporarily fixing the position of the balls and sensing device 5 for determining the location of the balls. The hydraulic control system includes vehicle control unit 27, power transfer unit 13, manifold 2, compensator 20 and various valves, filters 17 and quick disconnects 12 for moving preselected balls through the ball transfer line 33.

Abstract: An air floater comprises a balloon body which seals a gas therein and balancing means detachably attached to the balloon body. The balloon body comprises a film composed of a central layer made of ethylene-vinyl alcohol copolymer-resin, an aluminum evaporated layer provided outside the central layer, and a heated adhesive layer provided inside the central layer. The balancing means comprises a plurality of magnetic cards which are attracted by an attraction portion composed of a magnetic body attached to the balloon body. The plurality of magnetic cards includes one card having a reference weight matched with the buoyant force of the balloon body, first weight balancing cards having weight heavier by stages than the reference weight, and second weight balancing cards having weight lighter by stages than the reference weight. The balancing means may comprise sublimate sealed in a bag body.

Abstract: The balance of a spin-balanced spacecraft may be dynamically adjusted by moving a liquid between or among containers spaced about the spin axis. The transfer of liquid is accomplished by controllable heaters associated with each container, for heating that container from which liquid is to be transferred to increase the pressure and drive out liquid. A spacecraft for accomplishing this method includes a balance sensing arrangements such as a gyroscope and logic for determining which container or containers are to be emptied and for controlling the heaters. Weight is minimized by accomplishing the transfer of liquid among fuel containers by way of manifolds which also supply fuel to thrusters.

Abstract: A rescue balloon for rescuing individuals from high places such as towers and building includes an enclosed envelope for holding heated air under substantially greater than atmospheric pressure with a burner contained within the enclosed envelope for burning a combustible gas to generate sufficient heated air under pressure in the envelope to provide lift to the balloon. A rescue compartment is carried by the envelope for accommodating rescued individuals and a tether is provided for guiding the balloon as necessary to effect rescues. The balloon includes a porous blast shield positioned within the envelope to prevent direct contact between the envelope and the flame of the burner. The blast shield comprises an upright cylinder supported and secured in fixed relation within the envelope by a plurality of catenaries attached to the blast shield and to the inner walls of the envelope around its perimeter. The burn super-pressurizes the heated air within the envelope.

Abstract: A pitch control trimming system for a canard design aircraft has the ability to reposition the center of gravity of the aircraft along the longitudinal axis. The design permits trimming of the aircraft without external trim tabs and permits flaps to be used on a canard design aircraft without a nose down or negative pitching moment occurring. The aircraft has a substantial mass associated with the aircraft preferably the power plant including engine and propeller, which is movable substantially along the longitudinal axis of the aircraft, and includes an actuator to move the mass forward and aft on the longitudinal axis to reposition the center of gravity of the aircraft.

Abstract: A rescue balloon for rescuing individuals from high places such as towers and buildings includes an enclosed envelope for holding heated air under substantially greater than atmospheric pressure with a burner contained within the enclosed envelope for burning a combustible gas to generate sufficient heated air under pressure in the envelope to provide lift to the balloon. A rescue compartment is carried by the envelope for accommodating rescued individuals and a tether is provided for guiding the balloon as necessary to effect rescues. The balloon includes a porous blast shield positioned within the envelope to prevent direct contact between the envelope and the flame of the burner. The blast shield comprises an upright cylinder supported and secured in fixed relation within the envelope by a plurality of catenaries attached to the blast shield and to the inner walls of the envelope around its perimeter. The burn super-pressurizes the heated air within the envelope.

Abstract: The invention provides a kite, particularly an article dropping kite, consisting of a kite body, which usually is provided with a downwardly-extending kite keel to which is connected the kite string. The kite is provided with an article holding and releasing means consisting of a flexible-walled pocket, usually forwardly-opening, which is closed by the tension on the kite string to hold the article in the pocket during launch and flying. Upon release of the tension the pocket tends to open, assisted by entry of air into the pocket by the kite's forward motion, and the kite stalls and tips forward under the forward location of the article until the article is released. Alternatively, or in addition the holding and release means are flexible parallel straps cooperating with the keel, or a separate pocket. A weight is provided at the point of attachment of the kite string to the body and cooperates with the pocket to produce a swooping, gliding decending motion of the kite upon release of the tension.

Abstract: A towable gliding flexible wing craft for hauling a payload including a passive control means for responding to deviations from level flight. The gliding wing craft comprises a gliding flexible wing, spreader bar, support means for securing said gliding flexible wing to said spreader bar, a bridled tow line secured to said spreader bar for towing said gliding craft, means for securing said payload to said spreader bar and control means for causing wing tip lift or control dragulation of said wing. The control means is capable of passively responding in an opposing manner to deviations from level flight resulting in substantially level flight.

Abstract: Aircraft with rotary wings, characterized in that it comprises a nacelle (1) surrounding the user who seats on a seat (9) slidingly arranged in the medial plane of said nacelle, substantially in the normal displacement direction of flight of the aircraft, two parallel crowns (40-41) carried by the nacelle and imparted with identical rotational motions but in inverted directions about a common axis, extending substantially at the center of the nacelle, perpendicularly to the plane of said crowns, each of the crowns supporting at least one pair of blades (48-49, 50-51) or wings diametrically opposite and arranged in the prolongation of each other, drive means (19-37) for driving the crowns about the nacelle and means (66-67) for changing in each pair of blades the pitch thereof in an equal but opposite way for each of them.

Abstract: An aircraft of the hang glider type includes a wing (11) with a keel (12) in its plane of symmetry serving as a fastening point for a trapeze and a harness by which the pilot is suspended below the wing, the trapeze and the harness being disposed in conventional manner for suspending a pilot in the prone position. The invention provides a motor propeller unit (15) which is mounted in such a manner as to be movable at least in the longitudinal direction along the keel axis under pilot control, thereby enabling the pilot to displace both the center of gravity of the motor propeller unit and his own center of gravity between an extreme forward position ahead of the center of lift of the wing and an extreme rearward position behind the center of lift (1).

Abstract: A conventional aircraft having horizontal stabilizers and hinged elevators, which is controlled, preferably, through push-pull rods, is provided with a dynamic torque (bob) weight connected to a rotating member, in the direct line of control to the elevator surfaces. The torque member is located in the nose portion of the aircraft with its center of gravity angled up from 20.degree. to 50.degree. when the elevator surfaces are in the neutral position. The torque member is also mounted in a flexible manner to isolate it from horizontal tail vibrations, or flutter.

Abstract: An annular wing particularly suited for use in supporting in flight an aircraft characterized by the absence of directional stabilizing surfaces. The wing comprises a rigid annular body of a substantially uniformly symmetrical configuration characterized by an annular positive lifting surface and cord line coincident with the segment of a line radiating along the surface of an inverted truncated cone whereby a decalage is established for the leading and trailing semi-circular portions of the body, relative to instantaneous line of flight, and a dihedral for the laterally opposed semi-circular portions of the body, relative to the line of flight, the direction of flight and climb angle or glide slope angle being established by selectively positioning the center of gravity of the wing ahead of the aerodynamic center along the radius coincident with an axis for a selected line of flight.

Abstract: A device for controlling the movements or operating cycles of models, for example, model airplanes, model ships, kites, etc., which are driven by a drive motor is provided which includes a screw spindle which is affixed at about the center of a shaft which is coupled with the motor drive shaft. An internally-threaded element, preferably a nut, is longitudinally guided on the screw spindle for actuating the operating cycle in one or the other direction. At the two protruding ends of the shaft, a spiral spring is disposed which urges a washer against the screw spindle in such a way that when the element becomes unscrewed from either end of the screw spindle, the element is retained in a free-running position, and during the reverse rotation of the motor drive shaft, the element is pushed in a counter direction whereupon it is screwed onto the screw spindle.

Abstract: An aircraft is disclosed which includes a body having the shape of an inverted cone with a downwardly extending rim formed about the edge thereof and a triangularly shaped tail section. The aircraft can be constructed as a glider or a powered device and several alternative tail sections are shown such as square, radii, circle and tangent.

Abstract: The invention is particularly adapted, but not limited to, control of hand-launched gliders. A weight or mass is suspended in the manner of a pendulum below the aircraft. The weight is controllable by a gimbal mechanism which allows the weight to be swung fore and aft and laterally. The gimbal mechanism includes members mounted to be rotatable about a fore and aft axis and a lateral axis, which axes intersect and are perpendicular to each other. Radio controlled servomotors are provided for individually rotating the gimbal members for controlling the position of the weight or mass for controlling the aircraft in flight. The servomotors are controlled by a radio by way of separate frequency channels.

Abstract: A tube with weights slidably located inside and apparatus to remotely conl their position and thereby change the vehicle's center of gravity. The tube is rigidly attached to the vehicle with its centerline running fore and aft if trim is to be controlled or running athwartships if the system is to be used to control list.

Abstract: Apparatus for stabilizing a platform characterized by a frame carrying a stabilizing gyroscope that includes a substantially horizontal rotor with its shaft fixed with respect to the frame so as to effect a precessing force 90.degree. in the direction of rotation responsive to a torque force on the shaft in any azimuthal direction in a horizontal plane; a shifting carriage for shifting a load carrying compartment to move its center of gravity with respect to the frame to a plurality of successive second locations to offset to a desired degree a torque force and the reactive precessing force; and a control device for detecting a slight change in attitude from a desired attitude and effecting via the shifting carriage a controlled shifting of the load carrying compartment to a new second location to reestablish the desired attitude. The invention is readily applicable to vertical take-off and landing craft or other platforms having a lifting device connected therewith.

Abstract: A flexible lighter-than-air gas-containing envelope carries at least one rigid structural member which provides a track for pivotal and slidable mounting of a gondola. The track extends along the underside of the airship from the nose section to a point aft of the midsection so that the gondola can be positioned from a point directly under the belly to one at the nose, causing the longitudinal axis of the envelope to rotate through 90.degree.. Remote controls actuate the rudders, ailerons and elevators as well as fully rotatable horizontal stabilizers and wings.