Abstract: An active flight control arrangement for an air vehicle that includes a split span vee fin tail control arrangement whereby inner and outer spans of each fin are independently operable to provide yaw, roll, and pitch control for an air vehicle in flight. The inner and outer spans of each fin are preferably not, but may be, in the same plane. An intermediate controllable span may also be provided between the inner and outer spans of each fin.

Abstract: An apparatus and method for providing a specified amount of heat on a test specimen, a portion of a specimen, or multiple specimens, under space-like conditions. This system includes a vacuum chamber in which one or more test specimens are placed. This chamber is evacuated to the necessary vacuum. One or more external sources of high intensity light is used for providing the necessary temperature. One or more reflectors are used for concentrating the high intensity light. A fiber optic light guide is used for receiving concentrated light from the reflector. A port in the vacuum chamber wall is used so that the second end of the light guide can extend into the chamber so that light exiting the second end impinges on a selected area of the test specimen. A positioning apparatus is used for locating the second end of the light guide within the housing adjacent to vary the test specimen area subjected to the light.

Abstract: The device employs Hybrid Pulsed Transformer principles employing a projectile with an internal pay load. The projectile carries a light weight shorted secondary coil or coils constructed of aluminum and the projectile acts as a moving secondary through a plurality of aligned spaced apart transformer primary coils. The moving secondary coil includes a plurality of surrounding channels containing a liquid, such as water, for cooling. The cooling ability of certain liquids, as for example water, associated with change of state between liquid and gas is employed to cool the coil or coils.

Abstract: An improved mandrel for use in filament winding. Two embodiments are described for a new filament winding mandrel concept. The first embodiment comprises a plurality of spaced apart slots machined at an angle along the ends of the central mandrel section for use with machines of at least three degrees of motion. A second embodiment comprises a series of two circumferential rows of axial fins protruding along the circumference of the central section of the mandrel for use with machines having only two degrees of motion. A second configuration of the second embodiment is an addition of a strip of slots that are simply placed around and secured to the circumference of the mandrel at locations where fiber turn around is desired. This provides for fiber securing in place with minimal rather than requiring machining the axial fins into the tool.

Abstract: A deflated airbag is located on the outside of a missile or other vehicle beneath a folded, pivotally mounted airfoil member prior to launch, and a supply of pressurized gas is connected to the interior of the airbag via a suitable valve. After launch, or after lowering of a launch platform in the case of launch from an aircraft, an actuator such as an acceleration sensing device or timing device opens the valve, supplying gas to inflate the bag and simultaneously urge the airfoil into an extended, working position. After the airfoil is locked in its extended position, the airbag rapidly deflates and may be dropped off or retracted. Where more than one airfoil is to be deployed, separate airbags are located beneath each of the folded airfoils and a common gas supply is connected to all of the airbags.

Abstract: A process for manufacturing metal and ceramic matrix composite materials. The invention also encompasses various composite products made by the disclosed method. The resulting composite material comprises a reinforcement material in either continuous or discrete form embedded in a matrix material which is either a pure metal, a metal alloy, or a ceramic. The reinforcing material is optionally coated with a barrier coating material. An electric arc or plasma arc is used to spray a thin layer of matrix material over a preplaced layer of reinforcement material. Successive layers are built up until a desired object shape and thickness are achieved. There is an optional final step of high-temperature diffusion annealing or hot isostatic pressing.

Abstract: A cold vapor pressurization system for outer space vehicles that is used prior to and during engine burn to pressurize its fuel tank and oxidizer tank to produce the required engines net positive suction pressure (NPSP). The engine start system uses reaction control system (RCS) hydrazine to pass through a gas generator where it is disassociated. The by-products are then introduced into the hot side of the propellant heat exchangers. An oxidizer feed system and a fuel feed system pass through the respective cold sides of the heat exchangers to vaporize the propellants which are then used to produce the required engine NPSP for the oxidizer tank and fuel tank respectively. This system could also be used to provide engine NPSP during engine burn.

Abstract: An exhaust gas management system for missile launch arrangements which incorporates multiple launch cells exhausting into a common plenum. The system provides a flow passage configuration with a transition section that permits rocket exhaust flow gas to expand to fill the channel area downstream of the nozzle exit. Automatic aft closure members are included which serve to close off the flow passages to inactive cells while providing an open passage for exhaust gases from an active cell undergoing a missile firing. This arrangement prevents back flow or recirculation of exhaust gases into the volume in the cell which is upstream of the rocket nozzle exit.

Abstract: An improved wind tunnel six component balance having an outer shell assembly that receives a tubular inner rod and an axial member that is received within the interior of the tubular inner rod. The forward and aft ends of the outer shell assembly are connected to the inner rod. The loads imposed on the forward and aft ends of the outer shell assembly are transferred to the inner rod and into the tunnel support system. The central annular section of the outer shell assembly is connected to the axial adapters (four each and into the central disk of the axial member. The principal areas of the axial element are the central disk member, the flexures (two sets forward and two sets aft), the forward and aft gauged sections, and the forward and aft disk members. Normal force, side force, and rolling moment are carried by the outer forward webs of the outer shell assembly. The axial member will transfer the majority of the axial force then the forward and aft outer shell webs.

Abstract: An airplane has a control device for providing a directional moment to control yaw during high angles of attack. The control device includes a chine support member carried at the forward end of the airplane forward of the fuselage. The chine support member rotates about a chine axis which is parallel or coaxial with the longitudinal axis of the airplane. A chine is mounted to the chine support member, the chine having a pair of substantially flat, thin, flight control surfaces rigidly mounted on opposite sides of the chine support member. These flight control surfaces rotate with the chine support member to control vortices formed on the chine during flight to provide directional moments. A drive motor will rotate the chine support member to control the angle of the chine. A control means including the aircraft computer controls the drive motor.

Abstract: The purpose integrated aerospike rocket engine and space vehicle aerobrake is to provide for optimum installation and performance of these systems in a space vehicle. By integrating the aerospike engine into the middle of the aerobrake, the engine can be located with its center of gravity toward the face of the aerobrake. This location permits the maximization of the displacement of the aerodynamic center of pressure of the aerobrake relative to the center of gravity of the space vehicle, thereby maximizing the stability of the vehicle upon aerodynamic capture at the earth or another planet. By substituting an aerospike rocket engine for a conventional bell nozzle engine, the doors required to close the aperture in the aerobrake to accommodate the conventional engines can be eliminated. In addition to the unique combination of the aero-spike engine and the aerobrake, an included unique feature of the invention is the extendable nozzle plug.

Abstract: A filament wound composite structure, its tooling and method of manufacture. The isogrid filament wound composite structure is formed having at least one or more pseudo-isotropic laminate zones in its joint regions. This structure is realized through the use of specialized tooling. The ribs of the isogrid filament wound composite structure are discontinued by tapering them out into a thin skin. This is accomplished by gradually widening the grooves in the mandrel while simultaneously decreasing the depth of the grooves. This gradual change in the tooling redistributes the material in the ribs into a thin skin. The fibers that are redistributed into this thin layer, coupled with the skin wound over the top of the ribs, provide the necessary reinforcement in the joints.

Abstract: A method and arrangement for integrating a Global Positioning System and an Inertial Navigating System without the use of accelerometers to provided a velocity steering signal that is utilized in the guidance of a flying vehicle, such as a space craft. The method and arrangement do not require the use of accelerometers. A mechanization for interfacing the integrated Global Positioning System and the Inertial Navigating System with a flight control system which controls a flying vehicle is disclosed.

Abstract: An optical edge guidance system for automatic riveters. The guidance system utilizes a light source which directs light toward the material to be drilled/riveted, a video camera is also directed toward the portion of an object to be drilled/riveted and detects reflected source light from the material. The light from the source directed toward the material is angled about 10 to 15 degrees from the vertical. The material either is marked with a dark stripe or, for example, when the material cross-section is in the shape of a hat section, i.e. an aircraft longeron, a shadow is cast by the light striking the edge of the material and forms a dark area along the longitudinal centerline thereof. The edge of the dark stripe or shadow is detected by the video camera. The video signal from the camera is processed into a voltage equivalent of the video signal. A known reference voltage signal is established when the material positioned properly for drilling/riveting.

Abstract: Disclosed are formulations for producing chemical solvent admixtures that can be employed to clean a surface for further work; and that can be applied to cloths for the cleaning operation yet alleviate problems with solvent evaporation into the atmosphere to cause many legal and environmental problems, and a method of storing and disposing of cloths soaked with the formulation that alleviates current problems.

Abstract: A suspension system (28) for a track laying vehicle includes a support arm (30) that defines a cavity (36) and has a first end (32) about which the arm pivots under the control of a stationary crank arm (38) and a cylinder of (42) supported for swiveling movement by a swivel bearing (46). The cylinder (42) has a piston (48) that is connected to the crank arm (38) and which operates to compress suppression liquid within the cavity (36) to thereby control jounce and rebound movement of the support arm.

Abstract: Apparatus for cleaning paint spray gun nozzles automatically includes a housing having separate cleaning and reservoir chambers separated by a dividing wall, and a cleaning spray head in the cleaning chamber for directing a spray of cleaning fluid at a nozzle in the chamber. A supply of cleaning fluid in the reservoir is connected to the cleaning spray head by a supply tube. The cleaning chamber has an entrance for receiving a spray gun nozzle, and a supply of gas under pressure is connected to the reservoir chamber automatically on detection of entry of a spray gun nozzle through the entrance, to urge cleaning fluid from the reservoir into the supply tube. A passageway is provided in the dividing wall for returning used cleaning fluid to the reservoir. The supply of gas to the reservoir is cut off automatically at the end of a cleaning cycle on removal of the cleaned nozzle from the chamber.

Abstract: Video data is compressed, at a first site, by a transform scaling data compressor (12), and carrier signals are modulated with audio and digital data by a delta modulation data modulator (14) and a delta-sigma modulation data modulator (16) respectively. Their output signals are combined by a multichannel data compressor (18) and transmitted to a second site, where the procedures are essentially reversed to effectively regenerate the data as originally formatted.

Abstract: A solar concentrator panel having an array of off axis cylindrical parabolic mirrors with an optical design of relatively short focal length solar cells arranged in line that converts sunlight to electricity. The back surface of the mirrors are used as the solar cell mount and the heat sink for the adjacent mirror.

Abstract: An interface chip device, provided for use in a time-division multiplex serial data bus system is operable in a processor interface mode and at least one remote mode wherein the device is capable of directly interfacing with I/O devices. The system does not require software or processing capability for protocol communications or I/O control and, consequently, the communications protocol is transparent to the user, system developer or programmer. The communication protocol of the bus system includes a plurality of commands such that when in the remote mode, the chip device determines the validity of each of the commands and provides an echo response message on the data bus in response to each of the commands except for a broadcast command. The remote modes of the chip device include a remote switch mode, a data input mode, a data output mode or a combination of the remote modes.