Abstract: This invention discloses a method for determining when an orbiting satellite (10) is eclipsed from the sun in order to remove control torques to the satellite (10) which compensate for the disturbance of solar pressure on the satellite (10). A current measuring device (46) measures the current traveling through a particular circuit associated with the satellite (10) which is indicative of the satellite batteries being discharged, as would occur during an eclipse. The measured current is applied to a threshold logic circuit (48) which sends a signal to a control compensator (36) if the measured current exceeds a predetermined threshold level. Consequently, the compensation provided by the control compensator (36) removes the compensation for compensating for solar pressure when the satellite (10) is in an eclipse. In a second implementation, the threshold logic circuit (48) is replaced with a proportionality logic circuit to compensate for the effects of partial eclipses.

Abstract: A combination seat cushion and life vest particularly adapted for use as an aircraft chair includes a generally rectangular buoyant main rear panel and a buoyant segmented front panel hingedly joined to the rear panel in substantially covering relationship thereto so as to form, in a closed position thereof, a generally rectangular cushion of generally uniform thickness and, in an open position thereof, an openable and wearable life vest sized and dimensioned to cover the rear side and front side of a user from the shoulder to approximately the waist.

Abstract: Airbags are positioned relative to an aircraft yoke so as to minimize undesired force application to that yoke upon actuation thereof. The airbag actuation is accomplished by sensors which are capable of responding to multiple traumatic forces upon the aircraft to either establish multiple actuation of a common airbag, or actuation of separate airbags, upon occurrence of each event. The airbags can assume a side lobe configuration so as to minimize the possibility of impact upon side posts, or the interior side of the aircraft cabin structure. The sensors are arranged in an array with common directional alignment for maximizing probability of appropriate actuation. Use of multiple sensors and majority voting circuitry enhances the reliability of the systems and process.

Abstract: An aircraft berthing seat including a seat base; a support assembly borne by the seat base and moveable along a predetermined path of travel; a leg rest assembly borne by the support assembly, and moveable to predetermined supporting positions; a seat cushion assembly borne by the base and disposed in spaced relation relative to the support assembly; and a seat back assembly borne by the seat base and moveable along a path of travel from an upright position, into substantially coplanar relation relative to the seat cushion and leg rest assembly, respectively, thereby forming an aircraft berthing seat.

Abstract: An aircraft landing locking pin (12) automatically repositions from an engage position, wherein a rotating portion (15) of the landing gear is prevented from rotating, to a released position, wherein the rotating portion if free to rotate, in response to excessive side loading on the landing gear. The locking pin comprises a spring loaded actuator (32,34,60) which urges a roller (19) of a lock pin assembly (20) in contact with a bushing (22). In response to a side loading on the landing gear in excess of a predetermined loading, the locking pin is automatically released wherein the roller is expelled from the bushing. The threshold loading is determined as a function of the spring force applied to the lock pin assembly via the actuator linkage. The locking pin automatically reengages when the lock pin assembly is aligned with the bushing.

Abstract: A pneumatic and load-supporting spring device for use in bedding, cushions and the like. The disclosed embodiments have tubular telescoping members that are biased apart by either an elastomer located in the overlapping region, or a helical spring located within the pneumatic cylinder formed by the tubes. A conical or dish-shaped head element with clips for securely engaging a typical wire grid found in many bedding products is also disclosed, as well as a dish-shaped head element using cooperating lobe and trough pairs to hold a grid wire therebetween to fix a spring device in place. A foot element is also disclosed for use in attaching a spring device on the base frame of a typical bedding product. The foot element can straddle and snap into a metal frame rail, or be stapled to a frame rail.

Abstract: A composite wing for an aircraft comprises a plurality of elongated hollow one-piece composite spars arranged in juxtaposed generally parallel relation in an array defining an airfoil with a composite skin disposed about said assembled spars.

Abstract: A device for thermal protection of a structure (22) is provided. In one embodiment the device comprises a retention layer (12) impregnated by a fluid substance that is normally in the liquid state. The fluid substance is resupplied to the retention layer via a porous membrane that is impermeable to the substance when it is in the liquid state but is permeable thereto when it is in the vapor state. The membrane is interposed between the retention layer and a supply space for the substance in its liquid state adjacent the structure to be protected.

Abstract: A kite of delta shape having a frame and sail defining a keel and a pari of wings. Primary and secondary bridle lines are connected together and to the frame and carry connectors, two being located for dual line control and four being located for quad line control whereby the flyer can select either type of control depending on the desired variation he may wish in the maneuvers of the kite while flying.

Abstract: An electrically insulated support or the like is mounted on a helicopter to extend from both sides of the helicopter. A bucket for equipment, material and/or a worker is provided, which can be engaged or disengaged at the end of the support. To carry out operation on a high voltage line or installations, the bucket with its equipment, material and/or worker is hooked at one end of the support and is carried by the helicopter to a location of the high voltage line or installations where an operation has to be carried out. The operation is done while the helicopter holds the bucket or most preferably, the bucket which is provided with suspension wheels is mounted on the line conductors or installations and the helicopter is moved away while the operation is being carried out.

Abstract: A deployable system for assisting flight control under certain flight conditions, such as at high angles of attack, whereby two inflatable membranes are located on the forebody portion of an aircraft on opposite sides thereof. The members form control surfaces for effecting lateral control forces if one is inflated and longitudinal control forces if both are inflated.

Abstract: An electroexpulsive deicing system 18 in accordance with the present invention includes a plurality of expulsive elements 18, 22 comprised of printed circuit boards 12 having a plurality of parallel metal lines 14 formed thereon in a predetermined pattern. Adjacent expulsive elements have current flowing in opposite directions for creating expulsive electromagnetic forces between elements.

Abstract: An in-flight hose-and-drogue refueling system has the capability of steering the drogue using four thrusters which are energized by pressurized air. The system measures the drogue's 3-dimensional position relative to either the refueling aircraft or the probe on the receiver aircraft. A control system utilizes the measurements of the drogue's 3-dimensional position to activate the thrusters so as to either minimize the excursions of the drogue due to turbulence, thus enabling easier hook-up, or alternatively, to track the receiver's probe and automatically guide and contact the drogue to the probe.

Abstract: A tank system for an aerial liquid delivery comprises a liquid tank having an aperture for discharging liquid and a door for the aperture. The door has a seal and a door operating mechanism to remotely open the door a predetermined amount. There is an air pressure reservoir separate from the liquid tank connected to the liquid tank, and source of compressed air to pressurize the air pressure reservoir and liquid tank. The method of liquid delivery from the aircraft involves providing air pressure to a liquid tank, the tank having a door in an aperture for discharging liquid. The pressure provided to the tank before and during liquid discharge from the tank controls the flow of liquid discharging through the aperture.

Abstract: A quad-line kite having a sail shape consisting of a center rectangle or square and two outside pentagonal sections, one horizontal and at least two vertical spars, three strips of vent screen along the spars, and four control lines each attached to one quadrant of the kite, such that the kite can be flown at virtually equal speed in any direction or rotated about its axis in either direction, due to the unique balance of sail warping and air spilling capability, and also having a high sail area to weight ratio, enabling it to be flown in light as well as strong winds.

Abstract: A supply system for passenger aircraft uses one or more catering containers which are loaded with the aid of the aircraft's loading system into the cargo hold of the passenger aircraft and positioned in vertical alignment with a supply distribution and work cabin on the passenger deck or floor of the aircraft. A horizontal conveying system is capable of moving transport carts or standardized packages in the directions of a rectangular coordinate system for bringing carts or packages into a lifting position. A vertical lift cooperates with the horizontal conveyor system for bringing trolleys initially held in the carts or standardized packages into the distribution and work cabin. Instead of equipping the catering container with a horizontal conveyor system that works in the X- and Y-direction, it is possible to use any other robot system for retrieving standardized packages and/or trolleys from the catering container.

Abstract: An aft facing step situated across the span of an airfoil. A chemical or thermal deicing or running wet anti-icing device is located in or on the airfoil upstream of the step, and causes water to run back towards the step. The step suddenly reduces the thickness of the airfoil chord section, which causes a disturbance in the boundary layer across the span of the airfoil downstream of the step. The aforementioned disturbance causes runback water to form droplets and be blown clear of the airfoil surface downstream of the step, thereby preventing ice from being formed on the airfoil surface downstream of the step.

Abstract: The boundary layer of a fluid travelling in a mean-flow direction relative to a surface of a wall of a body is controlled by generating in a near-wall region of the flow a magnetic field B having flux lines parallel to the surface of the wall and an electric current density J traversing the magnetic flux lines in the fluid. An electrolyte or other conductivity-enhancing material is introduced into the flow to provide an electrical conductivity gradient in the near-wall region. The magnetic field B and the electric current density J create in the fluid a force J.times.B having a component normal to the surface of the wall that because of the increased conductivity gradient near the surface can stabilize or destabilize flow in the boundary layer. Numerous aspects of the fluid flow and its interaction with the body can thus be controlled.

Abstract: An aviator suit is provided with a sewn-on channel of hook and eye material which encloses an elongated line that extends to a floor bracket by a shear fastener. The enclosed line prevents snagging on objects within a cockpit and becomes easily removed when the VELCRO gives way during ejection when forces are exerted upon the enclosed channel line. A simplified snubber plug is releasably clamped to the aviator's seat and becomes released after the aviator has cleared a cockpit.

Abstract: A mechanism locking and controllably releasing two space vehicles along a preselected separation axis. The mechanism including a mechanical lock/release and a spring separation device that controllably forces the two space vehicles apart. An electrical interconnect maintains electrical communication between the two space vehicles when locked together. The two space vehicles can be reliably separated by activating a single disengagement actuator.