Abstract: A control system for a flying vehicle in an atmospheric environment, the vehicle having an aerodynamic shape including a front end and a rear end including a plurality of attitude control jet nozzles spaced outward from the vehicle near the rear end of the vehicle or a trailing edge of a vehicle part; and a generator for providing a low mass flow of a fluid through the attitude control jet nozzles to create an area of high pressure immediately forward of the nozzles and adjacent the flying vehicle, wherein the location of the attitude control jet nozzles is so close to the rear end of the vehicle that any area of low pressure created by the low mass flow of fluid through the attitude control jet nozzles does not contact the vehicle.

Abstract: A wing for an aircraft has a passive jet spoiler for providing yaw control by increasing drag on the wing. The spoiler comprises an inlet located near the leading edge of a lower surface of the wing and at least one outlet formed on the lower surface or on an upper surface of the wing. An internal passage connects the inlet and each outlet for allowing air to pass from the inlet to the outlet. The air exits the outlets generally normal to the respective surface of the wing, causing a laminar flow to separate from the surfaces downstream of each outlet. The separated flow increases the drag on the wing, producing a yawing moment on the aircraft. Selective placement of the outlets on the upper and lower surfaces limits undesirable roll and pitch moments. Valves are provided for selectively controlling the amount of air passing through the spoiler.

Abstract: A VTOL aircraft having a fuselage, a first wing extending from one side of the fuselage, a second wing extending from an opposite side of the fuselage, a first thruster supported on the first wing, a second thruster supported on the second wing and a propulsion system connected to the fuselage. The first thruster serves to direct a thrust of air at an angle toward an area directly below the fuselage. The second thruster is angularly directed so as to direct the thrust of air at an angle toward the area directly below the fuselage. The propulsion system serves to propel the fuselage through the air. Each of the thrusters is a jet engine. Each of the thrusters can be angularly moveable between a vertical position and an acute angle with respect to a plane of the wings.

Abstract: A dissolvable jet vane (22/30) is a composite structure, having a support frame (38), a plug leading edge (40) connected to the forward edge (42) of the frame (38), and an insulation layer (44) on the side walls of the support frame (38). The dissolvable jet vane materials withstand the pressure and thermal loads associated with missile steering during the first few seconds of rocket boost until the missile attains sufficient speed to use conventional external aerodynamic control fins for steering control. Once control passes to the external fins, the jet vanes rapidly and uniformly dissolve in the exhaust stream. The dissolvable jet vane provides a lightweight, reliable means of removing steering jet vanes from the exhaust stream of a solid rocket motor nozzle.

Abstract: A microthruster having an inverted exhaust system traps burst diaphragm fragments providing a clean exhaust while an exhaust port provides increased back pressure for efficient combustion of a propellant charge in a fuel cell. A converging diverging micronozzle provides a predictable exhaust vector for improved microthrusting well suited for propulsion system on small spacecraft.

Abstract: Disclosed is a fluid vehicle having one or more vertical wings in contact with the fluid for generating a forward motion. This fluid vehicle also has a stabilizing torque system for generating jets transverse to the forward motion for the purpose of counterbalancing any capsizing effect. Preferably, the system is devised to generate up and down jets to the opposite ends of at least one horizontal wing.

Abstract: A jet bomb guidance system in which bi-directional nozzles are fired in a manner to produce force state changes resulting in improved level of control, greater force compatibility and greater efficiency in propellant fuel usage. The system includes four bi-directional nozzles spaced at 90 degree internals in which at least four single nozzles are open at any given instant to maintain a substantially constant gas pressure. The system may be positioned at the nose portion, tail portion, or center of gravity of the bomb.

Abstract: A centerline mounted overbalanced multiple main jet engine configuration. The multiple jet engines are centerline mounted rather than parallel offset. While each jet engine is a “main” engine, capable of safely operating the aircraft in the event of a failure of the other engines, the engines are overbalanced in the sense that at least one of the main engines has substantially greater thrust than the other main engines. All of the main engines operate at critical periods of flight, but only one or the other of the main engines operates at other periods. The configuration of this invention combines the efficiency and performance of a single engined aircraft with enhanced safety advantages.

Abstract: A flow-through thrust takeout apparatus comprises an injection manifold (coupler) mounted to an engine and having a manifold passage. A ball line is attached to the injection manifold, and has a ball line passage fluidicly coupled with the manifold passage. A ball clamp is movably connected with the exterior surface of the ball line. A tank interface is attached to the ball clamp. The tank interface and ball clamp form a socket around the ball line to be movable relative to the injection manifold and the ball line. The tank interface is attached to a fuel tank. The interface member has an interface passage fluidicly coupled with the ball line passage to permit fuel flow from the fuel tank to the engine. A valve is mounted between the engine and the interface passage, and is adjustable to control fluid flow between the tank and the engine. The apparatus transfers the engine thrust from the rocket engine to the fuel tank, and the flow-through passages permit fuel transfer from the fuel tank to the engine.

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: 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: Brush seals formed in hemispherical rings are supported to the end of the convergent nozzle of the each of the clam shells of a multi-axis vector thrust nozzle of a gas turbine engine powering aircraft. The brush seal may be arced or straight and bear against the spherical surface of the collar formed on the end of the tail pipe and is mounted so that high pressure forces the bristles against the backing plate of the seals.

Abstract: The disclosure relates to a low cost and highly accurate precision guided system suitable for use in conventional aircraft launched bombs. The system includes a kit mounted upon the nose of the conventional bomb which replaces the conventional fuse disposed in a fuse well, the kit including guidance electronics controlling a self-contained jet reaction device and GPS P-code receiver electronics. The bombs are readied for discharge by signals broadcast from the aircraft into the bomb bay which transfer initial GPS data and commence operation of a gas generator which powers the jet reaction device.

Abstract: This invention discloses a fluid dynamic system including a fluid medium separated from a solid medium by a solid boundary, one of which media is moving with respect to the other, apparatus for controlling the motion of the moving medium, comprising, a perturbation-producing element at solid boundary, and a drive for cyclically driving the perturbation-producing element to produce cyclical fluid perturbations in the fluid medium sufficient to alter the motion of the moving medium. A method for including a fluid medium separated from a solid medium by a solid boundary in a fluid dynamic system is also disclosed.

Abstract: A method and apparatus for controlling the blowing of compressed air from an aerodynamic structure such as an aircraft wing or helicopter rotor blade and thus controlling the aerodynamic properties of the wing comprises a narrow slot (13) in the upper surface 915) of the structure near its trailing edge (14). Inside the wing (12) is a chamber (23) that is connected to the narrow slot (13) in the wing surface (15). The chamber (23) houses a compressed air conduit (16) for supplying and holding compressed air. A passageway (25) connects the conduit (16) to the slot (13) in the upper surface (25) of the wing (12). The lower wall (27) of the passage (25) has a slit (32) allowing a shutter (31) to move selectively into the passage (25) and obstruct the flow of compressed air through the passageway (25). The shutter (31) is attached to a smart material actuator comprising a piezoelectrical bender (29). When a control voltage is applied to the bender (29), the bender (29) will bend.

Abstract: An improved jet thruster system for use in a helicopter without a tail rotor. A non-rotating outer thruster assembly is attached to the rear of the tail boom which, within it, has a source of low pressure air. The outer thruster assembly has a window on each side. Nested within the outer thruster assembly is an inner thruster assembly with a single window which rotates within the outer thruster assembly in response to commands from the helicopter control system. As the single window in the inner assembly is rotated around to where it overlaps with one or the other of the side windows in the outer assembly, an exit opening is created for the low pressure air which in turn creates a desired side force on the tail boom to counteract the torque created by the main rotor and also to provide yaw control for the helicopter. The interior of the inner thruster assembly contains vanes and an air ramp to efficiently redirect the air flow from axial flow to lateral flow within the inner thruster assembly.

Abstract: A thruster for a helicopter is mounted in a rear portion of a tail boom. Two sets of vanes deflect an airflow stream flowing along the tail boom respectively to opposed sides of the tail boom. Two shutters are pivotally arranged partly around the sets of vanes to leave two openings in respective sides of the tailboom. The shutters are pivoted in sympathy toward each other or away from each other to open/close the respective openings symmetrically and simultaneously such that a geometrical center line of each opening remains static irrespective of the status of the opening.

Abstract: A propeller blade fabricated from composite material having a plurality of pper layers, each upper layer being flexible and having fibers oriented in a first direction. The material further includes a plurality of lower layers, each lower layer being flexible and having fibers oriented in a second direction which is different than the first direction of the fibers of the upper layers. A flexible layer of resistive heating material is disposed between the upper and lower layers. A control and power supply are provided for controlling the amount of electricity delivered to the layer of resistive heating material. The composite material changes its shape upon changing the temperature of the layer of resistive heating material by manipulating the controller.

Abstract: The bi-directional air flow deflector of the present invention efficiently deflects air to the left opening and the right opening, and minimizes any vertical components of force which may be generated. The air flow vector exiting from each of the openings comprises a dominant horizontal force vector rather than a large component of force in the vertical direction. Vertical components of force may be added, if desired. The bi-directional air flow deflector provides reduced transmission torque requirements, and generally comprises a relatively small number of moving parts. A single moving part may be used to deflect air to either the left opening or the right opening, and this single moving part is not exposed to the outside environment and, accordingly, will generally provide reliable functionality. The bi-directional air flow deflector of the present invention is simple in design, comprises a small number of relatively easy to manufacture parts, and can be used to retrofit existing direct jet thrusters.

Abstract: In a missile thrust vector control (TVC) system, two yoke plates are used which surround a pair of pivotably-mounted rocket nozzles. The rocket nozzles pass through corresponding elongated slots disposed on each yoke plate, the elongate slots engaging said rocket nozzles and operating to actuate the movement of the rocket nozzles in accordance with command signals issued by the missile autopilot. The actuator yoke plates are mounted for movement in orthogonal directions, and for rotation in unison. The orthogonal movement of the yoke plates effects corresponding movement of the rocket nozzles in the yaw and pitch directions. Simultaneous rotation of the yoke plates produces a relative twisting of the pivotably-mounted rocket nozzles causing thrust angles to deviate from the missile central axis in opposite directions but equal degree, thereby imparting a roll moment to the missile. In this fashion, any combination of movements of the missile during flight is made possible.

Abstract: An aircraft with automated means to transport. Spherical or one of its segments, without airfoils for lift or guidance. Means for flight are housed within the aircraft. The outer-most sureface is configured to disrupt the air-flow, over its surfaces, in flight. This, to reduce skin-friction and drag coefficients, and mollify heat build-up on the skins outer surfaces as speeds increase to and beyond mach 1. The weight of gas per unit volume, with temperature variations, is the means to reduce the gross-weight and adjust for temperature and weight changes during flight. Propulsion, within the propulsion component, is provided by turbojet engines. They are secured within an inner compression pod and an outer combustion pod. The compression pod and the attached vertical-air-duct, rotate through three hundred sixty degrees, as the means for directional guidance and direct thrust. Augmented power-thrust-tubes extend outward from the combustion pod to the mid-horizontal circumference of the aircraft.

Abstract: Process for guiding an elongated missile, equipped with booster motor, sustainer, power source, control electronics, payload, and search head, from above, upon a target, such as a helicopter, where the missile, after ballistic flight, is braked before the target area by a drogue chute and is diverted into a position that is essentially perpendicular to the earth's surface over the target area so that the search head of the missile, which is suspended from the drogue chute, will be pointed downward, whereupon, after the search head has locked on the target, the drogue chute is separated and the missile is guided to the target by the sustainer, characterized in that, immediately prior to, before, or after the moment of drogue chute deployment, a lateral motor, located in the center of gravity of the missile, is turned on so that, first of all, in order to accelerate the tilt-off of the missile into the vertical, there is generated a force that is added vectorially to the force of gravity and that thereupon one

Abstract: A ram wing vehicle comprises a main structure extending between a nose end and a tail end, including an aerodynamic lifting body having an aspect ratio less than approximately 1.0 and extending between a leading edge and a trailing edge. The ratio of the thickness of the lifting body intermediate the leading edge and the trailing edge to the length of the chord thereof is greater than approximately 1:8. A propulsion source is provided adjacent the nose end for generating an efflux and for directing the efflux beyond the tail end in a direction away from the nose end. A directional control mechanism is positioned adjacent the nose end for turning the vehicle about the yaw axis into a curve having a center and so vectoring the efflux from the propulsion source as to direct the efflux to the outside of the turn and the nose end toward the center of the curve.

Abstract: A variable area exhaust nozzle includes a divergent flap joined to an outer flap for allowing relative rotation and translation therebetween. An articulated fairing joins the aft ends of the divergent and outer flaps for providing aerodynamic streamlining. The fairing includes outer and inner shrouds, with the outer shroud being pivotally joined to the outer flap, and the inner shroud being fixedly joined to the divergent flap, and pivotally joined to the outer shroud for allowing relative rotation and translation therebetween.

Abstract: A stable and highly maneuverable lighter-than-air aircraft is provided. The aircraft includes a body portion which is supported beneath a balloon portion by a stem or axle. The balloon is fillable with a lighter-than-air gas and is sized to accept sufficient amounts of gas to make the aircraft buoyant. The balloon portion is rotationally fixed to the axle and the axle is rotationally journaled in the body. Thus, the balloon portion can rotate relative to the body portion and the body can selectively be rotated relative to the axle. A motor is housed in the body portion and is operable to propel the aircraft in a desired direction. The aircraft is operated such that the balloon portion rotates above the body portion without rotating the body portion. The rotation of the balloon portion provides stability to the aircraft and the ability for the body portion to rotate about the axle enables the aircraft to be highly maneuverable.

Abstract: A method and apparatus for controlling the blowing of compressed air from an aerodynamic structure such as an aircraft wing or helicopter rotor blade and thus controlling the aerodynamic properties of the wing comprises a narrow slot (13) in the upper surface (15) of the structure near its trailing edge (14). Inside the wing (12) is a chamber (23) that is connected to the narrow slot (13) in the wing surface (15). The chamber (23) houses a compressed air conduit (16) for supplying and holding compressed air. A passageway (25) connects the conduit (16) to the slot (13) in the upper surface (15) of the wing (12). The lower wall (27) of the passage (25) has a slit (32) allowing a shutter (31) to move selectively into the passage (25) and obstruct the flow of compressed air through the passageway (25). The shutter (31) is attached to a smart material actuator comprising a piezoelectrical bender (29). When a control voltage is applied to the bender (29), the bender (29) will bend.

Abstract: A nozzle for use on opposing ends of the rotor of a jet powered tri-mode aircraft is disclosed. The nozzle includes two thermally-controlled doors, which are moveable between an open configuration where hot jet engine exhaust is vented therethrough to propel the rotor in a helicopter mode, and a second closed configuration where the two doors are tightly sealed to provide a stable aerodynamic surface for the rotor when the jet powered tri-mode aircraft is operating in an airplane mode. The two doors are thermally-activated by an internal surrounding temperature, such that they remain open by the hot jet engine exhaust passing thereby in the helicopter mode, and remain shut by resulting cooler air when the hot jet engine exhaust is not routed by the two nozzle doors.

Abstract: The invention provides alternative flight control methods and structures which can prevent a crash of a passenger or a cargo aircraft under stall/spin and adverse flight conditions, failing Conventional ?aerodynamic! Flight Control ?CFC!, low landing speeds, asymmetric icing and partial loss of propulsion. That air-safety capability is provided by integrating roll-yaw-pitch engine-nozzle-nacelle thrust vectoring flight control ?TVFC! retractable/rotatable vane-doors, collectively operated in individual TVFC-sectors, with modified ?conventional! thrust-reversing ?TR! door-structures ?in one method!, or with novel retractable/rotatable TR vane-door sectorial structures ?a second method! to form various TVFC/CFC/TR systems. The methods and structures are intended for transport jets, except one configuration which is intended for turbo-prop transports. Another configuration replaces heavy and complex conventional TR doors and TR-nacelle-grids with an integrated, simpler and lighter TVFC/CFC/TR-systems.

Abstract: A flight vehicle which can be joined and firmly strapped to a load, the load being either a human pilot (P) or a remote-controlled pilot. The flight vehicle comprises a supporting frame for attaching to the load, a driving arrangement (100) incorporating a piston engine, and which is connected directly to the shrouded propeller (200) by means of a rotating drive shaft (108) for the purpose of setting up an air stream, also at least two jet pipes (300) which open into outlet nozzles (304, 305) mounted laterally alongside the load or the human pilot (P), whereby the said outlet nozzles can be adjusted to change the direction of the discharged air stream. It is by means of the outlet nozzles (304, 305) that the lift force is set up; this latter force enables the human pilot to lift off the ground to make hover or translatory flights.

Abstract: First and second pylon flaps are located on aft portions of the first and second jet engine pylons, respectively. The first and second pylon flaps are moveable between retracted pylon flap angular orientations and extended pylon flap angular orientations. The first and second pylon flaps can assume only fully retracted angular orientations and fully extended angular orientations. When the T-tailed aircraft enters into a deep stall condition, the pilot will more than likely push the control column forward to its maximum position. This full forward movement of the control column commands the first and second pylon flaps to assume fully extended angular orientations. A first pylon flap controller controls the first pylon flap to move between the fully extended and fully retracted angular orientations, and a second pylon flap controller controls the second pylon flap to move between the fully extended and fully retracted angular orientations.

Abstract: An aircraft for vertical or short take off and landing operations having two main lift nozzles, both positioned at or near the aircraft center of gravity utilizes one or more jet screen nozzles, arranged in a variety of shapes and combinations, discharging bypass air from a position forward of the center of gravity, and a variable pitch nozzle discharging engine exhaust gas mixed with bypass air from a position aft of the center of gravity, to achieve pitch control while airborne in vertical take off or landing mode. The jet screen nozzle also prevents or reduces ingestion of mixed hot exhaust gas and bypass air discharged through the main lift nozzles. The jet screen nozzle further prevents or reduces ingestion of foreign object debris disturbed by the vertical lift discharge flowing from the main lift nozzles.

Abstract: An airship capable of vertical and horizontal flight and able to make right angle turns is preferably of nearly neutral buoyancy and comprises two gas bags, the lower of which is toroidal in shape and surrounds a centrally located engine that has a downwardly facing inlet. Upwardly directed thrust from the engine is redirected by a gate valve arrangement into a manifold of ducts, each of which passes between the upper and lower gas bags to a respective outlet or nozzle adjacent the periphery of the aircraft. To fly the aircraft, a pilot uses the cable-operated valve arrangement to manage the distribution of thrust from the engine into selected ones of the ducts to provide thrust in a desired direction. Preferred pilot operated controls comprise a foot pedal and a rotatable steering wheel mounted on a pedestal hingedly attached to the gondola of the aircraft for fore and aft pivoting motion.

Abstract: A failsafe nozzle actuating system for an aircraft gas turbine engine axisymmetric vectoring exhaust nozzle has a vectoring ring operably linked to a plurality of pivotal flaps which are circumferentially disposed about a nozzle centerline and bounding an exhaust gas flowpath in the nozzle. The failsafe nozzle actuating system has at least two independently operable first and second vectoring actuating systems including first and second groups of actuators operably connected to the vectoring ring and first and second failsafe control means to control power to the first and second groups of actuators, respectively. The first group of vectoring actuators is interdigitated with the second group of second vectoring actuators around the nozzle. Either of the two groups of actuators are operable to actuate the nozzle when the other group is failsafed.

Abstract: A duct fixed to a vehicle propelled through an ambient fluid medium is innally provided with spaced channel passages from which the fluid medium is ejected under pressure tangentially of local duct surfaces through Coanda affected slots at the trailing edge of the duct from which only the ejection of the fluid medium occurs. The supply of the pressurized fluid medium under selective control is limited to different angular segments of the channel passages in order to modify the flow stream through the duct so as to perform certain functions such as thrust control and steerage control effects enhancing vehicle maneuverability.

Abstract: A VSTOL aircraft powerplant comprises a gas turbine engine (1), a chamber (2) for receiving exhaust from the turbine section of the engine (1), and a jet propulsion nozzle (3) and vertical lift nozzles (4, 5) connected to the chamber (2). Blocker doors (6, 7) are provided for blocking flow of exhaust from the chamber (2) and thus diverting the flow to the vertical lift nozzles (4, 5). A high pressure air curtain is provided by ducts (9) to control th area of the ports to the vertical lift nozzles (4, 5). Control means coordinate and control the operation of the blocker doors (6, 7) and the air curtain to vary the total efflux between three configurations, namely all efflux occurrng through the jet propulsion nozzle (3) for wing-borne flight; all efflux occurring through the vertical lift nozzle (4, 5) for hovering; and some efflux, which is steplessly variable, occurring through both the vertical lift nozzles and the jet propulsion nozzle for transition between wing-borne and jet-borne flight.

Abstract: An airplane steering system which permits 180 degree turns with minimum tire scrub. The system involves steering of both the nose landing gear and the front and rear wheels of both main landing gear each consisting of three inline wheels; thus, the center of turn is placed between the main gears and allows the airplane to make 180 "pirouette" turns.

Abstract: The invention is an exhaust duct system for an aircraft, the aircraft having at least one turboprop propulsion system mounted on the wing within a nacelle, the propulsion system having a circular shaped exhaust port generally aligned with the longitudinal axis of the aircraft. In detail, the invention includes a generally shallow S shaped duct having a longitudinal axis aligned with the longitudinal axis of the exhaust port. A duct includes a circular shaped inlet section, a rectangular exhaust port section and a transition section therebetween. The inlet has a larger diameter than the exhaust port of the propulsion system and is positioned there about. The inlet includes a plurality of flexible finger like members extending inward such that they are in slidable engagable with the external surface of the exhaust port.

Abstract: A system is disclosed for controlling the external flow passing along the external surface of an aircraft such as the tailboom of a helicopter. A fan blows air into a cavity within a surface, and the air exits the surface through one or more axially oriented slots. A ramp structure is positioned within the cavity and upstream of each slot, and a set of fence structures are mounted in each slot and spaced from each other as well as from the ramp structure. The ramp and fence structures trip the airflow which then couples to the downstream side of the ramp and fence structures, thus eliminating the axial airflow component adjacent to the slot, and exits the slot in a direction normal to the axis. The airflow exits the slot in a direction tangential to the external surface and generally parallel with the external flow, resulting in deflection of the external flow and generating lift which is used to augment antitorque control in the helicopter implementation described.

Abstract: A thrust-vectoring actuation system for rocket nozzles in provided with force attenuation means in order to limit transient loads which the nozzle and associated structure experience during engine startup and shutdown.

Abstract: A system for stabilizing an aircraft includes sensors positioned and disposed at predetermined locations on the aircraft and structured for sensing external forces acting on the aircraft at the sensor locations as a result of rapid changes in atmospheric conditions such as those associated with air turbulence and wind shear. A computer processor receives data from the sensors and activates one or more thrust generators positioned at predetermined locations of the aircraft to counteract the external forces and maintain the desired attitude and stability of the aircraft.

Abstract: A thrust-vectoring actuation system for a rocket nozzle is provided with a force sensor to enable detection of transient loads during startup and shutdown of a rocket engine. A motor responds to transient loads in excess of a predetermined threshold to drive the rocket nozzle in a direction of compliance with the transient loads.

Abstract: Apparatus and method for airflow vectoring control for an airfoil, a two dimensional jet, and the like. An airfoil or jet with a blunt open edge and a suction system for sucking air into the open edge. A blower system for blowing air out through the open edge. A control for changing the direction of flow through the open edge. A baffling arrangement for changing the magnitude and distribution of flow across the open edge.

Abstract: The spacecraft comprises a fuselage (1), a wing (2), a power unit incorporating two liquid-propellant launching rocket engines (3), two liquid-propellant boost rocket engines (4), six transverse-thrust rocket engines (5) located in the spacecraft fuselage (1) on a rotatable ring (6), solid-propellant emergency deceleration rocket engines (7), and solid-propellant additional boosting rocket engines (8), a payload compartment (9), a crew compartment (10), a tail unit with two vertical fin struts (11) a bottom tailplane (12), and a top tailplane (13). The fuselage (1) is provided with a movable center conical body (14). The spacecraft landing gear has a swivelling tail wheel (21). The crew compartment (10) is interposed between the fin struts (11) under the top tailplane (13). The spacecraft is provided with an orbital maneuvering system whose final control elements are in fact low-thrust rocket engines (22) and (23), and gyrodynes.

Abstract: An actuation system for controlling the steerable nozzle of a missile or like vehicle is combined with an aerofin control system, both of which are driven in unison by associated drive motors and gear assemblies, one set for each aerofin. The nozzle steering system comprises two essentially identical yoke plates mounted along a plane generally transverse to the missile axis and oriented orthogonally relative to each other about the missile axis for pivoting the nozzle through mutually orthogonal axes, thereby achieving omni-directional steering. The yoke plates are coupled at opposite ends to pinion gears which are driven by the same gear assemblies which drive the associated aerofins. The arrangement permits common directional control of the steerable nozzle and the aerofins while maintaining the nozzle in a neutral direction when the aerofins are rotated to a missile roll control mode.

Abstract: A thrust maneuver system for steerable vehicles comprising a plurality of thrusters of varying impulsive force, some of which provide a base force, and others varying multiples of the base force. The forces may be used additively or subtractively to obtain a desired force for any given maneuver.

Abstract: The invention is a propulsion system for a lighter-than-air vehicle, the vehicle having a longitudinal, lateral and vertical axis. In detail, the propulsion system includes a thrust producing assembly rotatably mounted on the vehicle, the assembly rotatable about an axis of rotation in a plane at an acute angle to the vertical axis of the vehicle, the assembly rotatable in the plane from a position wherein the thrust axis of the assembly is aligned with the longitudinal axis to a position at least plus or minus ninety degrees thereto. A powerplant assembly is coupled to the thrust producing assembly to provide power thereto. The powerplant assembly includes a fuel efficient powerplant assembly mounted within the vehicle having sufficient power for cruise conditions, the fuel efficient powerplant having a output drive shaft coupled to the thrust producing assembly. A light weight, high power powerplant assembly is mounted directly to the thrust producing assembly having sufficient power for docking conditions.

Abstract: An aircraft comprises a hollow elongated body having a plurality of short wings projecting outwardly form the body in a vertically stacked array. The wings transverse substantially the entire length of the body. Engines with diameters substantially equal to the maximum width of the wings are mounted behind the wings, with at least one engine mounted on either side of the aircraft. Honeycomb structures mounted behind each engine cause the air thrust rearward by the engines to be directed as a smooth laminar flow of air. Air deflectors mounted behind the honeycomb structures deflect the air thrust rearward by the engines. A steering mechanism can orient the deflectors: (i) in a downward direction to provide an upward lifting force on the aircraft, or (ii) in an upward direction to provide a downward force on the aircraft, or (iii) in a port or starboard direction to steer the aircraft. Landing gear is attached to the bottom of the aircraft. Resilient structures are used to absorb shock in case of a crash.

Abstract: A device for actuating a movable mechanical member, using a fluid source such as a gas generator of a missile, of the type having a controllable distributor connected to the source. The device includes a body (11) provided with a distributor (12), the body being coupled, via an inlet orifice (17), to a fluid source; a first conduit (15) capable of connecting the inlet orifice to a chamber (16) of the distributor; an actuator cylinder (14) arranged in the body and including a first chamber (19A) and a second chamber (19B) which are coaxial and separated from each other by a sliding piston (31) connected to a rod (31B) which projects externally in relation to the body in order to be linked to a mechanical member.

Abstract: An unmanned aerial vehicle incorporates a single engine with bifurcated exhausts which are coupled to side mounted rotating nozzles through a swivel joint. Jet deflection means are mounted to the end of the rotating nozzles to achieve additional degrees of freedom for the aircraft.

Abstract: A superagile tactical fighter aircraft and a method of flying it are disclosed. The superagile aircraft is characterized by articulatable air inlets, articulatable exhaust nozzles, highly deflectable canard surfaces, and control thruster jets located around the nose of the fuselage, on the top and bottom surfaces of the propulsion system near the exhaust nozzles, and on both sides of at least one vertical tail. The method of operating the superagile aircraft comprises the step of articulating the air inlets and exhaust nozzles, deflecting the canard surfaces, and vectoring the thruster jets so that supernormal flight is attained. Supernormal flight may be defined as flight at which the superagile aircraft operates at an angle of attack much greater than the angle of attack which produces maximum lift. In supernormal flight, the superagile aircraft is capable of almost vertical ascents, sharp turns, and very steep descents without losing control.