Abstract: Aircraft engine low thrust detection system having sensors for each engine mounted on the engine nacelle in the slip stream of each propeller. A given amount of decrease in engine thrust is detected by a thrust sensor and a signal is generated for a control device. The control device in turn activates a visual signal on the appropriate propeller control level in the cockpit informing the pilot which engine is losing thrust and whether the power loss is partial or total. Aural signals are also installed with different pitches to assist the pilot in identifying the engine which is losing power.

Abstract: An adapter for existing tow bars or spotting dollies to tow aircraft having on-conventional landing gears has a vertical member which is dimensioned to fit into a socket mounted in the bottom of the aircraft in the vicinity of the nose or tail. A structural cross member, integral with the bottom of the vertical member, has holes in the ends which receive the axle pins located at the ends of the tow bar arms or the lifting arms of the spotting dolly.

Abstract: A console assembly, suitable for example, for an aircraft cockpit, including a fixed structure, having a display area (1) permanently presented to, for example, a crew member, a movable panel (2) having a flat face region (3) and a flat edge region (4), both of rectangular form, the edge region being of substantially less area than the face region, a recess (5) in the fixed structure with a mouth (6) formed in the permanently presented display area (1), mounting means (7, 10) mounting the movable panel (2) on the fixed structure (1) for movement between a stowed position in which the movable panel (2) lies within the recess (5) with its edge region (4) presented to the crew member at said recess mouth (6), and a display position in which its face region (3) is presented to the crew member in front of the permanently presented display (1).

Abstract: A thermal indicator with a sensor (28) mounted over the wing stubs (12, 13) of a sailplane to detect relative movement therebetween due to bending moments applied to the wings on meeting a thermal and a processor of the sensor signals to generate signals indicative of the direction to be turned to enter the thermal. The processor signals are suitably displayed to indicate thermal strength, and left or right directions to enter the thermal.

Abstract: A glide path instrument for an aircraft to display to a pilot that the aircraft is descending on a predetermined inclined glide path. The instrument includes a rectangular casing mountable in stationary position in the aircraft and carrying a freely pivotable frame which has sighting elements at opposite ends spaced different vertical distances from the plane of the frame. The frame carries a pendulum-like structure including depending legs supporting free swinging weights. The sighting elements align in a single sight plane with a runway reference point when the aircraft is at the predetermined glide angle. A lamp in the casing illuminates the sighting elements.

Abstract: A camouflaged and deceptive preception distorted aircraft comprising an aircraft fuselage with nose tail top bottom and side surfaces having a real cockpit canopy on the top surface with length, width and height dimensions and a simulated cockpit canopy on the bottom surface positioned substantially in the same general area as the real cockpit canopy so that only one of the cockpit canopies is visible when the aircraft is perceived directly above the top surface or directly below the bottom surface, the simulated cockpit canopy having dimensions simulating the length, width and height of the real cockpit canopy, and at least one of the simulated cockpit canopy dimensions being greater than the corresponding length, width or height dimension of the real cockpit canopy; and the method for producing the simulated cockpit canopy.

Abstract: An alignment device for adjusting the takeoff assist thrust vector of a rocket booster in a desired relationship to the center of gravity of an autonomous missile. The device provides for using "plumb bob type" hanging tool prior to installing the rocket booster on the missile.

Abstract: An airborne refuse compactor to compact liquid laden trash for storage until the end of the flight. The compactor relies on the difference between pressure within the pressurized passenger cabin and outside pressure at operating altitude. The compactor also discharges to outside atmosphere liquid which has collected on the bottom of the receptacle in which the trash is collected. Liquid is discharged while compaction is taking place.

Abstract: Method for controlling humidity levels of internal ambient air for aircraft, utilizing air water separation devices for dehumidification strategically located so as to dehumidify ambient air prior to exhausting the air overboard from the aircraft. At least a portion of the water so recovered is utilized in fluid or vapor form to maintain desired humidity levels on the aircraft.

Abstract: A rain erosion resistant protective covering for aircraft having pointed or conical radomes and method of forming the protective covering. The protective covering is a layered material of polyurethane, contact adhesive, and polyethylene which is formed into the desired shape by precutting the material to the shape of the radome, placing the material in a mold, heating the material, and drawing a vacuum between the mold and material to draw the material into the shape of the mold, thus producing a cover having the shape of the mold.

Abstract: Various forms of V/STOL aircraft are disclosed, each having a tiltable exterior structure that is in the shape of a pair of connected partial circular conoids. In one general form the conoids house the thrust producing engines, whereas in another form they are immediately downstream thereof. Also provided is a sonic boom concentrator in the form of a fin having curved sidewalls and truncated ends.

Abstract: An aircraft 10 includes a pair of aerodynamic control members 11 pivotally mounted one to each side of the cockpit, each for movement about a pivotal axis P. A probe 13 is carried adjacent the outboard end of each control member in a predetermined orientation by fixed support means 25 anchored to the aircraft body and extending through the aerodynamic control member 11 adjacent the pivotal axis P. By this arrangement, the probe 13 remains in its predetermined orientation with respect to the aircraft irrespective of the angular disposition of the control member. The probe may be an air-data probe.

Abstract: A rudder gust control lock device is disclosed for securing the rudder and vertical stabilizer of single and twin engine airplanes to each other. The device includes a partial collet having a substantially U-shaped cross section and paired opposed flanges that extend from the extremities of the collet in a direction transverse to its longitudinal dimension. The collet is adapted to receive a leading edge of the rudder, and the flanges are adapted to slidably engage the adjacent surfaces of the stabilizer when the device is shifted along the rudder. A handle is included, that is attached to one of the flanges and extends in substantially the same direction as that flange, to enable the operator to grasp the device during installation and removal. A flag is also included, attached to the handle, to serve as a warning and reminder to the operator that the device is in position.

Abstract: A tactical wire-cutting system for helicopters includes a forwardly extending probe having a plurality of explosive cutting charges disposed along the probe. The probe is inclined with respect to the vertical as defined by the normal helicopter trim during flight such that a suspended cable will come into successive contact with the explosive cutting charges. The charges are designed to catch and hold the cable until detonation and thereafter to allow the cable to proceed to the next successfully positioned charge if unsevered.

Abstract: A camouflaged and deceptive preception distorted aircraft comprising an aircraft fuselage with nose tail top bottom and side surfaces having a real cockpit canopy on the top surface with length, width and height dimensions and a simulated cockpit canopy on the bottom surface positioned substantially in the same general area as the real cockpit canopy so that only one of the cockpit canopies is visible when the aircraft is perceived directly above the top surface or directly below the bottom surface, the simulated cockpit canopy having dimensions simulating the length, width and height of the real cockpit canopy, and at least one of the simulated cockpit canopy dimensions being greater than the corresponding length, width or height dimension of the real cockpit canopy; and the method for producing the simulated cockpit canopy.

Abstract: An impact apparatus responsive to a time rate of change of velocity of a housing is used to activate a system. A specific application of the invention fixes the housing to an aircraft body with an inertial member movably contained within the housing and uses the relative movement between the housing and inertial member upon impact to inflate and elevate a balloon above the aircraft.

Abstract: A thick panel is provided constructed of resilient deformable material and of a plan, size and shape to be snugly received in an airframe opening formed by the removal of an airframe stress panel. The resilient panel is positionable within the airframe opening in a manner fully closing the latter against the entrance of foreign material into the interior of the airframe from the exterior thereof. The thick panel includes an outer surface provided with a peripheral rabbet formed therein whereby the outer margin of the thick panel may be received beneath the airframe outer skin portions disposed about and defining the opening in which the thick panel is received. Further, the outer surface of the thick panel includes a flexible coating of substantially fluid impervious material.

Abstract: An aircraft instrument system for use on winged aircraft having an indicator visibly displaying a linearly variable ratio of a first pressure differential between a first pressure at a first location on the wing and a second pressure at a second location on the wing spaced from the first location and a second pressure differential between a third pressure at a third location on the wing and a fourth pressure at a fourth location on the wing spaced from the third location. An air pressure-electrical transducer is provided which is responsive to the first, second, third and fourth pressures for producing plural electrical signal outputs indicative of the individual pressures thus detected. An electrical circuit is responsive to each of the electrical signal outputs for producing a quotient signal representing the aforesaid linearly variable ratio. The indicator is responsive to the quotient signal. The air pressure-electrical transducer is fixedly mounted inside a compartment in the wing of the aircraft.

Abstract: Disclosed is a lock to lock open the speed brake doors of an aircraft to facilitate servicing the brake mechanism. The lock cooperates with lightening holes in the internal stiffening structure of the speed brake. The lock is adjustable to provide different amounts of brake opening. Surfaces of the lock that contact the aircraft speed brake structure are fabricated of resilient material to protect the aircraft.

Abstract: The device retains the ejection seat arm/dearm lever in safe position to allow the seat to be tilted safely for required maintenance and repair work. A bolt positioned through a clearance hole in an inverted U-shaped base member engages threads in the ejection seat structure. An upstanding brace extends upward from one end of the base member at an angle to abut the seat ejection arming lever to physically block and prevent its movement into the armed position. The bolt is retained in the base member by a cotter pin through the body of the bolt under the head to allow turning while preventing separation from the base.

Abstract: A disconnect device for an aircraft survival kit including a container and a lid secured thereto with a torso harness and anti-rotation strap associated therewith. The disconnect device includes a body adapted to be mounted relative to the kit, with the body including a recess, in accordance with one embodiment, adapted to enclose a portion of the kit therein, and a support assembly extending outwardly from the body and including a cavity adapted to receive an end of the harness therein. A locking device is provided and adapted to extend through the support assembly and the end of the harness to provide securement of the harness to the kit so as to obtain removal of the harness from the disconnect device for replacement thereof when the locking devise is disengaged such that the lid may remain secured to the container when the harness is replaced. The support assembly includes a pair of spaced apart arms integrally joined with the body and defining the cavity for receiving the end of the harness therebetween.

Abstract: An electronic warning system that alerts a pilot of light-weight foot-launched aircraft that the required pre-launch physical hook-up of pilot-to-aircraft has not been accomplished.

Abstract: Wind driven apparatus for the production of power at a ground location includes an aerodynamic lift generating vehicle capable of maintaining a stable airborne orientation, a tether linking the vehicle to a ground location, mechanical power generating equipment carried by the vehicle and responsive to relative motion between the air and the vehicle, apparatus for converting the generated power to reciprocating motion and structure for transmitting the reciprocating motion along the tether to the ground.

Abstract: An airplane angle of attack and direction of flight indicator includes a vane on the outside of the fuselage which is pivotally movable in response to changes in the airplane's angle of attack. A group of optical fibers are supported within the airplane with one end positioned for exposure to a light source. A light shield is movable into and out of blocking relation between the light source and optical fibers in response to pivotal movement of the vane. With the opposite ends of the optical fibers arranged in an indicator in the airplane cockpit, the illumination of fibers at the indicator affords a ready indication of the airplane's angle of attack. With the opposite ends of the fiber arranged in vertically spaced relation, a sighting device may be interposed between the pilot and indicator for establishing a line of sight along the actual direction of flight.

Abstract: A device for locking the ailerons and elevators of an aircraft controlled by a wheel-operated longitudinally shiftable and rotatable control column, and, at the same time preventing theft of the navigational instruments and radio equipment mounted on the instrument panel in the cockpit of the plane. The protective device takes the form of a cover plate mounted immediately adjacent the instrument panel by means of upper and lower clamping blocks secured about the control column in such a manner as to prevent unauthorized movements of the column and access to the instruments on the panel. The blocks have complementary semi-cylindrical grooves which clamp about the control column, and one block is fixed to the cover plate while the other has sliding, tongue and groove engagement to couple with said one block and clamp the control column against movement. The pair of blocks are held in clamped arrangement by a padlock whose shackle passes through aligned apertures in the blocks.

Abstract: A camouflaged and deceptive distorted vehicle comprising a top and bottom surface, the surfaces having pairs of coordinate sections including a fore and aft coordinate sections pair and a second left and right coordinate sections pair, at least one of the two pairs of coordinate sections of the top surface being colored, and the color on at least one of the two pairs of coordinate sections of the top surface graduating from dark to light beginning dark on one section and ending light on the other section, and including the method of assembling such vehicles.

Abstract: Process of landing an airplane on a solid landing surface covered with a layer of water comprising the steps of forming and maintaining a curtain of gas from a point forward and outboard of each of the landing wheels of an airplane on each side of the fuselage thereof to a point forward and central of the wheels and thereby displacing the water of the layer of water from the path of those landing wheels on that solid surface and later releasing the water from the curtain of gas at points lateral of each of the landing wheels while moving the gas curtain and airplane forward at a sufficiently high rate of speed to maintain the landing wheels in contact with the dry surface. Structural modifications of conventional cascade type thrust reversers and target type thrust reversers are provided to accomplish the steps of such process.

Abstract: The method and apparatus for conducting inspections and maintenance activities of this invention reduce the time required to conduct inspections and perform maintenance upon the aircraft structure and various systems, such as electrical and hydraulic, contained within the confined space located beneath the main deck of an aircraft by providing ease of movement for the individual and his tools. Additionally, this invention reduces the hazards associated with movement through the confined space and bulkheads under the main deck of an aircraft. The inspection and maintenance apparatus of this invention includes a trolley of proper size for a person and tools mounted upon parallel rails which are contained and extend longitudinally within the confined space under the main deck of an aircraft. The trolley is placed upon the rails at mounting points which are located under access panels in the main deck of the aircraft.

Abstract: This anti-theft device has a plurality of arcuate metallic sections hingedly connected to be removably applied to an airplane propeller blade at one side of the propeller shaft and locked in place to prevent unauthorized removal. The device forms an eccentric weight mass which when the engine is operated, causes vibrations so severe that the aircraft cannot take off or fly successfully. A warning flag or banner is attached to the device and anyone at all familiar with aircraft operation will not attempt to take the plane.

Abstract: A heat dissipating instrument package of a spacecraft, located in a canister having walls in heat transfer relationship with the package, is maintained at a substantially constant temperature. Fixed conductance heat pipes on the canister walls are connected to variable conductance heat pipes, mounted on a radiator structure separated from the canister walls by a thermal blanket. The effective radiating area of the radiator structure is controlled by the variable conductance heat pipes in response to a comparison of a sensed temperature of the instrument package or the canister wall with a seat point value. The comparison controls a heater in a gas reservoir containing a non-condensable gas of the variable conductance heat pipe. To enable the set point to be varied over a relatively wide range, such a 0.degree.-30.degree. C.

Abstract: A method and apparatus to obtain performance data for maximum cruise economy on any particular aircraft by means of a device comprising three thin round flat disc concentrically mounted to one another. Various aircraft performance scales are imprinted upon the rotatable discs and there is provided an indicating pointer which may be set in a level position based upon the readings of the calibrated scales and based upon the throttle setting of the aircraft while in flight to give maximum cruise economy.

Abstract: A directional gyro for aircraft having on its stationary face plate, color zones referable separately to portions of the 360.degree. movable directional scale; each color zone indicating a particular entry procedure (direct, parallel, or tear drop) for the preselected radial.

Abstract: In the disclosed aircraft instrument and panel cooling apparatus, each instrument is cooled uniformly and efficiently by air flowing through a plurality of small orifices which surround the large apertures in which the instruments are mounted. The orifices are preferably closely spaced around the instrument apertures with a distance between orifices of the order of two to four orifice diameters and located within a range of up to six orifice diameters from the instrument case so as to provide a plurality of cooling streams of air which tend to coalesce to provide a uniform and tailored sheet of air for maximum cooling efficiency.

Abstract: A camouflaged aircraft, surface vessel, vehicle or the like comprising an aircraft having upper and lower surfaces and having a plurality of visually contrasting surface coatings thereon, the coatings having lines of demarcation therebetween the surface coatings comprising one light and one dark coating, the dark coating being on a major portion of the upper surface of said aircraft, the light coating being on a major portion of the lower surface of the aircraft, substantially all of the lines of demarcation of the coatings when viewed from the side of the aircraft generally paralleling the longitudinal axis of the aircraft, and substantially all of the lines of demarcation of the coatings when viewed from above the aircraft being generally diagonal with respect to the longitudinal axis of the aircraft and substantially all of the lines of demarcation running in substantially the same direction.

Abstract: An oil replenishment system provides a remote reserve oil tank and the plumbing necessary to fill the main oil tank or tanks of engines, especially aircraft engines during flight. This system includes apparatus to determine the quantity of oil pumped to any one engine so that a quantity gauge is not required on the engine. A selector valve located on the reserve tank which may be remotely controlled directs replenishment oil to the selected engine tank. The system is designed to be powered from the existing on board hydraulic power system.

Abstract: A heat pipe having one wall formed by the component to be cooled and the other wall formed by a cover plate which is a portion of the missile skin, wherein the component wall normally forms the evaporator section and the other wall normally forms the condensing section, has a conventional wire mesh wick connected between the condensing section and the evaporator section. A support plate is attached to the wick adjacent the cover plate. A bellows is connected between the cover plate and support plate to move the cover plate and wick against a spring and away from the cover plate if the skin temperature becomes excessive.

Abstract: A heat transfer system in which a fluid of substantial heat absorption qualities is caused to flow in successive heat absorption and heat dissipation phases, a latter having one or more differential modes. In the disclosed embodiment of the system, a cold plate-liquid boiler assembly provides flow paths for the successive phases, the differential heat dissipation modes being provided by the liquid boiler and by external cooling means alternatively included in a heat rejection circuit. Vent control apparatus associated with the liquid boiler tends to maintain a pressure therein conducive of boiling at selected temperature values.

Abstract: A rudder restraint for grounded aircraft includes a central rudder trailing edge engaging bracket that may be secured on opposite sides of an airplane empennage by anchor clamps attached to the bracket through nonextendible cords. The clamps are attached to leading edges of opposite horizontal stabilizers. The leading edge clamps, nonextendible cords and central bracket hold the rudder against movement about its pivot axis. A spring is connected in line with one of the cords to enable a uniform tension to be applied to both cords when the restraint is positioned on the aircraft.

Abstract: A lightweight, high-strength duct comprised of two thin annular tubes, one fitted within the other, the outer tube having spaced annular stiffening beads extending radially outwardly therefrom, and one of the tubes being vented to prevent pressure differentials between the inner surface of the outer tube and the outer surface of the inner tube at various altitudes and temperatures.

Abstract: A high temperature tape for use in protecting a structural item to be subjected to high temperature, and the method whereby this novel tape is made are set forth. The tape is principally constituted by a number of elongated carrier fibers disposed in an essentially aligned array, and a large number of comparatively short fibers disposed in a nonwoven manner essentially transversely to the elongated fibers. The short fibers typically extend beyond the confines of the carrier fibers, at least on one side, thus to create a pliable, fringed tape capable of being wrapped for a number of turns about an item to be protected. This wrapping may be done in such a manner that the fringe formed by the short orthogonally placed fibers is available to extend over and cover previous turns of the tape. The fibers are of temperature resistant material, and various means are provided for securing the short fibers to the elongated fibers, including the use of certain resins.

Abstract: Solid state spaced-oriented means convert solar radiation into microwave energy which is amplified and beamed to earth as a source of electrical power. A large number of semiconductor devices operating in the current multiplication region are irradiated by single mode coherent light beam generation means which is pumped by solar energy. A neodymium yittrium aluminum iron garnet laser or CW gallium arsenide junction diode laser mode-locked at a predetermined microwave frequency, such as 3,000 MHz provide for generation of a light beam. The generated current is directly proportional to the radiant energy and is coupled from the semiconductor device array to antenna means for transmission to earth stations for conversion into low frequency electrical energy.