Abstract: A propulsion/control system for aircraft of the vertical takeoff and landing type having a body without wings or tail and relying entirely on fluid streams for effecting liftoff, propulsion, and control. The body has an air duct with an inlet adjacent the rear end and a downwardly directed outlet at each side, an engine driven fan being disposed in the duct at the inlet and a cascade of adjustable vanes at each outlet. Operation of the fan causes air to flow into the inlet, through the duct, and issue in streams from the outlets, the reaction of such streams imparting lifting and flight forces to the body. By adjusting the cascades of vanes, the effects of the forces can be varied to control the movement of the body. To further control the movement and stability of the body in the air, additional adjustable elements may be provided.

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: An air inlet control inset in the skin or outer wall surface of an aircraft or the like. The control device has an open position in which it is able to capture ram air flowing over the wall surface and which at the same time defines an open flow area through which lower pressure ambient air can be inducted when ram air is unavailable. The air inlet control includes a shutter opening into ram air flow, and an actuating mechanism therefor. In one disclosed form of the invention, the shutter is aerodynamically biased to reduce actuating forces required to close the shutter against ram air pressure.

Abstract: This invention relates to a compact hypersonic modular inlet which divides captured airstream and compresses it supersonically without the need for a variable geometry diffuser. According to the invention, an innerbody is provided with a plurality of perimetrically spaced inlet ducts which are defined by a single concave sidewall. The sidewalls intersect to form a center spike and radially directed, swept back leading edges. A cowling covers the inlets and is provided with a swept back leading edge adjacent to each duct, each leading edge having a profile conforming to a normal shock front.

Abstract: A lift augmenting device to provide a vertical take-off capability in aircraft which includes a pair of rotor assemblies with independently individually pivoted rotor vanes so that the attitude of the vanes can be changed at different positions along the circumferential rotational path of the vanes as they rotate with the rotor assemblies to pump air therethrough and selectively generate lift on the aircraft.

Abstract: A cylindrical type automotive barrier filter is adapted to be used in the inlet airflow of a gas turbine engine that is used in an agricultural aircraft. Air is drawn in through an inlet in the upper portion of the aircraft nose body without appreciable disturbance to the aerodynamic contours. The outlet of the filter is connected to a duct in a sealed relationship to direct the airflow to the engine inlet. The airflow passage is sealed by a connecting flange mounted on the filter to which the duct is connected. A longitudinally extending firewall is constructed to separate the filter and connecting duct from the turbine section of the engine. An emergency bypass door is provided to provide an inlet airflow in the event the filters become clogged. The bypass door is designed to provide particle separation of the incoming air.

Abstract: To enhance the flow of air into a flush-type, air inlet on the fuselage of an aircraft, a wing-like deflector is mounted on a pedestal attached to the aircraft and is positioned outwardly from the fuselage and forwardly of the inlet so as to deflect free stream air flowing past slower-moving boundary layer air adjacent the fuselage, into the inlet. The deflector has an ogee shaped planform and is pitched at a predetermined angle of attack with respect to the direction of free stream flow to generate counterrotating flow vortices that trail the deflector and produce a strong downwash behind the deflector. The vortices entrain high energy air from the free stream and direct it down into the inlet. In one disclosed embodiment, the inlet is equipped with a door that swings between a closed position, flush with the exterior of the fuselage to block air flow from entering the inlet, and an open position, recessed within the inlet duct.

Abstract: A combination air brake and engine shield for a jet powered aircraft. A hydraulically operated, hinged shield member, shaped so as to conform to the surface of the aircraft fuselage when in its retracted position, may be swung outwardly therefrom so as to be disposed in front of the air intake of the jet engine powering the craft, to thereby divert any foreign objects from being drawn into the intake and damaging the engine. The same arrangement may also serve as an air brake to effect deceleration of the aircraft. Spring loaded louvers are provided in the shield to permit sufficient air to reach the engine such that problems due to cavitation are avoided.

Abstract: An inlet air cleaner assembly is provided for the air intake of gas turbine engines comprising, in combination, an array of vortex air cleaners removing coarse and heavy contaminant particles, but not light and well dispersed contaminant particles, and an array of sheets of filamentary woven or nonwoven material, arranged to receive partially cleaned air from the vortex air cleaner array, and remove light and well dispersed contaminant particles suspended therein.

Abstract: There is disclosed an air inlet for a turbine engine suitable for use on a short takeoff and landing (STOL), a vertical takeoff and landing (VTOL) or a conventional takeoff and landing (CTOL) type of aircraft. A critical region in which critical flow occurs under certain conditions communicates with a less critical region of lower static pressure. Air is drawn away from the critical region and reinjected into the air flow at the less critical region.In one embodiment a circumferentially extended slot is provided in the inner surface of the air inlet at the windward side and downstream of the throat region. The slot communicates with a circumferential plenum chamber formed in the front of the air inlet just behind the lip. Circumferentially extending rows of apertures are provided on the lip establishing two sets of apertures spaced circumferentially away from the slot in opposite directions.

Abstract: The forwardly open intake end of a jet engine, powering an aircraft, is screened against birds and other airborne objects by a conical cage formed from an array of metal rods converging on the engine axis, the rods being held together at the vertex of the cone by a solid tip and in an intermediate plane as well as at the cone base by a pair of metal rings. In flight, they are free to vibrate so as to shake off adhering ice particles. De-icing can be further promoted by feeding back exhaust gases from the rear of the engine to the interior of the cage through an external pipe.

Abstract: An inlet for a gas turbine engine is provided with a fixed geometry upstream lip defining the primary inlet flow passage, and a variable position downstream lip partially defining an efficient auxiliary fluid flow passage through the inlet. The upstream lip is sized to pass all of the engine flow requirements at a near-sonic average Mach number during engine approach operating conditions. Apparatus is provided to position the variable lip for modulating flow through the auxiliary passage during higher engine power settings.

Abstract: An air inlet duct for a jet propulsion missile or other vehicle which is movable between a housed, pre-launch position and an extended or deployed flight position. A method of manufacturing the duct is also disclosed. The duct system includes a flexible leading edge attached to a double-wall inflatable duct body. Drop threads extend between the duct body walls to hold an exact desired contour when the duct is inflated. A pivotable plate moves the inflatable duct between a housed, deflated, position and an inflated flight position. Manufacture of the inflatable duct is basically accomplished by preparing a foamed plastic form in the desired duct wall shape, covering the form with fabric, stitching through the foam and fabric, coating the fabric with a flexible sealing compound, dissolving away the foamed plastic and attaching the resulting inflatable duct to other missile components.

Abstract: A supersonic diffuser having a plurality of blades therein for dividing the diffuser channel into a plurality of approximately axisymmetric ducts wherein a portion of said ducts ingest a boundary layer along at least one of the walls of the supersonic diffuser. The blades in the diffuser channel have their upstream ends bent away from the wall having the boundary layer to redirect the flow into the ducts. In one embodiment the wall between the duct having the boundary layer and the duct adjacent to the duct having the boundary layer is made in two sections with both sections being bent away from the wall having the boundary layer, to provide internal redistribution between the two ducts.

Abstract: An improvement in an air intake for an aircraft engine, particularly a prop-jet engine, which intake is ring-shaped at the forward part thereof and has a central, non-rotatable body mounted in said intake, which together form an intake diffuser, the improvement comprising a displaceable inlet lip on said intake, said lip being displaceable to sealing contact against said central body and against the direction of air onflow, and said lip in said sealing contact position forming a ring-shaped inlet gap behind said lip.

Abstract: Aircraft having subsonic and supersonic flight capabilities which utilize travelling tail units with circular arc motions, connected with the rear fuselage by means of two arm-frames that swing upward and rearward and vice versa, to generally increase stability and control of aircraft during low-speed flight and to reduce accidents at zero altitude operations.

Abstract: An air intake control for an air utilizing jet aircraft engine. The control is provided with fixed and movable air intake control ramps and the positioning of such movable ramps for air control purposes is determined by the static pressure above one thereof modified by the static pressure of the external air flow, the total pressure and the angle of attack of the aircraft. One control parameter is produced by a device responsive to the relationship between the static pressure above the one movable ramp and the total pressure of the external air flow. Particularly, this pressure relationship is calculated as a function of the operating cylinder feedback signal indicating the actual position of the center ramp, and is applied as a modifying value to a summing junction provided in the control circuit to produce a variable demand signal.

Abstract: Noise generated by the tips of the fan blades in a turbofan jet propulsion engine is suppressed by generating an annular fluid layer or wake in the inlet of the turbofan engine forwardly from the fan blades and spaced inwardly from the inner wall of the inlet and by lining the inner wall of the inlet with an acoustically absorbent layer of material. Sound waves generated by the fan blades are reflected outwardly by the fluid layer and are absorbed in the acoustic absorbent layer on the inner wall of the inlet. In order for the wake to reflect sound waves, either the local fluid velocity in the wake must be lower than the fluid velocity of the surrounding airstream traveling through the inlet or the acoustic speed in the wake must be greater than or equal to the acoustic speed in the surrounding airstream. It is preferred that both conditions be met.

Abstract: An inlet for a supersonic aircraft capable of varying capture area. The inlet is of a rectangular shape, and has a ramp attached to the top and bottom of its fore end. The ramps are positioned to maximize air capture area during supersonic flight. At subsonic speeds, the ramps are moved to a position which slightly reduces the capture area. The ramps may have a blunt edge or sharp edge, and are controlled by an actuator located within the aircraft and connected to the ramps by suitable linkage. The ramps have a smooth contour provided by a flexible outer skin to reduce aerodynamic drag during operation of the aircraft.

Abstract: An axisymmetric air intake system for a jet aircraft engine comprising a fixed cowl extending outwardly from the face of the engine, a centerbody coaxially disposed within the cowl, and an actuator for axially displacing the centerbody within the cowl. The cowl and centerbody define a main airflow passageway therebetween, the configuration of which is changed by displacement of the centerbody. The centerbody includes a forwardly-located closeable air inlet which communicates with a centerbody auxiliary airflow passageway to provide auxiliary airflow to the engine. In one embodiment, a system for opening and closing the centerbody air inlet is provided by a dual-member centerbody, the forward member of which may be displaced axially with respect to the aft member. The air inlet is open when the forward centerbody member is in a first, rearward position with respect to the aft member.

Abstract: An improved deflector type of device for preventing suction of foreign matter into an air intake port of a gas turbine engine for an aircraft. The deflector is movable and by displacing said movable part to a desired position an intake air flow passageway of the engine can be varied. Thus, suction of foreign matter into a gas turbine engine during a flight under a freezing weather condition can be prevented without degrading air intake efficiency during a flight under a non-freezing environmental condition.

Abstract: A control system for suppression of shock-induced flow separation caused by the interaction of turbulent boundary layer air and a strong normal shock in the air inlet of a supersonic aircraft by application of continuous bleeding upstream and across the shock boundary layer interaction region of the inlet through a porous cover which leads to a row of plenums from whence the bleed air is exhausted to atmosphere, through a controlled incrementally operated door. The control system can control interactions with normal shock strength approaching Mach=2 in strength.

Abstract: Sand and dust erosion of turbine engines by ingested particulate matter is major problem facing both airframe and engine manufacturers. Various types of particle separators are used to keep sand and dust out of the engine. In these separators the particles are diverted by swirl vanes and similar devices to keep them out of the engine. An inlet scroll separator herein permits the particles to continue their course of travel and diverts the air stream, reducing power requirements and eliminating swirl and deswirl vanes.

Abstract: The flap covering or opening a secondary air intake in an aircraft engine is linked to a shock attenuator so that movements of the flap near the closing position are strongly attenuated while movement about the fully open position is very little attenuated.

Abstract: An integrated thermal anti-icing and environmental control system for a gas turbine powered aircraft uses hot high pressure bleed air from the turbine compressor to de-ice the wings and the engine air inlet, and supplies conditioned air for the aircraft cabin. In order to minimize total bleed air requirements and maximize heat recovery, bleed air exhausted from the inlet anti-icing system is passed sequentially through other systems. In this invention, the usual pre-cooler unit and the associated heat sink are eliminated and the pre-cooling function is performed within the inlet anti-icing system, preferably through the use of a double skin heat exchanger contained within the lip of the inlet. One embodiment of this system includes a closed-loop liquid anti-icing system for acoustic rings mounted in the inlet wherein the liquid is heated by passing the bleed air through a heat exchanger mounted immediately downstream of the inlet anti-icing system.

Abstract: A particle separator for separating and removing foreign particles from engine inlet air incorporates a plurality of identical channel assemblies. The channel assemblies are arranged in side-by-side fashion in a defined panel area. Separation is achieved by accelerating the particles to a high velocity and bending the airstream such that the particle inertia carries the particles into a capture area. A small percentage of the incoming air is used to induce particulate matter to proceed into the capture area. By use of a turbulence generator particulates are kept in suspension in the capture area to enable easy exhaustion overboard.

Abstract: The invention relates to an improvement to an installation for preventing the ingress of super-cooled water, ice, snow and other debris as taught in U.S. Pat. No. 3,329,377. In the patent, an inertial separator effect is used to prevent ingress of super cooled water, ice, snow and other debris to an aircraft engine. The effect is obtained by an installation including a duct formed in a sub-nacelle of the engine to extend generally longitudinally of the engine. An air deflecting surface in the duct confines the incoming air to a passage of reduced cross section, and an opening in the duct wall downstream of the deflecting surface is formed between the trailing edge of the deflecting surface and the leading edge of a rearward portion of the duct, the opening in the duct wall communicating with the engine air intake. In accordance with the present invention, any or all of the following improvements are made to the above installation:A.

Abstract: A ram air filter for light aircraft comprising a parallelepiped housing and a replaceable filter element is disclosed. The housing comprises a base element and a cover element, which are injection molded of high impact plastic and are connected together in a snap-lock manner. The parallel faces of the base and cover elements include a plurality of ribs that define aligned apertures through which incoming air enters and leaves the housing. The ribs are formed such that they present a minimal amount of surface area to the incoming air stream during flight. A plurality of 90.degree. locking studs attach the housing to the air intake channel of the aircraft's carburetor. The replaceable filter element is also parallelepiped in form and lies in the space defined by the housing so as to filter the air flowing through the aligned apertures. The replaceable filter element is formed of a compressible foam, preferably having a porosity grade lying in the range of 20-50 pores per linear inch.

Abstract: A supersonic two-dimensional intake arrangement for two or more jet propulsion engines has a duct for each engine, a mouth region for each duct, said mouth regions being positioned in adjacent rearewardly staggered rearwardly such that at least one shock wave is common to all mouth regions. Preferably one duct wall is common to adjacent intake mouths.