Abstract: This disclosure provides a solar rechargeable aircraft that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. Travelling at relatively slow speeds, and having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn. Each of five sections of the wing has one or more engines and photovoltaic arrays, and produces its own lift independent of the other sections, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface. The aircraft is capable of a top speed of about ninety miles per hour, which enables the aircraft to attain and can continuously maintain altitudes of up to sixty-five thousand feet.

Abstract: A special purpose helicopter based on an existing airframe, power train, and engine, modified to provide greatly enhanced performance, payload, speed and maneuverability. The modification consists of modifying an original helicopter universal transmission center case for installation of twin drive shafts, at 180.degree. apart, and mounting a second engine on the airframe structure, at 180.degree. to the first engine, and forward of the transmission. An exhaust system for the second engine is split into two units for directing the exhaust outwardly and upwardly.

Abstract: An aircraft (10) including a stowable, wingtip mounted, vortex turbine (30) for dissipating or extracting energy from a lift induced vortex (28) emanating from the aircraft (10) is provided. The vortex turbine (30) includes a first and a second array (38, (40) of blades (32a,b) (34a,b) extending respectively from a first and a second hub section (32), (34). Hub sections (32), (34) may be independently pivoted about a common axis of rotation (36) to a stowed position for landing, take-off, or ground operation, whereat none of the blades (32a,b) (34a,b) extend below a minimum ground clearance of the aircraft, or beyond a maximum horizontal extension of the wing (16). In flight, the hub sections (32), (34) may be deployed and the pitch of the blades adjusted to maximize dissipation of the lift induced vortex (28), thereby minimizing drag and providing improved safety for other aircraft flying through the wake of the aircraft (10) producing the vortex (28).

Abstract: A passive cooling system for aircraft auxiliary power units having an intake duct extending between an inlet opening and the compartment in which the auxiliary power unit is positioned. An inlet scoop is positioned in the intake duct for diverting a portion of the airflow in the intake duct through an outlet in a wall of the intake duct. A vacuum duct is positioned near an oil cooler for the auxiliary power unit, and an aspirator is operatively positioned between the vacuum duct and an exhaust passage of the auxiliary power unit. The aspirator creates a low-pressure region in the vacuum duct that draws the diverted air out of the outlet and through the oil cooler.

Abstract: A ram air turbine power system is provided with a deployable ram air turbine mounted in-line with a power supply unit such as an electrical generator and/or an hydraulic pump. The ram air turbine includes a turbine shaft supported for rotation by bearings within a generator housing, wherein a rear end of the turbine shaft and a generator shaft are supported by a common bearing, and further wherein the forwards ends of the turbine and generator shafts are supported by a pair of bearings separated by a resilient bearing mount. In addition, the in-line ram air turbine and related power supply unit are supported from a hollow strut with hydraulic and electrical lines and related mechanical linkages extending therethrough.

Abstract: A supersonic airplane having four or two supersonic engines and one or more boost engines. During take-off and initial climb the supersonic engines are operated at a lower thrust setting within acceptable noise limits, and the subsonic engine(s) is operated to provide boost thrust to enable the airplane to operate a take-off and climb. During cruise, the subsonic engines are in a nonoperating mode, and the supersonic engines alone provide the thrust for supersonic operation. In one embodiment, one subsonic engine is deployed on one side of the fuselage during the operating mode. In a second embodiment, there are two subsonic engines deployed on opposite sides of the fuselage. In another embodiment, a single subsonic engine is installed inside the fuselage.

Abstract: A novel, high-altitude, solar powered aircraft, capable of staying aloft at high altitudes for many months or even years to conduct around the clock surveillance and/or reconnaisance, includes a forward wing with solar energy capturing cells, a rear wing, inflated pontoons for keeping the aircraft aloft, suspension wires attached to the pontoons, a gondola suspended from and connected to the wires, control apparatus for moving the gondola along the wires, shifting the weight of the aircraft and thereby enabling banking to optimize exposure of the solar cells to the rays of the sun. The gondola preferably contains a sensor suite, power generating and storage apparatus, and synthetic aperture radar imaging apparatus.

Abstract: An aircraft subsystem provides the aircraft with all its electrical and conditioned air requirements without requiring the extraction of either shaft power and/or pressurized air from the aircraft's main engines. At the core of this subsystem are two rotating assemblies journaled on non-oil lubricated bearings to a housing. One assembly includes a cooling turbine, a starter/generator, a core compressor, and a high pressure stage of a two stage axial turbine, all mounted on a single shaft. A combustor is disposed between the core compressor and the turbine. The other assembly is comprised of the low pressure stage of the axial turbine coupled to a load compressor via a second shaft. The high pressure turbine stage and cooling turbine are sized to drive the core compressor and starter/generator which provides all the aircraft's electrical needs both on the ground and inflight.

Abstract: The difficulty and expense of fabricating a support strut for a ram air driven turbine are reduced by providing an axially opening channel in a central portion of the strut. Blockage of a portion of the airstream flowing through the ram air turbine and past the strut is reduced by extending the axially opening channel through the entire axial length of the strut. Apparatus for converting or transferring power generated by the ram air turbine to a point of use, such as an aircraft, is routed through the axially opening channel, thereby allowing convenient access to such apparatus. A strut design is provided which may be readily manufactured as a single unitary structure from a variety of metallic and non-metallic materials including fiber reinforced composites.

Abstract: An apparatus for generating or recovering energy on board an aircraft effectively utilizes the cabin exhaust air stream, which has a high thermal energy and a differential pressure, before it is discharged into the environment outside the aircraft. In this manner, the total efficiency of the aircraft is improved. The apparatus essentially includes an energy conversion unit (8) connected to the cabin exhaust air duct (2) to generate or recover energy from the exhaust air stream (5). Bleed or tap air (11) from the engine (10) is provided from a bleed air port (10A) through a cabin supply air duct or tap air duct (3) to an air conditioning plant (12) for final preparation of cabin supply air. A heat exchanger (4) is arranged between the cabin exhaust air duct (2) and the tap air duct (3), upstream of the energy conversion unit (8) in the cabin exhaust air duct (2).

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: An actuator suitable for use as an ejection jack for deploying an aircraft mounted ram air turbine is provided. The actuator utilizes a spring powered ballscrew operatively coupled to a centrifugally actuated brake in such a manner that the brake limits the speed of reciprocating movement of the ballscrew. The problems of fluid leakage and slow deployment at cold temperatures, often encountered in prior ejection jacks utilizing hydraulic dashpots for speed control, are thus eliminated. The actuator also includes a locking device for locking the actuator in either an extended or a retracted position. Features are also provided for attaching an external drive mechanism in a manner allowing the ballscrew to be utilized for resetting the actuator to an initial non-extended position.

Abstract: A solar energy concentrator assembly comprises flexible polymeric sheet which carries an integral optical element in the form of a Fresnel lens for concentrating a substantial amount of incoming solar radiation on a desired location on the earth's surface. Lofting elements such as propeller driven wings is attached to the sheet for providing aerodynamic lift thereto to maintain the optical element a predetermined distance above the surface of the earth. The propulsion system is powered electrically with energy derived from sunlight.

Abstract: An integrated aircraft power unit providing the electrical and other forms of energy needed during auxiliary power unit operating conditions-while the aircraft is on the ground, and also providing airborne or emergency power including high altitude flight emergency conditions power wherein the power unit uses an oxidant supply carried by the aircraft. In this high altitude operating condition the power unit provides lower electrical output, but lower losses and improved efficiency over previous power units. The disclosed power unit includes separate electromechanical transducers or motor generator devices coupled to a segregated pair of rotational shaft members, one for the inlet or compressor fan and one for the outlet or exhaust turbine fan with electrical coupling and then friction clutch coupling of these shafts accomplished for low altitude high energy output operation of the power unit.

Abstract: To ensure the power transmission between a driving shaft (42) and two assemblies to be driven, such as the rotor or rotors and the ancillary systems of a gyroplane, a mechanism is proposed, which has a connection shaft (48) constantly engaged on the driving shaft and on device (54) for riving the ancillary systems. An actuator (80) controls a translation of the connection shaft between a first position in which a free wheel (44), interposed between the driving shaft (42) and a device (46) for driving the rotor or rotors, occupies a rotation engagement state and a second position, in which the free wheel occupies a rotation disengagement state. This particularly simple mechanism can be switched from one state to the other, even during the rotation of the driving shaft.

Abstract: An electrically powered engine has a tip-driven fan assembly. The engine includes an electric motor which comprise a rotor mounted on the periphery of the fan assembly and a stator mounted to the frame. Power is supplied to the electric motor by a metal/air battery assembly mounted to the frame and having a cylindrical shape. The fan assembly produces a flow of air with at least a portion of the battery assembly. The battery assembly comprises a plurality of metal/air battery cells each having a cylindrical anode, a cylindrical cathode with insulating spacers forming an annular chamber for holding the battery electrolyte.

Abstract: Drag produced by cold, viscous oil, interacting with the gear meshes of a gear drive (8) connected to a ram air turbine (2) of an aircraft (1), is controlled to allow proper start-up of the ram air turbine. The lubricating oil is isolated from the gear meshes in remote sumps (11, 12) when the turbine is located in the stowed, inoperative position. An oil metering orifice controls the oil flow from the remote sumps to gearbox sumps with movement of the turbine from the stowed position (A) to the deployed position (B), so as to delay the application of cold, viscous coil to the gear meshes until after start-up of the turbine. This avoids excessive start times and failure to start from the high drag caused by cold, viscous oil on the gear meshes.

Abstract: An apparatus for generating power from a trailing vortex induced at the wingtip of an aircraft. A turbine is mounted on the wingtip and is disposed in the trailing vortex. The turbine includes propeller blades extending generally parallel to the axial component of the vorted velocity of the vortex to utilize substantially only the radial component of the vorted velocity of the vortex to thereby reduce the vortex strength and decrease wing drag. The turbine is coupled to an operative system of the aircraft for providing power to the system from the turbine, such as a wing de-icing system, a wing boundary layer control system, a hydraulic pump and an electric generator.

Abstract: An environmental control system for supplying aircraft or cabin air to an aircraft is provided with a propulsive engine compressor bleed supply means and an ECS bleed air flow control means which includes an energy recovery means for using the unrequired or unused energy to pump boundary layer air from the surface of the aircraft, such as from the engine nacelle, and exhaust this air rearward of the engine to produce thrust, thus returning some of this unused energy to the propulsive engine.

Abstract: An anti-deployment device and method for preventing inadvertent deployment of a ram air turbine of an aircraft during servicing or repair of turbine employ an anti-deployment pin which can be manually inserted in a support arrangement for the pin on the aircraft when the ram air turbine is in the stowed position for preventing deployment of the turbine upon release of a lock mechanism which locks the turbine in the stowed position. The pin has an elongated body with an outer, flat contact surface portion which extends in a plane that is inclined with respect to a longitudinal center axis of the pin.

Abstract: A multi stage high-altitude data acquisition system comprising a first stage manned lighter-than-air, engine propelled aircraft and a second stage air-buoyant vehicle of stratospheric altitude attaining capability statically sustainable aloft by a sufficient quantity of lighter-than-air gas contained within an expandable envelope balloon to carry the vehicle to a stratospheric float altitude and transportable from ground level to a tropospheric launching altitude by the first stage aircraft from which the air buoyant vehicle and its partially expanded gas containing envelope is releasable at the launching level while the first stage aircraft is established in a flight condition of substantially zero airspeed.

Abstract: A drive system is provided between a ram air turbine (10) and at least a pair of accessory power units (38,40) of an aircraft, the ram air turbine being movable between stowed and deployed positions relative to the fuselage of the aircraft. The problems of providing a compact lightweight design which eliminates extraneous components in the airstream and a system which operates at optimum speeds are solved by the use of a drive shaft (28) extending between the ram air turbine and a first accessory power unit (38), such as a hydraulic pump, within the aircraft fuselage. First gears (30, 34) rotatably couple an outer end of the main drive shaft to the ram air turbine. Second gears (36,48) rotatably couple an inner end of the main drive shaft to the first accessory power unit. Third gears, in the form of a gear train (54), rotatably couple the first accessory power unit to a second accessory power unit (40), such as an electrical generator, within the aircraft fuselage.

Abstract: An electromotor helicopter is provided in which a downward maneuvering of the helicopter will operate a propeller directly connected to a generator to regenerate a battery carried in the helicopter while another battery operates a drive assembly of the helicopter. A switching system can alternately cause the generator to regenerate one battery while other battery operates the drive assembly.

Abstract: A means for extracting rotational energy from the vortex created at aircraft wing tips which consists of a turbine with blades located in the crossflow of the vortex and attached downstream of the wingtip. The turbine 30 has blades 40, 41, 42 and 43 attached to a core 45. When the aircraft is in motion, rotation of core 45 transmits energy to a centrally attached shaft 50. The rotational energy thus generated may be put to use within the airfoil 20 or aircraft fuselage 10.

Abstract: An emergency on board power source (28) for jet aircraft having high (22) and low speed (14) spools is disclosed for operation above altitudes where auxiliary power units (14) are operational. A power takeoff (56) is provided from the low speed spool of the jet engine to drive an emergency power unit (28) for supplying electrical and/or hydraulic on board power to the aircraft to maintain control during emergency conditions during which the auxiliary power unit is not operational or is not operational to supply sufficient power to maintain hydraulic or elecrical on board power to uninterruptible electrical and hydraulic power loads.

Abstract: A high altitude reconnaissance platform is implemented by an ultralight aircraft powered solely by long wave infrared cells mounted on the lower surfaces of the wings and the fuselage. The aircraft may be of the pusher, slow speed propeller style, with a larger rear wing and a small, canard-type front wing. The bottom of the fuselage may be flat. The two wings may be vertically offset from one-another, and the cross-section of the wings may be relatively thick, with the ratio of the width of the wings to their thickness being in the order of about 6 to 8.

Abstract: This invention relates to an air missile comprising at least one temporary, releasable power unit, connected to the rest of said missile by a fit capable of allowing said power unit to slide parallel to its axis in the direction opposite said rest of the missile, wherein a communication is established between, on the one hand, the space inside said fit and disposed between the front of said power unit and said rest of the missile, and, on the other hand, the aerodynamic flow around said missile. The invention is more particularly applicable to the natural separation of said power unit from the rest of said missile.

Abstract: A relatively inexpensive, high efficiency, detachable thrust vector mechanism is provided for addressing the current shortcomings in the art. In the illustrative embodiment, the invention is used in conjunction with a nautical or aeronautical vehicle having primary propulsion means and at least one fin movable, to provide maneuverability, in response to a conventional control system. The invention is a detachable thrust vector mechanism comprising auxiliary propulsion means pivotally attached to the missile through connecting means. Contact means are provided for transferring bi-directional motion of the fin to the auxiliary propulsion means. The mechanism is operable to provide auxiliary thrust for the missile along a thrust vector determined by the control system. The invention is effective to provide missile steerage at low speeds, particularly during initial launch and pitchover.

Abstract: A ram air turbine and deployment mechanism has commonly had power-generating means in the form of either one, or both, of a hydraulic pump and electrical generator mounted at the end of a pivotal strut adjacent the ram air turbine. Relocation of the power-generating means can provide a system with improved operation, lesser weight and other improvements over prior known systems.The ram air turbine is mounted at the end of a pivotal strut for movement between stowed and deployed positions. The electrical generator forms a major part of the strut and is located close to the pivot axis of the strut. The hydraulic pump is mounted to aircraft structure within the stowing compartment of the aircraft and has a driven member aligned with the pivot axis of the pivotal strut.

Abstract: Rocket booster motor vectoring system and method for shortening take-off distance of aircraft, the aircraft being airborne before it is going fast enough for its conventional controls to provide adequate stability and control. A rocket booster motor (52) is coupled to aircraft (50) by means of thrust arm link (56) is pivotal engagement with the aircraft and fixed to the booster, and coupled by rearwardly positioned links (62, 64, 66) having ball and socket joints at both ends, one end being connected to the aircraft through aerodynamic surfaces (68, 70) or through actuators (124, 126), the aerodynamic surfaces being operable by conventional systems within the basic aircraft, and the actuators also being operated by motion sensing systems within the aircraft to vector the thrust of the booster to provide stability augmentation of the aircraft during the boosted launch phase to provide pitch, roll, and yaw control.

Abstract: An indexing mechanism for use with a deployment mechanism of a ram air turbine having front and rear linkages pivotally connected at one of their ends within the storage bay of an aircraft and their other ends pivotally connected to a housing for the ram air turbine, for moving the ram air turbine between a stowed and deployed position. The improved indexing mechanism includes a spring-loaded detent member coupled to the housing which engages a slot in the turbine hub preventing rotation of the turbine hub and blade when the ram air turbine is in the stowed position. Coupled to the rear linkage adjacent the pivot joint at the ram air turbine is a cam member which moves through an arc as the ram air turbine is deployed, said cam member engaging the spring-loaded detent member to release the turbine hub and blade as the ram air turbine nears the fully deployed position.

Abstract: A method of fabricating complex frames, e.g. for engines and aircraft comprises forming the principal components of the frame from resin-bonded filamentary material and securing them together, each of the principal components being formed by a method which includes the step of winding the filamentary material about a former having longitudinal axis and impregnating the material with a hardenable resin. One or more of the components so made may form part of the former for one or more of the other components. The method of forming the individual components may further include the step of axially dividing the element which is made by winding filamentary material about a former and impregnating the material with hardenable resin.

Abstract: A lightweight auxiliary power and forced air supply unit that may be used to provide electricity and forced air for use by an air conditioning system on a vehicle such as an aircraft. The unit includes a turbine (12), a generator (13), a forced air unit (14), a primary control unit (16), and a primary display and input control unit (17). The apparatus further includes an electronic sequence unit (18), a secondary display unit (19) and an ignition exciter unit (21), in addition to a modulated bleed air valve (22), a fuel pump (23), a fuel valve (24), and a fuel source (26). The apparatus also includes a heat sensor unit (27) and a fire protection unit (28), and connects to the electrical system buss (29) of the aircraft. As configured and as installed, this apparatus weighs less than two hundred pounds.

Abstract: Vacuum systems deriving their trustworthiness by means of simplified apparatus, wherein, the vacuum source will be derived from simple venturis common to the state of the art, whereby, ice prevention will be achieved by use of bleed air from the turbine section of the jet engine used to power the aircraft. Venturi ice prevention will be selectable by the pilot and will fail safe to the on position should the aircraft encounter a complete electrical failure. The remaining units comprising of the vacuum system and connective tubing will all be common to the state of the art. One of the vacuum systems will supply regulated vacuum pressure to the earth reference gyros by means of a venturi being located within the inlet mouth of a jet engine, said pressure then routed to a pressure regulator and then routed to the gyros, therefore, regulated pressure will be available immediately following engine start and will remain available in flight even should its respective engine fail.

Abstract: A high altitude, ultra lightweight aircraft has broad area relatively flat wings, and is provided with solar cells on its upper wing surfaces, and long wavelength, infrared responsive cells on its lower wing and fuselage surfaces, to provide enough power to maintain the aircraft aloft at high altitudes indefinitely. The aircraft is intended to fly at altitudes of about 60,000 feet to 110,000 feet, at speeds in the vicinity of 70 to 200 miles per hour. A battery or fuel cell and electrical system is provided to store excess electrical power and to supply electrical power when needed. A large, low speed, pusher propellor is driven by an electrical motor. The aircraft may be launched with an opaque balloon, which not only raises the aircraft to the desired elevation but also conceals it.

Abstract: The multifunction power system is a combination auxiliary power unit, environmental control system, engine start system, and emergency power system for an aircraft. The system is essentially a four-wheel auxiliary power unit comprising two compressors driven by one turbine by means of a common shaft and in addition a free turbine. The pressurized flow from the second compressor can be directed to parallel combustors and thereafter to the two turbines. A starter-generator and motor are coupled to the compressor drive shaft and the free turbine is used to power a generator and for engine starting. Ducts, heat exchangers, valves, etc., are so arranged as to provide the four functions by proper selection and routing of air.

Abstract: Deployment mechanism for a ram air turbine has conventionally consisted of a strut pivotally mounted within a storage bay of an aircraft and which pivots to a downwardly-extending position to bring the ram air turbine into deployed position. Such a structure has required a storage bay in the aircraft having a large stowing volume because of the primarily rotational movement of the ram air turbine and has not maximized the speed of deployment of the ram air turbine. The improved deployment mechanism for the ram air turbine has front and rear linkages pivotally connected at one of their ends within the storage bay of the aircraft and their other ends pivotally connected to the ram air turbine and includes a spring-loaded deployment actuator operable to move the ram air turbine from stowed position.

Abstract: An ocean wave energy converting vessel which can remain perpendicular to the ocean waves for maximum energy conversion, regardless of its direction of travel. As either end of the quadrapod is lifted by a wave and the pendulum deck tends toward the center of the earth, force is applied to the generator due to the shifting weight of the pendulum deck, generator battery bank and all other equipment on said deck. This results from cables looped around racheted pulleys on the generator shaft, connected at their ends to the bow and stern of the quadrapod. Maximum energy conversion depends upon the quadrapod being perpendicular to the ocean waves. The paradox of a vessel facing one direction while traveling another is resolved by a navigation system consisting of four simultaneously swiveling, finned, motorized pontoons to maintain course direction, operated in conjunction with a wind fan with rudder mounted to the pendulum deck which holds quadrapod perpendicular to ocean waves.

Abstract: An aerodynamic heated steam generating apparatus having an aerodynamic heat immersion coil steam generator adapted to be located on the leading edge of an airframe of a hypersonic aircraft and being responsive to aerodynamic heating of water by a compression shock airstream to produce the steam pressure, expansion shock air-cooled condenser adapted to be located in the airframe rearward of and operatively coupled to the aerodynamic heat immersion coil steam generator to receive and condense the steam pressure, a steam pressure reacting device operatively coupled between the aerodynamic heat immersion coil steam generator and the expansion shock air-cooled condenser for driving a load and an aerodynamic heated steam injector manifold adapted to distribute heated steam into the airstream flowing through an exterior thrust generating channel of an air-breathing, ducted power plant is shown.

Abstract: A motor-generator powered airplane is provided and consists of an internal combustion engine that drives an electric generator. Two transformers are electrically connected to the generator and are each electrically connected to an electric motor. Each electric motor drives a propeller so that the airplane can fly. An emergency battery is connected between the generator and the transformers so that in case of a failure of the engine the battery will supply electricity to continue operation of the electric motors.

Abstract: A tornado-type wind energy system is provided which is suitable for aircraft in flight or emergency use. Wind energy propels a turbine to provide shaft power to drive an electrical generator or the like. A vortex flow regime is produced downstream of the ram air driven turbine. The creation of a low pressure core draws ram air by the turbine at an increased rate, thereby generating greater shaft power to a load.

Abstract: An unmanned aircraft vehicle to be launched from a container is provided with a rocket engine for launching and a propeller drive for cruising; the wings can be folded to the body of the vehicle and will be deployed as the vehicle leaves the launching container. The propeller is freely rotatable, even if the vehicle is still in the launching container. The rocket engine is releasably connected to at least one point on the propeller drive and in symmetrical relation to maintain the propeller drive coaxial to the propeller shaft, and to react rocket thrust directly into the propeller drive.

Abstract: A deployable inlet for use with a center boost engine on a jet propelled aircraft having the capability of aerodynamically fairing the air inlet located in the leading edge of the vertical stabilizer at such times as the center boost engine is shut down and non-operative, thus minimizing drag. More particularly, an inlet construction for use with aircraft of the type commonly employing multiple main power plants and an auxiliary center boost engine of the type which is commonly used only: (i) during take-off; (ii) during air refueling operations; and/or (iii), under certain emergency operating conditions; and, wherein the air inlet for such center boost engine is located at the root leading edge of the aircraft's vertical stabilizer.

Abstract: A retractable/deployable nozzle fairing for use with a center boost engine on a jet propelled aircraft having the capability of aerodynamically fairing the center boost engine's exhaust nozzle and reducing the diameter of the empennage outlet when deployed so as to minimize the base drag characteristics of the empennage body structure when the center boost engine is shut down. More particularly, an exhaust nozzle retractable/deployable fairing for use with aircraft of the type commonly employing multiple main power plants and an auxiliary center boost engine of the type which is commonly used only: (i) during take-off; (ii) during air refueling operations, and/or (iii), under certain emergency operating conditions; and, wherein the retractable/deployable fairing member is formed of flexible sheet material that is fabricated into a truncated generally conical nozzle configuration--i.e.

Abstract: Disclosed is apparatus for collecting solar energy with means of producing electricity by concentrating solar energy on sets of photovoltaic cells to be either positioned at high altitudes and which may be fitted to balloons or to structures floating on water.

Abstract: The nose portion of a missile having a ram air turbine for driving an electric generator for supplying electric power to the electric circuits of the missile, especially of its fuse, is designed in a special manner in order to provide, at high missile speeds, a throttling of the air flow, whereby the speed of rotation of the turbine may be kept within reasonable limits. Thus, the air inlet is divided in a plurality of inlet ducts arranged as a wreath around the foward end of the missile. Further, the outlet openings are forwardly directed and co-operate with the shock waves from the acute forward end of the missile and from an annular edge surrounding the wreath of inlets but lying radially inside the outlet openings.

Abstract: An apparatus and method for modifying a jet engine to be carried externally in an inoperative condition on an aircraft to minimize aerodynamic drag and oscillation of the engine. The apparatus includes an annular inlet extension adapted to be mounted to the operating air inlet which slightly extends and contracts the inlet to reduce air spillage. The disclosed method includes the removal of the fan blades from the fan section of the inlet, attaching an ice deflector dome to the engine core inlet, and attaching the inlet extension to the nacelle air inlet.

Abstract: A powered aircraft having an auxiliary thruster engine normally disposed within the fuselage of the aircraft, but which, when activated, is moved to an operative position outside of the fuselage prior to its energization, the auxiliary thruster engine providing sufficient thrust to power the aircraft if one or more of its normal engines is inactive.

Abstract: In a motor-glider provided with a propeller power system fully encased within the fuselage thereof, outer shapes of the elements adapted for selectively closing air-intakes and, when required, an outlet are designed quite flush with the streamlined shapes of the surrounding portions of the motor-glider and the air is ejected in directions away from the tail boom, whereby aero-dynamic drag acting on the motor-glider during power-off gliding is considerably minimized.

Abstract: A helicopter is provided with an emergency drive system adapted to rotate the helicopter rotor in the event of motor failure, the drive system being powered by compressed gas stored in the helicopter. The system may comprise nozzles aimed at the plane of rotation of the rotor, or a turbine coupled to the rotor drive shaft.