Abstract: A method and system for determining the general three-axis attitude measurement for a spacecraft is disclosed. The system provides a cost-effective attitude measurement system for geosynchronous momentum bias spacecraft which need a continuously updated, moderately accurate, yaw measurement in addition to the usual roll and pitch measurements. The continuous yaw measurement enables control of the spacecraft yaw axis in the presence of disturbance torques. A sun sensor generates a signal which may be used to calibrate a continuously updated yaw measurement derived from the combination of signals generated by an Earth sensor and a space-to-ground link.

Abstract: A satellite telecommunications and remote sensing system including a plurality of satellites arranged above the Earth in short-period elliptical sun-synchronous orbits which have the following Keplerian parameters: an orbit inclination of 116.6.degree. on an equatorial plane of the Earth, a daily rotation of a nodal line of 0.9863.degree., an orbital period selected such that N orbital periods fit into M sidereal days, any desired argument of perigee and any desired value of the right ascension of the ascending node.

Abstract: A velocity command system is provided with a velocity stabilization mode wherein aircraft flight path referenced velocities are determined with respect to an inertial frame of reference, the flight path referenced velocities are held constant during pilot commanded yaw maneuvers so that the aircraft maintains a fixed inertial referenced flight path regardless of the pointing direction of the aircraft. Velocity control with respect to an inertial frame of reference is accomplished by controlling the aircraft flight path based on aircraft body referenced commanded lateral and longitudinal acceleration and based on aircraft body referenced lateral and longitudinal centrifugal acceleration. Operation in the velocity stabilization mode is provided in response to the manual activation of the velocity stabilization mode by the pilot, provided that the aircraft is already operating in the ground speed mode and the aircraft is not in a coordinated turn.

Abstract: An airplane passenger seat row is disclosed which comprises a seat frame, which is common to all seats and which includes cross members and feet that are fixed to said cross members. Seat cushion carriers and backrests can be adjusted in their position of inclination. A section of the seat cushion carriers and a section of the backrests are designed as components which can be moved in at least two positions in the longitudinal direction of the cross members. A backrest of a center seat includes a center section located between two side sections. Each side section is assigned a locking mechanism, by means of which in the one position of the moveable components both side sections can be connected shape-lockingly to the center section, in order to form sections of the center seat, and in the second position the side sections can be connected shape-lockingly to the seats backrest which adjoin laterally the center seat, in order to form sections of both side seats.

Abstract: This invention, and the associated methods, relate to fighting fires from aircraft. The invention, and the associated methods, also relate to early detection of fires; delivering liquids (primarily fire retardant or water) in a timely and accurate manner for the suppression of fires; and performing those functions under conditions of smoke obscuration and darkness which currently inhibit or prohibit aerial fire fighting. The novel capabilities detailed in this patent also allow for useful functions not now performed by airtankers such as, but not limited to, search and rescue; disaster damage assessment and recovery; law enforcement; natural resource protection such as dispersant spraying on oil spills, and avalanche control.

Abstract: An autogyro has a teetering semi-rigid rotary wing with rigid rotor blades. The angle of attack (blade pitch) of the rotor blades is fully adjustable in flight continuously over an operational range, and varies along the blade length. A prerotator rotates the rotor blades up to takeoff speed at minimum drag, no lift and optimum engine efficiency. Engine power is disconnected from the rotor blades and their angle of attack is changed for optimum lift to facilitate smooth vertical takeoff. Rotor blade pitch is likewise adjusted during vertical landing. In flight, rotor blade angle of attack is varied to adjust autorotation, lift and drag at any flight airspeed. On the ground, the rotary wing is braked to prevent rotation.The autogyro may roll, pitch, or yaw, with complete independence of blade pitch with respect to all other relative motions. The pedals have disproportionate forward and backward motions. The autogyro has retractable gear capable of fail-safe gear-up landing.

Abstract: An improved ice protection apparatus 8 includes a top polyurethane layer 10, an active layer 12, and a base layer 14 cured together into a unitary matrix, wherein the base layer is either polyurethane or chloroprene. The active layer may be either a thermal ice protector, a pneumatic ice protector, or an electro magnetic protection apparatus.

Abstract: A parachute deployment system having a pack with an attached parachute and a detachably coupled handle. The handle is used to activate the deployment system by physically opening the pack via an internal rip cord pin in communication therewith. Further, the handle is used to pull a pilot bag, which holds the parachute, from the pack and into the air stream. The pilot bag provides sufficient drag for effectively deploying the parachute therefrom.

Abstract: A leading edge slat wing combination where the slat is mounted to a pair of circularly curved carrier tracks positioned within the outer surface contour of the fixed wing. In moving from the cruise configuration to the take-off and climb configuration and thus to the fully deployed landing configuration, the slat has a fixed angular orientation relative to the carrier track. This eliminates the need for auxiliary track assemblies of the prior art that are used in addition to the carrier tracks to change the angular position of the slat for the high lift configuration. Also, in two embodiments, the slat, in the take-off and climb configuration, forms a gap or slot with the fixed wing, and the gap or slot is sealed in the vicinity of the carrier tracks.

Abstract: A quick release coupling apparatus and method used to connect and quickly disengage a night vision assembly from a pilot's helmet. The quick release coupling apparatus includes a locking element disposed on a pilot's helmet. An aperture is disposed on the night vision assembly to be attached to the pilot's helmet. The locking element of the pilot's helmet is passed into the aperture of the night vision assembly wherein the locking element is engaged and retained by a collet. The collet is biased against the locking element by a wire that is wrapped around the collet. As such, the collet engages the locking element and prevents the locking element from being withdrawn out of the night vision assembly, thereby firmly joining the night vision assembly to the pilot's helmet.Springs or similar repelling elements are disposed between the night vision assembly and the pilot's helmet.

Abstract: An energy absorbing structural unit is attached outside the fuselage belly of an aircraft having at least two decks arranged one over another. At least the lower deck, of which the floor is adjacent to the fuselage belly, includes passenger cabin compartments and/or service facilities. The energy absorbing structure is an energy absorbing structural unit (5) that is attached outside of the existing aircraft fuselage (2) approximately vertically below the passenger cabin compartment (9) and/or service facilities provided on the lower deck of the aircraft. The energy absorbing structural unit absorbs impact energy arising in a crash or emergency landing of the aircraft. Because impact energy is absorbed by the external structural unit rather than or in addition to the structure of the aircraft fuselage and air frame, it is possible to provide lower deck passenger cabin space that may be continuously occupied by passengers and crew even during the take-off and landing phases of a flight.

Abstract: This invention discloses a method for compensating for the disturbance torque on an orbiting satellite (10) from the interference of the earth's magnetic field lines with particular current loops associated with the satellite (10). The current flow in these current loops on the satellite (10) is measured by a current sensing device (42). A scaling factor (44,46) is applied to the measured currents to derive an estimated disturbance torque in particular axes of the satellite's attitude. The estimated magnetic disturbance torques are applied, along with other control torques, to a satellite actuation device (38). The actuation device (38) actuates the satellite (10) in the particular axes to compensate for the disturbance torques being applied to the satellite (10).

Abstract: A plug-type door is provided for an aircraft of the double-decked type. A compartment is formed between the upper deck of the aircraft and a header. An aperture is provided adjacent an edge of the header for permitting transit of the door therethrough. A set of guide tracks is arranged at the edge of the door jamb and a pulley system is provided for guiding the door between closure and storage within the compartment.

Abstract: A hardover protection system for an aircraft. A differential motion sensor is mounted to a sector for receiving cockpit pitch commands input via a cable system. The motion sensor includes a pair of cranks held together by a predetermined spring preload. One of the cranks is coupled to a rod that forms a portion of a power linkage for hydraulically driving an elevator surface while the other is coupled to a rod that is linked to a shutoff valve. A linkage for mechanically driving an elevator control tab is also mounted to the sector. The design of the shutoff valve and its location within the aircraft's hydraulic control system interact to disable powered operation of the elevator surface upon a predetermined degree of deflection of the shutoff valve piston. Such deflection is responsive to the detection of a predetermined mismatch between the input command motion to the sector and the output motion of the power linkage.

Abstract: An aircraft which rolls along a guide rail at low speeds and attains aerodynamically airborne flight guided along the rail at high speeds. The guide rail structure includes I beams suspended end to end from spaced apart arches. The guide rails are mounted on the lower ends of the I beam and include flat bottom surfaces and curved upper surfaces that receive the wheels of the aircraft in the low speed operating mode. The upper surfaces are portions of elliptical surfaces to assure proper positioning of the aircraft wheels. In the high speed airborne mode of operation, proximity sensors on the aircraft sense the distance to the guide rail. Controls receive inputs from the sensors and adjust the flight path accordingly.

Abstract: A method for the determination of the location of the line-of-action of the resultant of the wind forces on a tethered aircraft is disclosed. The location is referenced to a line-segment that is referenced in turn to the aircraft structure. The line-segment is from the point of attachment of the tether to the center-of-gravity of the aircraft. The location is the distance along the line-segment from the center-of-gravity to the point of intersection of the resultant and the line-segment and the angle between them. The method includes the measurement of the length of the line-segment and the measurement of the aircraft weight. While the aircraft flys in force equilibrium, measurements of the tether-tension, of the inclination of the tether, and of the slope of the line-segment are recorded. The measurements provide locations of a plurality of coordinate points on the line-of-action. The resultant that is located by the points is marked on or within the structure.

Abstract: The invention relates to an underframe for a passenger aircraft seat, the underframe including a triangular base defining a front anchor point and a rear anchor point, and a raised intermediate vertex; and a leg associated via its top end with the structure of the seat and via its bottom end with the triangular base. In accordance with the invention, the leg is associated rigidly with the base by rigid association means which, during normal use of the seat, hold the leg positively relative to the base, in particular so as to prevent any forward or backward pivoting of the leg.

Abstract: A launch vehicle system includes at least one primary solid fuel motor, a shroud for housing a payload and an attitude control system. The attitude control system is connected intermediate the primary solid fuel motor and the shroud. It has a circular outer wall and liquid fuel motors for exerting thrust along a longitudinal axis of the rocket system, and for controlling pitch, roll and yaw of the shroud. The attitude control system includes a support structure defining three pairs of fuel tank supporting zones, each zone having laterally extending supporting brackets connected to the outer wall. The attitude control system also includes connecting tubing for connecting outlets of sets of fuel tanks consisting of one, two and three pairs of fuel tanks to the liquid fuel motors.

Abstract: A video signal display system is provided at a back of each of a number of seats arranged in rows and columns. A recess is formed in the rear portion of the back of each seat and spherical-shaped support units for pivotally supporting a picture display unit of the display system are provided on the bottom of the recess and at a mid portion of the back surface of the picture display unit for assembling the picture display unit in the recess. The spherical-shaped supporting units are rotated for varying the position of the screen of the picture display unit built in the rear portion of the back of the seat to an easy-to-view position.

Abstract: A duplex complementary carrier includes a flight vehicle floating above the ground, a control system moving on the ground for controlling movement of the flight vehicle, and a connecting system connecting between the control system and the flight vehicle. When the control system is moving on the ground, the flight vehicle above the ground is able to follow movement of the control system due to the connection provided by the connecting system such that the pressure of the control system on the ground and the frictional force of the ground on the control system are reduced by the buoyancy of the flight vehicle. The flight vehicle is able to move above the ground stably by the directing and guiding effects of the control system.