Abstract: An articulating and telescoping duct is provided for use in a helicopter reaction drive flow path for ducting the exhaust and/or bypass gases from the aircraft engine into the flow ducts of the rotor blades. In a preferred embodiment the telescoping duct comprises a tubular member having a bead formed at each end. Each of the beads has an outside surface formed into a spherically curved sector that is centered radially about the axis of the tubular member. The receiving duct at one end comprises a complementary spherical bore that seals against and retains the spherical outside surface of the tubular member while permitting the tubular member to articulate relative to the receiving duct. The receiving duct at the other end comprises a complementary cylindrical bore that seals against the spherical outside surface of the tubular member while permitting the tubular member both to articulate relative to and telescope in and out of the cylindrical bore.

Abstract: A helicopter aircraft with an upper hollow center circular plenum in gaseous communication with a plurality of hollow hinged attached rotor blades. Below the plenum and in gaseous communication with it are two fan jet engines whose gaseous output can be inputted to the plenum and their attached hollow rotor blades through a operator controlled valve system. This same valve system can be adjusted to completely or partially by-pass the plenum and discharge the jet engines' gas to a common rear rudder located on the aircraft's to provide directional control to the aircraft when in flight. The plenum is shaped lenticular in cross section similar to an airplane wing to provide a lifting body when the helicopter is in forward flight.

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 helicopter rotor seal for gas-driven helicopters wherein the rotor is rotatably driven by a compressed air jets at the tips of the rotors directed rearwardly with respect to rotor rotation. A non-rotatable mast extends vertically from the helicopter fuselage including a concentric bore for communication of compressed air therethrough. Positioned at the upper extremity of the mast, above the rotor blades, is a rotatable plenum for distributing compressed gas to the helicopter's respective rotor blades.

Abstract: A circulation control aerofoil having an internal chamber for receiving during operation air for exhaust through a circulation control air exhaust slot defined by spaced-apart slot lips is provided with a plurality of actuators of electrically deformable material adapted during operation to cause local bending of the aerofoil structure to which they are attached to selectively adjust the width of the air exhaust slot. The actuators may be piezo-electric actuators.

Abstract: A rotary wing aircraft with rotor blades mounted on a rotor head and with reaction drive. The rotor blades have hollow interiors and are provided on their trailing edge with at least one outlet opening for compressed air supplied via the rotor head. Such rotor head may include an air suction region in which there is mounted a suction device having a pressure side connected to the hollow interiors of the rotor blades.

Abstract: Control law system for the collective axis, as well as pitch and roll axes, of an X-Wing aircraft and for the pneumatic valving controlling circulation control blowing for the rotor. As to the collective axis, the system gives the pilot single-lever direct lift control and insures that maximum cyclic blowing control power is available in transition. Angle-of-attach de-coupling is provided in rotary wing flight, and mechanical collective is used to augment pneumatic roll control when appropriate. Automatic gain variations with airspeed and rotor speed are provided, so a unitary set of control laws works in all three X-Wing flight modes. As to pitch and roll axes, the system produces essentially the same aircraft response regardless of flight mode or condition. Undesirable cross-couplings are compensated for in a manner unnoticeable to the pilot without requiring pilot action, as flight mode or condition is changed.

Abstract: A circulation control rotor system for aircraft in which compressed air is directly supplied at generally constant pressure to plenums in the rotor blades and discharged through area controlled slots, the area controlling means involving camming surfaces and being actuated by cyclic, collective, aircraft vibration and flight stability inputs.

Abstract: The present invention relates to a circulation flow control rotor system for an aircraft which includes rotor blades provided with slit shaped blower nozzles further comprising control devices for obtaining a cyclic or multicyclic or collective rotor blade angle control under utilization of individual pressure gas flow from a pressure chamber to the nozzle slits; further including deformable control members which are going to be deformed in accordance with certain rules underlying the requisite control.

Abstract: A circulation control aircraft rotor blade of advanced composite material having a spanwise Coanda surface 16 and a plurality of spanwise extending flexible panels 18 cooperating with the Coanda surface to define slots for the discharge of compressed air from a duct 14 within the blade with each panel having flexure means 34 associated with attaching means 24 and limiting means 38 for establishing a slot opening preload and a slot maximum opening and with limiting means 38 providing structural equilibrium and reduced bending moments in the inboard corners of the air duct.

Abstract: A device for producing a force when in a moving fluid, such as air or water, and a method for using said device. The device may be placed in a fluid moving in a first direction for producing a force in a second direction, which is substantially transverse with respect to the first direction. The device avoids the use of large sail areas needed where the force derived from wind is proportional to said area. The device according to the invention comprises an elongated body having in cross-section a rounded symmetrical profile, which defines an elongated and rounded leading portion whose thickness increases from the front to the rear and a rounded trailing portion whose thickness decreases from the front to the rear, the leading portion being longer than the trailing portion. The device according to the invention is also provided with at least one flap, which projects from the body and which is located on the trailing portion of the profile.

Abstract: A circulation control aircraft rotor blade having a spanwise Coanda surface 16 and a plurality of spanwise extending flexible composite material panels 18 cooperating with the surface to define slots for the discharge of compressed air from within the blade with each panel having first flexure means 60 associated with screw adjustments 36 for establishing a slot opening preload and second flexure means 62 associated with screw adjustments 38 for establishing a slot maximum opening.

Abstract: A high wing, twin jet gyrodyne having air jet reaction, contrarotating rotors powered with bypass air from twin turbofan engines. Tail pipes from the turbofan engines are disposed parallel to and at opposite sides of a longitudinal duct for discharging bypass air rearwardly. Control valve means can control supply of bypass air selectively to the hollow rotor mast for driving the rotors and to the longitudinal air discharge duct. The aft portions of the tail pipes and of the air discharge duct are connected by a horizontal stabilizer and rudders are located in the slipstream discharged from the tail pipes and the air discharge duct. The wings have drop tip sections providing flotation outriggers in their downwardly projecting positions.

Abstract: X-wing aircraft employ a rigid rotor-wing utilizing symmetrical circulation irfoils. The rotor is driven mechanically, and lift is achieved by modulation of air circulation about the base airfoils. This is accomplished by blowing compressed air through trailing edge openings in the rotor blades, and controlling the amount of air being ejected through those openings. By cyclically modulating the amount of ejected airflow, cyclic lift control is obtained. Likewise, by collectively controlling the ejected airflow collective lift control is obtained. One reason for the lack of popularity of circulation control rotor systems is concern over a loss or air pressure resulting from a damaged rotor blade. The damage to a rotor blade, such as ballistic damage, can cause the entire plenum pressure to be vented through that damaged blade. The result is a loss of pneumatic control, not only of that blade, but control of all rotor blades.

Abstract: A circulation controlled airfoil has a body structure with leading and trailing ends and upper and lower surfaces extending therebetween, and a cylindrical member disposed along the trailing end of the body structure between the upper and lower surfaces thereof so as to form a rounded, blunt trailing edge surface on the airfoil. A first blowing jet slot is defined between the outer surface of the cylindrical member and the trailing end of the body structure adjacent its upper surface. A second blowing jet slot is defined in a tubular wall of the cylindrical member. The latter member can be rotated to vary the distance of the second jet slot from the first jet slot and thereby adjust the point of separation of air flow along the airfoil from the outer surface of the blunt trailing edge surface formed by the cylindrical member. In such manner the lift generated by the airfoil can be optimized by providing blowing that is specifically tailored to given flight conditions.

Abstract: Quad-redundant signal processors in a flight control computer control valves to modulate airflow in a circulation control rotor system. The valves are arranged in a series and each valve is responsive to two signal processors. Loss of a valve occurs when both signal processors for that valve fail. A first valve, and every fourth valve in the series thereafter is responsive to a first signal processor and a third signal processor. The next valve in the series, and every fourth valve in the series thereafter is responsive to a second signal processor and a fourth signal processor. The third valve in the series, and every fourth valve in the series thereafter is responsive to the first signal processor and the fourth signal processor. The next valve in the series, and every fourth valve in the series thereafter is responsive to the second signal processor and the third signal processor.

Abstract: Aircraft engine exhaust is mixed with air and fuel and recombusted. Air is drawn into the secondary combustion chamber from suction surfaces on wings. Exhaust of the secondary combustion chamber is blown over wing and fuselage surfaces.

Abstract: Mechanical collective pitch control system for a circulation control rotor system aircraft utilizing an axially moveable pneumatic system plenum 32 in the collective pitch control system.

Abstract: A power plant having a fluid powered flywheel is disclosed. The flywheel comprises internal cylinder spaces which extend radially outwardly from a central region of the flywheel but which curve in a particular circumferential sense about the axis of the flywheel. Helical structures are disposed within the cylinder spaces to define respective helical flow paths through the cylinder spaces. Power fluid is delivered to a central region of the flywheel for entry into the cylinder spaces. Exhaust ports are provided to extend between the outer perimeter of the flywheel and the radially outer end of each cylinder space so that the exhausting fluid is jet discharged. Pressurized fluid is delivered from a reservoir containing a gas-over-liquid power source. An impeller driven by the flywheel collects the fluid discharged from the perimeter of the flywheel and returns it to the reservoir.

Abstract: A non-moving fluid thrust deflector and force augmentor is disclosed for aerodynamic and hydrodynamic vehicles and devices. When the deflector is utilized in an aerodynamic application and in conjunction with a thrust producer and a plenum, upon pressure initiation within the plenum, a jet sheet issues and remains attached to a specially designed wing having a rounded trailing edge by balancing reduced static pressure with centrifugal force, and thus provides a controlled resultant force or thrust in some direction other than that corresponding to the original flow. Upon application to hydrodynamic vehicles, the deflector is placed in the propulsor stream and provides turning or pitching forces to the vehicle without any deflection of itself. These applications require no mechanical moving components to deflect or augment the thrust or force, and thus yield considerable reductions in weight and complexity.

Abstract: A reactive impeller for pressurizing hot flue gases. The impeller has a hub and blades exposed to the gases. The hub and blades are cooled by an internal cooling fluid, which is expelled from nozzles on the blades to drive the impeller so as to propel and pressurize the gases.

Abstract: A propulsion system for an underwater vehicle includes a solid propellant gas generator producing gas which drives a gas turbine. The turbine drives one, or alternately two, centrifugal pumps which induct sea water from intake ports and supply it under pressure through a passage to passages leading to tip nozzles in the blades of a propeller which drives the vehicle, thereby using the reaction force from the tip nozzles to drive the propeller. Exhaust gas, after driving the turbine, is conducted through a conduit and to an annular chamber where it is cooled by means of a spray of sea water, thus condensing the steam present and reducing the volume of exhaust gas.

Abstract: A non-moving fluid thrust deflector and force augmentor is disclosed for aerodynamic and hydrodynamic vehicles and devices. When the deflector is utilized in an aerodynamic application and in conjunction with a thrust producer and a plenum, upon pressure initiation within the plenum, a jet sheet issues and remains attached to a specially designed wing having a rounded trailing edge by balancing reduced static pressure with centrifugal force, and thus provides a controlled resultant force or thrust in some direction other than that corresponding to the original flow. Upon application to hydrodynamic vehicles, the deflector is placed in the propulsor stream and provides turning or pitching forces to the vehicle without any deflection of itself. These applications require no mechanical moving components to deflect or augment the thrust or force, and thus yield considerable reductions in weight and complexity.

Abstract: A multi-purpose mono-element airfoil is disclosed for aerodynamic and hydrodynamic vehicles and devices. The multipurpose mono-element highlift airfoil when utilized in an aerodynamic application provides a combined no-moving-parts high lift and cruise airfoil which in conjunction with a plenum, upon pressure initiation, causes pressurized air to issue from a slot tangent to the airfoil surface and remains attached to the airfoil's shaped trailing edge, providing a controlled resultant force of thrust. Upon application to hydrodynamic vehicles, the multi-purpose mono-element airfoil is placed in the freestream and provides turning or pitching forces to the vehicle without any deflection of itself or any mechanical components.

Abstract: This disclosure is directed to a flexible fluid conduit means for directing fluid from a pressure source to a propeller of a ship for minimizing cavitation. The conduit is formed of split annular rings adapted to be mounted over a propeller shaft, the rings being interconnected to form passages for directing air pressure from the A-bracket through relative rotating seal members and into the body of the propeller. The disclosed interconnection of the annular rings permits substantial axial and bending movement of the propeller shaft without loss of air. Being submersed, the conduit is hydraulically balanced such that the force of water pressure tending to open the seal members is always less than the force tending to close the seal members.

Abstract: A turbine designed for use with steam contaminated with corrosives, the turbine has a plurality of turbine wheels with a peripheral rim around which are symmetrically arranged a plurality of nozzles; steam supplied to the center of a wheel is directed outward at an angle from a tangent to the periphery of the rim, the wheels having a cooperating housing for redirecting the steam from the periphery of one wheel to the center of the next adjacent wheel, the turbine being constructed for directing wear primarily in the stationary housing and/or components which are inexpensive and easily replaceable.

Abstract: A circulation control airfoil having an edge slot formed by upper and lower uct panels. A plurality of struts are spaced along the length of the edge slot and are adjustably attached to the upper and lower duct to maintain the edge slot height. A reinforcing saddle is provided at each attachment position on the panels for distributing load applied to the struts over a large area of the duct panels. Each strut is provided with a differential lead thread system which provides high resolution adjustment capability for the edge slot.

Abstract: This fluid valve is mounted in the hub of a circulation control helicopter otor to modulate the flow of air through the hub to the blowing slots on the leading and trailing edges of the blades. The valve independently controls the air pressure to the leading edge slots and trailing edge slots so as to vary the lift produced by each rotor blade as a function of its azimuth angle. The periodic waveforms of the air pressure provided to the leading edge slots and trailing edge slots in the blades are controlled by a combination of flow regulating cams and programming rings.

Abstract: A circulation controlled rotor blade which reduces rotor flutter by introing a laminar flow over the trailing edge. A trailing edge structure has a deformable tube to control a spanwise slot formed by the juxtaposition of an upper trailing edge lip over the deformable tube. The laminar flow is created by compressed fluid directed through the rotor blade and through the slot.

Abstract: A vertical take-off and landing aircraft features an improved tail-lifting rotor and rotor directional controls. A new type of suction pressure jet-mechanical-flap rotor blade with a higher coefficient of lift is employed. The aircraft has a mechanism for loading and unloading passengers and a more efficient method of handling baggage and cargo. A much more efficient utilization of space in the fuselage is achieved through a reduced height passenger space and overhead rotor storage compartment.

Abstract: The present invention relates to a hydrodynamic transmission for ship propulsion comprising a prime mover driving an axial flow pump in combination with an open, water-powered turbine for driving propeller blades. The power plant and the propeller are not mechanically connected, and power is transmitted through the hydrodynamic transmission. The invention also provides for a thrust-reversing mechanism specially adapted to the hydrodynamic transmission described herein.

Abstract: This invention is for rotating machines of all types such as helicopters, propellers, compressors, to be equipped with slotted tube or a tube with series of holes extending outwardly in the spanwise direction near the trailing edge of a jet-circulation-control rotor-blade tip for blowing jets of fluid in the direction opposite to the lift of the blade. Thereby achieving flow in the form of a jet sheet to abate, diffuse the undesirable blade-tip vortices and to increase the overall efficiency of the machine.

Abstract: A control system for rotary wing aircraft having a circulation controlled tor is provided. Two axial flow air compressors driven from the engine input shaft provide an air flow which is ducted to the rotor blades through a bifurcated duct and a non-rotating air plenum and released through spanwise slots in the blades. Damping is accomplished by a conically shaped diverter valve in the air plenum and a butterfly valve adjacent the air compressors. Aircraft stability is achieved through a gyro coupled to the rotor shaft which integrates pilot controlled input with rotor cyclic flap moment input.

Abstract: An airflow control valve for a circulation control rotor helicopter blade wherein the airflow path is equally distributed about the closure element so as to prevent the generation of unbalanced pressure forces.