Abstract: A temperature regulating arrangement (7) at least partially surrounds a fuel or oxidizer storage tank (1). The tank (1) is divided by a polymer membrane (3) into a first partial chamber (2) receiving the fuel (2′) therein, and a second partial chamber (4) receiving a gaseous pressure medium (4′) therein. The temperature regulating arrangement (7) includes thermal insulation, at least one heater, at least one heat sensor, and a temperature control and regulating unit. By heating the second partial chamber containing the gaseous pressure medium, any fuel vapor permeating through the membrane (3) from the first partial chamber (2) into the second partial chamber (4) is prevented from condensing within the second partial chamber (4). The permeation process is also limited. It is simply necessary to maintain the second partial chamber (4) at a temperature a few degrees Celsius higher than the temperature of the liquid fuel.

Abstract: An improved tilting rotor aircraft, a control system for an elongated shaft, and a method of controlling an elongated shaft are provided. Sensors are utilized to detect an amount of twist on a flexible and elongated shaft. A controller receives the signal and generates a command signal. A plurality of actuators receive the command signals and compensate for the twist in the flexible and elongated shaft.

Abstract: In accordance with the present invention, there is provided an aerodynamic control device for integrated use with an aircraft having an inboard lifting member. The inboard lifting member having a leading edge, a pair of opposing distal edges and a trailing edge. The control device is provided with a movable outboard member which extends substantially about the leading, distal and trailing edges of the inboard lifting member and is spaced apart therefrom. The outboard member is provided with a leading edge portion, a pair of opposing distal edge portions, and a trailing edge portion. The leading, distal, and trailing edge portions are movable in relation to the inboard lifting member to form an airfoil surface extending about the inboard lifting member and the outboard member for achieving aerodynamic control of the aircraft.

Abstract: A redundant ice management system and method to de-ice and anti-ice an aircraft member (150) is provided. The system comprising a primary ice management sub-system (154) for providing thermal ice management to the aircraft member and a secondary ice management sub-system (172) for providing back-up thermal ice management to the aircraft member (150) in the event of a failure by the primary ice management sub-system (154). The system provides primary and secondary de-ice and anti-ice capabilities to the aircraft member (150) before and during airborne operation.

Abstract: A single-stage earth-to-orbit launch vehicle employs a combination of rocket engines and turbojet engines to propel a device into orbit. The vehicle is driven through a unique set of operating conditions of the engines to conserve oxidizer and optimize acceleration. Cooling effects of fuel used by both types of engines is employed to maintain operating temperature of the turbojet engines within limits of lightweight materials. The rocket engines are used during initial acceleration and then permitted to remain deeply throttled or idle until the vehicle reaches a speed of about Mach 6. The rocket engine, with most of its oxidizer intact, is then used to accelerate the vehicle into orbit.

Abstract: A gyroscope suitable for a remote-controlled helicopter is provided that can improve the control characteristics to a disturbance factor such as wind as well as the response characteristics under yaw-axis control in a correct pitch operation. The angular velocity detection signal from the yaw-axis angular velocity sensor 10 is added to the yaw-axis control signal and the angular velocity reference value from the controlling gear. The PID controller 2 receives the resultant addition signal. The control signal from the PID controller 2 is added to the correct pitch control signal and the yaw-axis control signal sent via the correct pitch to yaw-axis control mixing unit 3. The actuator 6 receives the resultant addition signal and controls the yaw-axis driving unit 7. The yaw-axis angular velocity detection sensor 10 detects the angular velocity around the yaw-axis of the airframe 9.

Abstract: Blue icing can be prevented by an apparatus inside an aircraft. A sump is provided which has a removable screen cover disposed over an open-top container. The sump is placed underneath the aircraft's service valve, between the service valve and service door, to collect leaked aircraft lavatory fluid. A level sensor switch placed on an interior wall of the container senses the level of the fluid in the sump and activates a pump inside the sump when the fluid reaches a predetermined level. A recirculation loop has a recirculation hose in circuit with a one-way valve. The activated pump pumps the fluid through the recirculation loop. The recirculation loop leads to a three-port fluid return fitting, allowing the pumped fluid to return to the lavatory fluid reservoir. The fluid return fitting connects to the recirculation hose, lavatory fluid reservoir and to a vent hose equilibrating the pressure within the reservoir with the ambient pressure of the aircraft's interior.

Abstract: A mobile blower or fan is used to inflate the envelope portion of a hot air balloon. The fan includes a propeller which is driven by a gasoline/fuel engine and the engine is mounted on a wheeled base and is covered by an encompassing cage. By means of wheels attached to the base, it is possible to move the fan or blower on all types of terrain as needed.

Abstract: A synchronized target subsystem for use in an automated docking system for docking a chase vehicle with a target vehicle wherein the chase vehicle is provided with a video camera for feeding digitized frames to an image processing unit which controls a timing circuit. The timing circuit turns on the video camera to digitize a foreground frame and at the same time turns on a transmitter on the chase vehicle. A power generating antenna on the target vehicle receives the transmitted signal from the transmitter and actuates lights on the chase vehicle so that these lights appear in the foreground frame. After the foreground frame has been grabbed, the timing circuit turns the transmitter off and signals the video camera to digitize a background frame. The image processing unit subtracts the background frame from the foreground frame and provides a docking signal.

Abstract: A occupant protection system for protecting an occupant of a motor vehicle, boat, or airplane during a crash. The occupant protection system includes a chair positioned inside a vehicle such as an airplane, automobile, truck, or a boat. The chair has a seat portion and a backrest portion. The seat portion has a pair of leg clamp panels pivotally coupled to it to lock a pair of legs to the seat portion in anticipation of a crash. The backrest portion has a pair of arm clamp panels pivotally coupled to it to press the arms and torso of a user towards the backrest and hold them tightly therebetween. Also disclosed is a capsule in which the chair is disposed. The capsule has several protective layers. An emergency raft forms part of the backrest of the chair when not in use, and is removable for use in case of an accident on or above water.

Abstract: A fairing for protecting a payload from excessive acoustic energy is disclosed. The fairing can be used with a launch vehicle for launching payloads such as satellites or the like. The invention provides structure to surround a payload and absorbs acoustic energy so that the noise is suppressed to acceptable levels and the payload is not damaged. The fairing comprises a two dimensional honeycomb core having composite face sheets and load skins bonded to each side of the core. A water barrier is connected to the inner side of the fairing to prevent moisture from entering the payload area. The fairing may include an energy absorbing blanket connected to the inner side of the fairing to further suppress the energy generated by a launch vehicle.

Abstract: A vehicle that combines the freedom and swiftness of flight with the utility of surface travel. A simple, light weight, safe and stable conveyance with positive yaw-roll coupling, special safety features, no fold wing stowage and a unique single power source. It can be built using common tools and techniques with readily available materials at a cost competitive with the family automobile.

Abstract: A brake for a flap adjusting mechanism and a method for condition monitoring are proposed. The brake has one or more temperature sensors (30). In the method for condition monitoring, the temperature signal is compared with a desired temperature (T1, T2) in the signal processing unit in a time period during or after a rotation of the driveshaft (2) in the housing (4) while expending the braking moment. An error signal is produced in case of deviations of the temperature signal from the desired temperature.

Abstract: A improved tilt rotor aircraft comprising an airframe, at least one wing member coupled to the airframe, and at least one tilt rotor assembly carried by the at least one wing member. The tilt rotor assembly is actuated by a conversion actuator. The improved tilt rotor aircraft includes a low-height tunable downstop assembly for absorbing oscillatory vibration loads, such as pitch loads and yaw loads. The low-height tunable downstop assembly comprises a pivotable striker assembly having an adjustable stiffness, and a cradle assembly adapted to releasably receive the striker assembly. The striker assembly is attached to the tilt rotor assembly and the cradle assembly is attached to the wing member. A plurality of sensor modules are bonded to the cradle assembly. The sensor modules include a plurality of strain gages arranged to sense shear strain in the cradle assembly. The sensor modules are electrically coupled to sensor circuits and flight control computers.

Abstract: A large scale parafoil apparatus which makes use of an energy attenuator positioned between the initially deployed drogue parachute and the parafoil for controlling the initial stages of deployment thereof and significantly reducing rebound to enhance the deployment of the parafoil canopy in an orderly manner with the suspension lines thereof extending from the canopy to the load retained therebelow being maintained under continual tension during canopy deployment for enhancing rapid and full deployment thereof. The energy attenuating device is a ripstitch modulator having preferably multiple ripstitch sections for gradually decreasing the force resistant to separating the drogue from the parafoil and ultimately completely separating to allow full deployment of the parafoil canopy. The parafoil canopy defines a plurality of air cells with one main air cell being deployed in the lateral central location thereof.

Abstract: A system (300) for determining the ephemeris and attitude for a spacecraft includes ephemeris and attitude determining subsystems (700, 800) that obtain ephemeris data (708, 806) for one or more reference spacecraft crosslinked to the spacecraft. Crosslink sensor pointing information (706, 802) is obtained for the crosslink sensors. The satellite ephemeris and attitude (712, 810) are then calculated with ephemeris and attitude determination algorithms (702, 804) based on the ephemeris data (708, 806) and crosslink sensor pointing information (706, 802). Other available information, such as stored results of previous measurements and calculations, time (710, 808), spacecraft attitude (704), information from non-crosslink sensors and ranging information may be used to enhance the accuracy or decrease the complexity of the ephemeris calculations.

Abstract: A leading edge (50) for an aircraft has a hard durometer elastomer tip (52). An elastomer panel (54) has a first end attached to the hard durometer elastomer tip (52) and has a plurality of reinforcing members capable of freely sliding inside the elastomer panel (54). A rigid block (58) is attached to a second end of the elastomer panel (54) and is attached to a structure (62) of the aircraft.

Abstract: A life preserver for aircraft includes a fire-protective, anti-knock, inflatable bag defining an inflatable chamber and a life chamber within the inflatable chamber and having an exit, a bumper frame structure supported inside the life chamber for protecting the user in the life chamber, a safety helmet with a mouthpiece connected to an oxygen cylinder mounted in the bumper frame structure for providing oxygen to the user, and a parachute carried on the inflatable bag on the outside and controlled by a rip cord suspended inside the life chamber.

Abstract: A method and apparatus for actively enhancing aircraft weapon separation by actively modifying the flowfield characteristics of an open, shallow weapons bay during flight is disclosed. The apparatus includes a source of high pressure gas in fluid communication with an injector located on the aircraft. A control valve controls the introduction of a flow of high pressure gas from the source into the injector. The injector is placed ahead of the nose of the weapon and directs the flow of the high pressure gas externally into the airstream of the aircraft in flight. The injection of the high pressure gas into the airstream initiates a flowfield in the open weapons bay similar to that which occurs in a deep bay, encouraging a flat, even weapons separation.

Abstract: A wing-drive mechanism is described that permits, with proper control, movement of a wing about multiple wing trajectories. The wing-drive is capable of independent movement about three rotational degrees of movement; movement about a flap axis is independent of movement about a yaw axis, and both are independent of changes in the pitch of the wing. Methods of controlling the wing-drive mechanism to affect a desired wing trajectory include the use of a non-linear automated controller that generates input signals to the wing-drive mechanism by comparing actual and desired wing trajectories in real time. Specification of wing trajectories is preferably also accomplished in real time using an automated trajectory specification system, which can include a fuzzy logic processor or a neural network. A vehicle that derives controlled motion as a whole from the wing-drive mechanism is also disclosed.