Abstract: An aircraft engine cowling interlock system (10) for sequencing the closure of adjacent overlapping cowlings. The cowling interlock system (10) includes a telescoping rod (22) that holds an overlapping thrust reverser cowling (12) in an open position; a locking mechanism (24) that locks the telescoping rod (22) and the thrust reverser cowling (12) in the open position; and a connecting assembly (26) that connects the locking mechanism (24) to an overlapped core cowling (14), such that the locking mechanism (24) locks the telescoping rod (22) in the open position when the core cowling (14) is in an open postion to prevent closure of the thrust reverser cowling (12), and the locking mechanism (24) unlocks the telescoping rod (22) when the core cowling (14) is in a closed position to allow closure of the thrust reverser cowling (12).

Abstract: An aircraft having a substantially circular body having a profile in the direction of flight as a profile of an airplane wing, at least two concentric counter-rotating turbo-blade assemblies within said body for effecting a vertical lifting air stream through said assemblies. Power generating devices and devices for coupling the power generating devices to the turbo-blade assemblies for maintaining them in rotary motion. It also includes thrusting devices coupled to the power generating devices for applying horizontal thrust to the aircraft, retro-boosting devices including a plurality of combustion chambers located below the turbo-blade assemblies for boosting said vertical lifting airstream.

Abstract: A movable cowling for an aircraft is disclosed having a stationary fairing portion attached to an engine support pylon and a movable cowling portion. The movable cowling portion defines a generally longitudinally extending slot to accommodate the stationary fairing portion when the movable cowling portion is in its closed position to enclose the aircraft engine. The movable cowling portion, which may be generally annular in shape and have a generally "C"-shaped cross sectional shape, is attached to the engine by way of a telescoping beam. A portion of the beam is attached to the movable cowling and a second portion of the beam is attached to the engine. The movable cowling moves in a direction generally parallel to the longitudinal axis of the engine such that it has no portions requiring lifting about a hinge axis. A locking mechanism is provided between the movable cowling portion and the stationary fairing to lock the movable cowling portion in its closed position.

Abstract: The present invention comprises a cowling structure for a gas turbine aircraft engine which allows the aerodynamic characteristics of the inlet passageway to the engine to be varied in accordance with flight conditions. This structure includes an annular lip portion positioned at the front edge of the cowling defining an aerodynamically sharp contour and which is mounted on a set of support struts constructed for allowing the lip portion to be translated forwardly and backwardly from the forward edge of the cowling. The structure further comprises a mechanism for injecting pressurized air into the airflow along the trailing edges of these support struts in order to suppress turbulence induced in tha airflow such that noise as may be produced as a result of airflow is substantially decreased.

Abstract: A turbo-prop driven aircraft has the engines (6) and propeller assemblies (10) spatially separated fore and aft of the wing box (4) and interconnected by a drive shaft (27). This arrangement permits the engine to be located away from the wing box without causing excessive overhang of the turbo-prop installation.

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: An unducted turbofan engine comprises first and second fan blades journaled for rotation from a folded position substantially parallel to the axis of rotation of the engine to a radially orientated propulsion condition. A releasable shroud normally retains the fan blades in the folded condition and releases the fan blades in a controlled sequence.

Abstract: An aircraft converting aerodynamic compression ram thermal stream energy into thrust power generation comprising:(a) an aerodynamic compression ram thermal stream generating multiple vane diffuser as the air-inlet to a pressure plenum;(b) a ram thermal-pressure stream induction double throttle duct consisting of a main ramflow inducing nozzle and a fuel injection ramflow inducing nozzle wihch coalesce to form the air-oulet of a pressure plenum-engine pod;(c) a compressed air shooting annular slotted ignition chamber downstream of the fuel injecting ramflow inducing nozzle with flame bed-walled combustion chamber forming a ramjet engine;(d) a ram thermal-pressure stream induction annular slotted thrust nozzle extending rearward from the combustion chamber of the ramjets and exit nozzle of a turbojet engine thereby creating a tailpipe for the turbo-ram induction jet engine; and(e) an aerodynamic compression ram thermal stream sink double-walled shockcone airframe, the double walled shockcone housing the ram the

Abstract: A pusher turboprop engine is provided with an interior exhaust duct structure which directs the hot turbine gases through and out of the engine nacelle and around the rear spinner which surrounds the propeller hub. The spinner supports blade-shaped shields which protect the roots of the propeller blades from the hot exhaust gasses.

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: A pusher turboprop engine is provided with an interior exhaust duct structure which directs the hot turbine gasses through and out of the engine nacelle to an annular duct mounted on the rear spinner which surrounds the propeller hub. The rotating annular duct includes blade-shaped shields which protect the roots of the propeller blades from the hot exhaust gasses and also pulls warmed cooling air through the engine nacelle thereby providing a rearwardly directed jet thrust to augment the propeller thrust.

Abstract: A vortex control device is designed for installation on the exterior surface of an aircraft nacelle in a position which does not compromise the optimum aerodynamic performance of the vortex control device. Existing cowling structure is bridged by this vortex control device which attaches only to movable structure and which is cantilevered over adjacent stationary structure. A resilient seal prevents air from swirling under the cantilevered portion, thus contributing to vortex generating efficiency and reduced aerodynamic drag.

Abstract: An aircraft cowl, and in particular a translating cowl, used as a component of a thrust reverser, formed of at least one one-piece bondment cured in a single operation. Preferably, a one-piece inner bondment and a one-piece outer bondment fastened together at a joining region. The bondments have constant density cores and tapered closures. Acoustically absorbing materials are part of the lay up for one of the bondments and are integrally cured therein.

Abstract: A nozzle for a gas turbine engine having a first fixed petal 44 and a second movable petal 46 which is pivotally mounted at a point intermediate its leading edge 46(a) and its trailing edge 46(b). Actuation means 48 are provided to move the nozzle between a first and a second position. In the petals first position, its leading edge 46(a) is positioned forward of and slightly radially inward of the trailing edge 50 of the exhaust duct 52, such that a small ejector gap 54 is provided therebetween and the trailing edge 46(b) approaches the trailing edge 44(b) of the fixed petal, such that the gap therebetween defines the exit area of the nozzle 36. In the petals second position (shown dotted), its leading edge 46(a) is moved radially inwards of its trailing edge 46(b) such that the exit area of the nozzle is defined by the area between the trailing edge 50 of the exhaust duct 52 on the second petal side and the trailing edge of the first petal 44(b).

Abstract: An engine suitable for use in an aerospace plane is a composite engine comprising, in combination, a turbo jet engine, a ram jet engine, and a rocket engine, all arranged co-axially. An aerospace plane comprises such an engine mounted in a body defining, toward a rear thereof, in association with said engine, a nozzle surface which extends rearwardly in curved, concave manner, and which is part-round in cross-section, said or each nozzle surface being arranged in relation to a nozzle of said engine to be an extension of the nozzle.

Abstract: An improved nacelle is provided for housing an aircraft engine and reducing aerodynamic drag during aircraft operation. In one embodiment, the nacelle houses a gas turbine engine and comprises a leading edge and a trailing edge, having a reference chord extending therebetween, and an outer surface which is continuous from the leading edge to the trailing edge. The outer surface includes a forward portion, an intermediate portion and an aft portion that has a profile defined by a varying thickness measured perpendicularly from the chord to the outer surface. The profile has a maximum thickness at the intersection of the forward and intermediate portions, which intersection is located greater than about 36% of the chord from the leading edge, and is effective for increasing laminar flow over the nacelle for reducing aerodynamic drag.

Abstract: An unmanned aircraft is equipped with a helium-cooled Brayton cycle nuclear reactor. Heated helium gas drives turbines which in turn rotate propellers to maintain the aircraft aloft for a protracted period of time. After the helium gas expands in the turbines, it is passed through a closed loop including radiator tubes which radiate waste heat from the helium gas to space. The cooled helium gas is returned through the closed loop for repeat of the Brayton cycle.

Abstract: A casing surrounding a fluid stream over which an unbounded fluid flows in a downstream direction has a plurality of alternating, adjoining troughs and ridges in its external surface, extending in the downstream direction to a thin trailing edge of the casing, which will thereby have a wave-like shape.

Abstract: An ultra hypersonic aircraft having aerodynamic heat transferring pipes forming an airframe structure is shown. The heat transformer pipes include a high pressure steam generator located at the forward section thereof and a low pressure steam condensator located at the rearward section thereof. Low pressure water is circulated between the rearward section and the forward section for heat balancing of the air frame structure and for operating the room air conditioning system of an aircraft. A steam pressure reactant turbine, which drives an electric generator, is used as a boundary between the high and low pressure steam sections. The electric generator provided electrical and power supply for the infrared or arc heaters, and electric heaters recessed in the ceiling and wall panels of an acrodynamic lift-thrust generating channel for back-heating of the turbo-ram oval thrust stream in the thrust generating channel of a hypersonic aircraft.

Abstract: A flexible solar skin which absorbs radiant solar energy to convert it into electricity, made possible through a conductive plastic, which conceals a conductive fiber, whereby the fiber directs generated electricity to a terminal in the form of a contact strip hemmed or fused alongside the material. Additionally, an air vehicle covered with this photovoltaic material to collect solar radiant energy during flight which is converted into electricity to assist the propulsion system of the vehicle.

Abstract: The inlet of a jet engine is equipped with a pivotally displaceable deflector which becomes deployed when the aircraft is in a stalled, horizontally stabilized condition. As the aircraft undergoes vertical descent, vertically impinging airflow is reflected off the interior surface of the deflector and flows coaxially through the inlet thereby forcing continued rotation of turbine blades. Hydraulic and electronic control devices deriving power from the turbine may be maintained operative even though the aircraft is in a stalled condition, thereby permitting limited horizontal maneuvering of the aircraft as the vertical descent continues.

Abstract: A unitized static sensor probe 20 for a gas turbine engine 10, machined from a single piece of raw material. The probe preferably has integral kiel cups 26 that form a part of the probe airfoil. The probe is manufactured by electrical discharge machining, and is shaped with an airfoil (53, 70) that minimizes disruption of the engine airstream. Integral air seal platforms 56, 58 and a mounting plate 54 are also provided.

Abstract: An aircraft having a rotatively driven blade cooperating with an electrochemical power system for operating an electric drive system. The blade provides cooling heat transfer relative to the lithium/peroxide fuel system effecting desirable separation of the lithium-hydroxide monohydrate in a suitable filter/plenum provided as a portion of the power system. In one form, the cooling is effected by disposing a heat transfer portion of the power system in the path of air flow generated by the propulsion blade of the aircraft. In another form, the cooling is effected by flowing the electrolyte through the propulsion blade. Molarity of the electrolyte is maintained by separating the precipitated lithium-hydroxide monohydrate in solid form in the filter/plenum and addition of replacement hydrogen/peroxide solution from the reservoir thereof.

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: A compound helicopter shown in FIG. 1 of the drawings has wings 12 in addition to a helicopter rotor 14 and has twin powerplants 16 each including a low pressure compressor 18, a core engine 20, a power turbine 22 driven by the core engine and connected through a gearbox 32 to drive the helicopter rotor, and a variable area final, propulsion nozzle 24 which receives the exhaust from the power turbine. Augmentor wing flaps 28 are provided on the wings and fed with air from the low pressure compressor for providing additional lift and thrust from the wings. In operation, at take-off the nozzles 24 are fully opened and all of the power produced by the power turbines 22 is used in driving the helicopter rotor for producing lift. In addition, the augmentor wing flaps 28 are directed downwardly to provide lift. For forward flight the nozzles 24 are closed down, reducing the power to the rotor and slowing it down, while at the same time generating forward thrust.

Abstract: A nozzle system for providing improved thrust augmentation for an aircraft lift and/or propulsion system is provided. The unique nozzle structure is designed such that counter-rotating vortices emanate from the nozzle tips. When this unique nozzle configuration is combined with simple slot nozzles in a specific manner a vortex rich flow will result. When a diffuser is placed around this unique combination such that jet pumping is obtained, significant improvement in thrust augmentation is realized from the vortex rich flow mixing with the coflowing secondary air stream.

Abstract: A hold open rod for holding open a hinged section of a nacelle system for maintenance. The rod includes a tubular member connected to the hinged section and a rod which telescopes within the tubular member and which is connected to the engine contained within the nacelle system. The hold open rod is provided with a novel locking feature which permits telescoping of the rod member within the tubular member only when the hinged section is opened further to permit manual disengagement of a latch member locking the rod member within the tubular member.

Abstract: A latch signal for mounting inside an engine cowling structure. The signal indicating when an internal latch is inadvertently left unlatched when the cowlings are closed. Further, the signal prevents adjacent cowlings from closing until the internal latch is properly secured.

Abstract: A tensioning assembly for applying tension to a band-type clamp includes a T-bolt having a shank portion and a T-head portion. The T-bolt is adjustably mounted to a first end of the band clamp and a keeper constructed and arranged to receive the T-head portion of the T-bolt is affixed to a second end of the band clamp. A nut threadably engages the shank portion of the T-bolt and rotation of the nut on the T-bolt draws the head to the T-bolt towards the first end of the band clamp thereby drawing with it the second end of the band clamp. An anti-rotation device is associated with the nut operably engageable with the nut to prevent its rotation. The anti-rotation device cooperates with a force-applying tool, such as a wrench, so that when the tool is placed on the nut, the anti-rotation device disengages from the nut. Preferably the tensioning assembly also includes an indicator remote from the T-bolt and operably associated with it to indicate the achievement by the T-bolt of a predetermined tension.

Abstract: A large cylindrically-shaped balloon-like structure having hemispherical ends with fins utilized in conjunction with airflow thereacross based upon Bernoulli's principle for maneuvering and maintaining stability. The balloon is compartmentalized, contains a uniquely designed structural support system, and contains pumps for evacuating the air therein. The structure may be used for any lifting application. In particular solar-energy is collected through a transparent portion of the structure and reflected from shaped surfaces that direct solar energy on energy converting panels. The electrical energy generated is utilized to operate an evacuation system, while the remainder of the electrical energy is beamed by microwaves to a receiving station on earth.

Abstract: A duct 11 for an aircraft comprises a flexible panel member 18 which is normally held in a non-fluid conducting condition adjacent the surface of the aircraft body by biass tension means 12, 13, so as to define a substantially continuous surface. On introduction of fluid pressure between the panel and the aircraft body, the panel member is inflated to overcome the biass of the tension means 12, 13, and to expand to a fluid conducting condition of relatively large cross-sectional area, upstanding from the surrounding aircraft surface regions.

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: A liquid fuel prevaporization and backburning induction jet thrust transition tailpipe having a primary inlet adapted to be affixed to a turbojet engine and having a diverging area in the transition tailpipe formed of vertically converging and horizontally diverging walls terminating in a thrust nozzle, a pair of air plenums for directing an air/ram flow into the main airflow path having a bellmouth shaped inlet which communicates with an airflow inducing nozzle which terminates in a chamber having a downstream end opening forming a secondary inlet to the diverging area, a plurality of parallel, vertically spaced curved inductor vanes positioned in the secondary inlets and which are adapted to deflect a secondary airflow passing through the bellmouth shaped airflow inducing nozzle, chamber and secondary inlet into a path through the diverging area which is substantially directed towards the thrust nozzle, an upper and lower liquid fuel prevaporization chambers, fuel injectors, and gas outlets, a vaporized gas

Abstract: A below-wing engine nacelle mounted by a pylon forwardly of a wing having a rearward sweep. The pylon upper outboard edge that extends forwardly of the wing is formed with a relatively sharp radius of curvature. Thus, airflow which flows over the top of the pylon in an outboard direction separates over the sharp pylon edge to form a vortex which passes beneath the wing adjacent the outboard surface of the pylon. This vortex maintains attached flow at the outboard pylon surface immediately beneath the wing to reduce drag.

Abstract: An actuating mechanism, for putting into operation a ram-air turbine of an aircraft, includes a slide member linearly moveable and connected with a Bowden cable which is actuatable in dependence on a blocking mechanism. In order that the actuating installation can be operated in a simple and safe manner, the blocking mechanism is connected with a hand lever which in the opened condition releases the blocking mechanism and cooperates with a support element of the slide member in such a manner that the slide member is adapted to be displaced into an end position by means of the hand lever.

Abstract: This invention is an improvement of my system for supersonic aircraft which provides the required angular momentum reaction to the continuous generation of new lift circulation by vorticity in lieu of dissipative shock waves. This new system relocates the propulsive jet forward utilizing its excess energy to generate this vorticity in a planar sheet below the wing acting as a pressure shield, which continues downstream beyond the wing trailing edge as a vortex flap simulating an extended wing chord. The present invention provides mechanical vortex generating means to augment this free surface mechanism in cases where the jet velocity is insufficient. This invention also incorporates a wide-body fuselage above this pressure shield, and provides further system improvement in propulsion/wing integration.

Abstract: A propulsion system for vertical take off and landing aircraft includes a forward compressor fan (40) and an aft compressor fan (42) downstream of the forward fan and in series flow communication with the forward fan. The forward and aft fans are positioned in a central duct (26). A gas turbine engine (44) is in series flow with the forward and aft fans for driving the fans. The forward fan, aft fan and turbine engine are interconnected by a common shaft (50). A forward diverter structure (100) is positioned downstream of the forward fan and is movable between a first position for diverting exhaust from the forward fan downwardly relative to the longitudinal axis of the aircraft while simultaneously permitting the introduction of air behind the forward diverter structure but ahead of the aft fan and a second position wherein the exhaust from the forward fan is channeled through the aft fan and turbine.

Abstract: Nacelle installation having devices for constraining hot core exhaust gas from flowing over the trailing portion of a highly swept pylon supporting a high bypass turbofan engine. The devices can comprise a pylon ejector, a core nozzle shroud or a plurality of vortex generators and are disposed generally in the region adjacent the intersection of the core nozzle exit of the engine and the pylon shelf portion of the pylon.

Abstract: An improved jet engine two dimensional, asymmetric afterburner nozzle of the type adapted to be mounted on a jet engine suspended from an airfoil's wing spar structure, and characterized by its low profile configuration, simplicity of construction, and lack of interference with, or excessive intrusion into, the wing spar structural space within the airfoil; yet, which permits minimization of the included angle between the wing chord reference plane and the visual line-of-sight from the airfoil trailing edge into the jet engine nozzle while in its cruise position. More specifically, the present invention pertains to a simplified two dimensional, asymmetric convergent or CD nozzle construction, and an actuating mechanism therefore, which avoids the necessity to devote critical wing spar structural space to pneumatic load or pressure balance chambers, and wherein the nozzle may be shifted to a dry nozzle position--i.e.

Abstract: A nacelle mounted directly to and below a wing so as to extend forwardly therefrom. The wing has a critical zone, which includes an area in the airstream flow about the wing where either of the following conditions occur:1. The local pressure coefficient in the airstream has an absolute magnitude greater than 0.05,2. The airstream flow about the airfoil is supersonic.The nacelle has a critical surface region which is a side surface portion of the nacelle adjacent to a forwardly swept portion of the wing. The critical contour area of the nacelle surface is that portion of the critical surface region that is within the critical zone. The critical contour area of the nacelle is shaped to be in alignment with a plurality of airfoil streamlines that are immediately adjacent the critical contour area. Other surface portions of the nacelle are out of alignment with adjacent streamlines and correspond more closely to the engine structure contour.

Abstract: An integrated power plant installation system for underwing high-bypass mid-length fan air duct core-mounted engines readily permits disconnection of the entire powerplant at the wing thereby virtually eliminating the necessity of disconnecting the engine and complex systems per se from the support strut when engine replacement or removal proves necessary. Excessive congestion within the vicinity of the strut box structure is eliminated by disposing the engine accessories, and auxiliary equipment and system lines, within the lower quadrant of the powerplant assembly in both a laterally and longitudinally distributed array. Potential catastrophic fire hazards within the nacelle are substantially eliminated by routing the fluid lines and electrical conduits axially aft and upwardly around the circumference of the engine within the nozzle section of the powerplant aft of all rotating discs.

Abstract: A cruciform wing structure for a solar powered aircraft is disclosed. Solar cells 28 are mounted on horizontal wing surfaces 20, 22. Wing surfaces 24, 26 with spanwise axis perpendicular to surfaces 20, 22 maintain these surfaces normal to the sun's rays by allowing aircraft to be flown in a controlled pattern at a large bank angle.The solar airplane may be of conventional design with respect to fuselage, propeller and tail, or may be constructed around a core 70 and driven by propeller mechanisms 75, 76, 77, and 78 attached near the tips of the airfoils.

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: A wing-mounted gas turbofan engine is provided with an exhaust system that reduces airflow drag during subsonic aircraft flight operation. The system reduces drag by turning the engine bypass exhaust stream away from the underside of the airplane wing to lessen its tendency to reduce air pressure under the wing. Low pressure below the airplane wing has a detrimental effect on wing lift which, in turn, causes greater airflow drag. The exhaust system construction lessens its pressure lowering influence by first, inwardly curving the exhaust system exit to turn the bypass flow away from the airplane wing; second, by predetermining the location of a nozzle throat within the bypass stream to control exit exhaust pressure so as to match outside air pressure and third, by decreasing the diameter of a portion of the engine nacelle just downstream of the bypass exhaust stream exit to provide a flow region for the exhaust that is further from the airplane wing.

Abstract: The present invention relates to a method of providing thrust and added lift to a vehicle by accelerating fluid heated by solar energy. The present invention also relates to apparatus for carrying out the aforementioned method. Accordingly, the present invention relates to a method of providing initial acceleration and propulsion or enhancing the initial acceleration and propulsion of a vehicle in an environment having at least some fluid, the vehicle being of the type having at least one member, at least a portion of which is treated for absorbing solar radiation for heating fluid adjacent the member for use in propelling the vehicle through the environment. By use of direct and/or focused solar radiation, fluid is heated, accelerated and deflected away from a vehicle by natural or forced convection to provide thrust and lift of the vehicle.

Abstract: A self-contained apparatus for moving the portions of a cowl covering the gas-generator portion of a turbofan jet engine includes a motor-driven pump for pumping hydraulic fluid from a reservoir mounted on the engine through a control circuit which selectively channels the fluid to actuators associated with each of the cowl portions to move the cowl portions to their desired positions. The hydraulic control circuit preferably includes solenoid-actuated valves associated with each of the actuators and operable to selectively permit flow of fluid into and out of the actuators as is desired to open and close the cowl portions. Another solenoid valve is provided to control passage of the fluid from the actuators back to the reservoir during the closing of the cowl portions. The speed of closure of the cowl portions is regulated by one-way flow restrictors in the outlet ports of the actuators that control the rate of flow of fluid out of the actuator.

Abstract: A latching system for an infrared suppression device, which reduces the iared signature of the exhaust of a gas turbine engine, employs a two-point hinge for supporting and swivelling the IR suppressor and for permitting the IR suppressor to be translated forward and backward a substantial distance in order to complete the latching operation. Guide pins entering guide holes and held in firm engagement therebetween by retractable hooks engaging loops, support the forward end of the suppressor to the aft end of the gas turbine engine while resisting lateral and twisting displacement of the suppressor when it is latched in place.

Abstract: An improved latch for aligning and securing together a pair of hinged cowlings surrounding an aircraft engine. The latch not only holds the cowlings together during thrust and reverse thrust loads, but also absorbs shear loads placed thereon by the aircraft.

Abstract: Two groups of half shells capable of being retracted from the jet flow, in a position closing the jet pipe. The thrust reverser and the silencer are concentric and their axes of rotation are upstream with respect to their position in the jet flow.