Abstract: A metal skin trimming device which cuts an edge of a first metal skin to a net shape that is complementary to the edge of a second metal skin that has been previously attached to a frame, such as the airframe of an aircraft fuselage. A guide carried by the device is adjustable to set the gap that will appear between the edges of the first and second metal skins when they are attached as by riveting to the airframe.

Abstract: A tool for removal of round internally threaded collars from high efficiency aerospace fasteners. The tool includes a central cylindrical pin having a head at one end held against rotation, a non-round extension at the second end and a transverse bore intermediate the ends, containing a ball which is spring biased to project slightly beyond the pin wall. A mandrel assembly surrounds the pin and is rotatable relative thereto. A gripping collet is positioned between the mandrel and pin with collet fingers at one end extending beyond the mandrel and a threaded second end threaded into said mandrel. An axial slot in said collet is adapted to receive said ball when aligned therewith to form a releasable latch mechanism. In operation, the open collet fingers are placed over a threaded collar with said extension in engagement with a corresponding recess in the end of the bolt within the collar. The socket and mandrel are rotated in the collar unthreading direction.

Abstract: A method and system for improved performance of a V/STOL aircraft characterized by directing a major portion of exhaust gas flow from a propulsion system through a closed conduit means to exit through a thrust producing primary nozzle that includes turning apparatus for forming a bend for the exhaust flow downstream of the propulsion source; turning the exhaust flow while simultaneously bleeding-off through at least one secondary nozzle a second and minor portion of the exhaust flow from an outer portion of the bend downstream of the bend leasing edge to reduce the vortex formation in the bend and directing the bleed-off and exhaust flows adjacent each other and oriented in the same direction in all flight modes for recovery of the maximum thrust potential.

Abstract: A device for securing a workpiece to a fixture for performing machining operations includes a tubular, radially expansible mandrel. The mandrel is carried in a passage provided in the fixture and extends into a hole provided in the workpiece. An expander stem is carried within a bore of the mandrel. The stem has an upper end that is tapered for expanding the mandrel. The lower end of the stem is connected to a hydraulic piston. A spring applies an upward force on the mandrel. A hydraulic cylinder moves the stem downwardly, while the spring retains the mandrel in a stationary position until it grips the workpiece. Then, the hydraulic force overcomes the force of the spring to pull the mandrel downward slightly to secure the workpiece to the fixture.

Abstract: Disclosed is an orbital space transfer vehicle comprises essentially a composite hollow cylindrical body structure enclosing a spherical oxygen tank suspended and spaced from the inner wall of the cylindrical body structure, a hollow toroidal hydrogen tank suspended from and spaced from said cylindrical body structure, a main thrust rocket engine, and an aerobrake located at the aft end of the vehicle. This arrangement provides a vehicle with a very short length, lowers the required aerobrake size and maximizes vehicle controllability that may otherwise occur due to non-uniform distribution of the propellants during operation of the vehicle. Thus disclosed is a vehicle which can fully benefit from space basing, easily maintained while stationed in orbit, and transportable in a fully assembled state from earth to low earth orbit. Also disclosed is a space station with which the orbital transfer vehicle may cooperate while in space.

Abstract: A punch for setting a rivet has features to prevent swelling of the rivet between the two members being secured together. The punch has an elongated, solid blow transmitting member with a blow receiving surface and a shank. A sleeve is slidingly carried by the shank and movable from a position protruding past the lower end of the shank. The sleeve has a sidewall with at least one elongated slot extending therethrough. A pin is secured in the shank and extends laterally outward from the shank into the slot to retain the sleeve. A spring urges the sleeve downwardly.

Abstract: Disclosed is a single control thruster having the expanded capability of operating at various thrust levels and more than one propellant fluid so that the number of control thrusters for a maneuvering vehicle can be reduced to one third from that now required for appropriate maneuverability in space, resulting in large cost savings and improved reliability. Also disclosed is a "plug in" package with control thruster which can be removed from the vehicle and replaced to make the vehicle easily maintainable.

Abstract: A radar correcting system has features for providing a corrected radar receiver reflection to a Doppler process unit. The corrected receiver pulse accounts for variances in phase, amplitude and frequency of the transmit pulses. The system has a phase detector that detects the phase difference between a stable oscillator and the transmit signal, providing a complex video or real and imaginary outputs. An operator that will normalize the transmit pulse is determined. The operator is applied to the reflections received by the receiver antenna to remove from the reflections any vagaries due to varieties in the transmit pulses. The data proceeding to the processor deals only with the objects causing the radar reflection.

Abstract: A vehicle-mounted passive synthetic aperture system for locating sources of electromagnetic radiation having a given wavelength .lambda.. The system includes first and second receiving antennas, a phase sensitive receiver and a signal processor. The first and second antennas are mounted to a vehicle and spaced apart from each other in the principle direction of motion associated with the vehicle. The first and second antennas respectively provide first and second received signals in response to a wavefront of electromagnetic radiation having the given wavelength .lambda.. The phase sensitive receiver is coupled to the first and second antennas and responds to the first and second received signals by providing a phase difference signal that indicates a phase difference .phi. between the wavefronts of the radiation of the given wavelength received by the respective first and second antennas when the received radiation is radiated spherically from its source. The speed of the vehicle also is measured.

Abstract: A cover for openings in a partially assembled missile or aircraft structure to prevent entry of chips, oil or other debris during further machining or other manufacturing operations. The cover has a central elastically compressible plug section adapted to fit snugly in an opening and an outwardly extending flange around one end of the plug. When the plug portion is inserted into the opening, the flange covers a ring of bolt holes surrounding the opening. The plug is formed from an elastic closed cell foam material and preferably has a cross-section slightly larger than the opening so as to be compressed slightly when inserted in the opening. The cover is coated with an elastomeric polyurethane coating to prevent flaking of the foam plug when inserted and removed from the opening and to prevent adhesion of contaminates to the cover. Because of the compressibility of the plug, each cover can be used with similarly configured openings of slightly varying sizes.

Abstract: Electro-optical interface connections between electronic modules are used for data transmission rather than conventional pin and socket connections. Each module has on its top a number of diode pairs, one of the diodes transmitting light, and the other receiving light, and converting the light into electrical pulses. A data bus block is mounted across the tops of the modules. The data bus block has corresponding diode pairs that align with the diode pairs in the modules. Light pulses may be transmitted from the modules to the data bus block onto parallel data bus lines, then transmitted back to other modules from the data bus lines. On another side of the module, a serial electro-optical connection using a diode pair transmits to and receives light pulses from a fiber optic line for communicating with modules other than in the cluster.

Abstract: A self contained failure tolerant linear drive mechanism that is especially adapted for celestial space applications. First and second motors are concentrically connected to a shaft for axial movement through rotation of either or both of the motors. A locking mechanism having failure tolerant releasing means cooperates with each motor to provide for selective actuation of either motor and predetermined axial movement of the shaft.

Abstract: Disclosed is a method and apparatus for forming a cold weld joint between parts comprising a sleeve (or coupling) to receive the ends of conductors (or pipes). The sleeve is provided with weld pads which when the sleeve cools will engage one of the conductors and be cold welded thereto by the forces of shrink fit. Serrations are provided for axial strength of the joint and to limit the plastic flow of the material of the pads. A second conductor is loosely telescoped in the sleeve by bellows for compensating for any misalignment when the parts are initially brought together. Later the bellows is provided with a backing material to rigidly connect the second conductor to the sleeve.

Abstract: An easily separable but conventional-appearing hinge wherein the hinge flaps can be connected or disconnected to/from one another without relative lengthwise displacement of the flaps by employing short axial movement of the hinge pin. The flaps thus may be hingedly securely connected together, or disconnected and separated within limited space. The flaps have tubular knuckles with adjacent space or gaps so knuckles of one flap can be interdigitated with knuckles of the other flap and held together by the hinge pin. Knuckles of one flap are slotted longitudinally forming open sided or split tubes; those of the other flap are fully tubular, i.e., unslotted. The removable hinge pin has adjacent cylindrical and flat portions, the latter positionable in gaps longitudinally aligned with the full tube knuckles of one of the flaps.

Abstract: A store load and ejector device for carrying stores on the exterior of an aircraft or the like and for dispensing same at the option of a pilot comprising a cap plate for connecting with the aircraft, struts connected with the cap plate and carrying at their bottom ends support beams having ejector racks capable of selectively dispensing the stores and at least two cross braces connected to and between respective support beams forward and aft of the struts so as to maintain separation of the support beams and any stores thereon. The cross members and the struts have biconvex shape with leading and trailing edges sweeping at respective angles within the range of 20.degree.-50.degree. so as to present low radar reflection or radar cross section. The struts, support beams and cross braces have biconvex shape for reduced drag.

Abstract: A deployable truss structure particularly adapted to space applications which has high structural efficiency, packages in a volume efficient manner and can be remotely deployed in a controlled, sequential manner. The truss in its deployed configuration exhibits a "diamond" cross section. Each of the four sides of the structure is essentially a "Warren" truss. Diagonals on the opposite sides of each diamond incorporate a mid-span hinge and the other two diagonals are rigid tubes. When packaged, all elements of the truss are folded so that they are parallel to one another and contained between two guide rails. The guide rails are located on either side of the diamond truss. The horizontal strut connection points or nodes are fitted with rollers that are locked in the guide rails for movement therealong. At the start of deployment the upright truss members are lifted to the vertical position, forming the basic diamond shape of the truss.

Abstract: A mobile vehicle having a high degree of survivability against a nearby nuclear blast. The vehicle includes a chasis on which wheels or the like are mounted for movement along the earth's surface and a protective shell covering the vehicle. A skirt extends downwardly from the shell to a substantially uniform distance above the earth's surface during normal conditions. In the event of a nearby nuclear detonation, sensors on the top of the shell detect the initial flash and initiate braking, retraction of the wheels, and closure of any vents. The vehicle comes to rest on the skirts, which may include seals in contact with the earth. Blast overpressure and winds cannot leak underneath the vehicle. Overpressure on top then forces the vehicle tightly against the earth, preventing it from being overturned or blown away by the blast winds. Thereafter, the vehicle can return to its normal function, e.g. erect and launch a missile contained therein, extend the wheels and resume movement, etc.

Abstract: A device for securing a workpiece to a fixture for performing machining operations includes a tubular, radially expansible mandrel. The mandrel is carried in a passage provided in the fixture and extends into a hole provided in the workpiece. An expander stem is carried within a bore of the mandrel. The stem has an upper end that is tapered for expanding the mandrel. The lower end of the stem is connected to a hydraulic piston. A spring applies an upward force on the mandrel. A hydraulic cylinder moves the stem downwardly, while the spring retains the mandrel in a stationary position until it grips the workpiece. Then, the hydraulic force overcomes the force of the spring to pull the mandrel downward slightly to secure the workpiece to the fixture.

Abstract: A takeoff and landing platform for V/STOL aircraft has features to reduce ground effect. The platform has a plurality of vanes mounted above a flat horizontal surface. Each of the vanes is curved to turn the jet stream from the vertical. The upper edges of all the vanes lie in a plane that is parallel with the horizontal surface. This plane is located at a distance from the horizontal surface that is about 0.5 to about 2.0 times the engine nozzle diameter at takeoff and landing of the type aircraft that use the platform.

Abstract: A nosepiece for a drill motor. The nosepiece is adjustable to allow the nosepiece length to be changed rapidly to compensate for different drill lengths. The nosepiece is threaded to mate with threads on the drill motor housing and can be adjusted longitudinally along the motor center line axis. When the nosepiece is threaded along the housing to a desired location it is locked in place by a locking ring keyed to the nosepiece and fixed in position on the drill motor housing by a hand adjustable set screw.