Abstract: Apparatus for and a method of rendering selected areas 17, 18 of an aircraft canopy 2 receptive to an adhesive by means of which a detonating cord 7 is attached in loop form to the canopy, to facilitate fracture of the canopy for pilot ejection in an emergency, comprises pretreating those areas 17, 18 by corona discharge. The canopy 2 is mounted in a jig 10 shaped to conform with the canopy and having rebates 11 for accommodating discharge electrodes 12 located at a distance from the canopy 2. A pump 16 is provided to remove ozone formed due to the discharge and trapped between the canopy 2 and the jig 10.

Abstract: An airfoil having improved aerodynamic characteristics has a leading edge and a trailing edge longitudinally spaced therefrom. A continuous lower surface of the air foil forms a lower camber extending from the leading edge to the trailing edge. The upper surface of the air foil has a first fixed upper surface extending rearwardly from the leading edge and terminating in an offset and a second upper surface extends rearwardly therefrom and is movable from a first position defining a first upper camber portion of the airfoil to a second position defining a second upper camber portion thereof.

Abstract: An RPV for use on shipboard, the RPV having a lower support (for example a plurality of legs) comprising a plurality of broad pads at the lower end, a downwardly extending probe (or finger) extending from each pad, the lower end carrying wings within the probe that may be extended from the probe to extend laterally for securing below a grid through which each probe (or finger) may extend.

Abstract: A light aircraft for short distance takeoff and landing includes an airplane having a propeller provided on a rear pedestal thereof for producing vertical propulsion and an airship having a propeller provided on a rear pedestal thereof for producing vertical propulsion and also having a flight attitude sensor provided within an operating compartment thereof. The flight attitude sensor is always directed in the vertical direction, detects forward and rearward inclinations of the airship, and transmits signals corresponding to the inclinations to the two propellers, thereby rotating the two propellers to produce downward or upward propulsion to maintain the aircraft at the normal horizontal attitude at all times.

Abstract: A charge control apparatus for a flightcraft uses an inherent droplet charging mechanism to remove unwanted charge from the distal portion of a reference body mechanically connected to, and external to the craft, and a driven ion attachment mechanism to adjust the potential of the craft to that of the reference.

Abstract: An apparatus for producing lift in a flying vehicle comprising a top deck of a flying vehicle having a cylindrical well formed thereinto, a discoidal member positioned within the cylindrical well, an air intake system formed in the center of the discoidal member for drawing air through the discoidal member for use elsewhere in the flying vehicle, and a labyrinth member formed on the periphery of the discoidal member for restricting the clearance between the discoidal member and the wall of the cylindrical well. The discoidal member is adapted and powered for rotating within the well. The top deck has a generally flat exterior surface. A fluid passageway extends through the interior of the flying vehicle for passing air from the air intake system. The discoidal member has a flat top surface generally parallel to the top deck of the flying vehicle. The top surface of the discoidal member is positioned within the well below the upper surface of the top deck.

Abstract: An inflatable bladder is placed between the wall of an aircraft inlet duct nd the liquid fuel to reduce the potential damage caused by hydrodynamic ram effects from a projectile penetrating the fuel tank. The inflatable bladder is inflated by a regulated gas source prior to combat. The inflatable bladder may be formed as a double layered section of a rubber bladder fuel cell type fuel tank, or an inflatable bladder may be bonded to the inner surface of an integral fuel tank wall.

Abstract: A mid-air aerial recovery system comprising a payload, a parachute, and an aerial engagement apparatus. The parachute is connected to the payload. The parachute has a sufficient size to support the weight of the payload. The parachute has a plurality of suspension lines extending from the payload to a canopy of the parachute. The aerial engagement apparatus is a loop rope fastened to the parachute and extending outwardly beyond the canopy of the parachute. This loop rope forms a reception area. The parachute is a ram-air parachute. The loop rope is fastened at one end to the payload and extends along the suspension lines of the parachute and is attached to a leading edge of the canopy.

Abstract: This method serves for calibrating gyros forming part of the attitude control system of a satellite stabilized in three axes and which have an unknown drift. A two-axis sensor measuring the direction of a radiating reference object in the coordinate system x, y, z fixed with respect to the satellite is used. Two reference attitudes each different with respect to the reference object are commanded to the satellite in the course of two consecutive time intervals spaced from each other. The values measured by the sensor representing the respective actual direction of the reference object are recorded at the start and at the end of the time intervals. The respective time integrals of the gyro output signals are computed during the time intervals, which represent the gyro drift plus the respective instantaneous satellite deviation from the commanded reference attitude. Finally the gyro drift is determined from these time integrals and the values measured by the sensor.

Abstract: A lavatory module for a passenger airplane, enabling a serviceman to carry out a task for replenishing and changing the stock of amenities from outside the lavatory module in a reduced time, facilitating the work for achieving the task, and facilitating passenger' actions to gain access to the amenities. The lavatory module has a lavatory box having a shape conforming to a space in the fuselage of the passenger airplane in which the lavatory module is installed, and is integrally and internally equipped with lavatory equipments, such as a vertically elongate amenity closet having a plurality of amenity storage compartments arranged in a vertical row, a washstand and a toilet bowl. The lavatory box has a front wall facing the passage of the passenger airplane and provided with a service opening closet by a service door hinged so as to be opened from the passage and a passage opening closed by a passage door from the passage.

Abstract: Agile (electronically steerable) beam sensing with associated on-board processing, previously used exclusively for positioning of antennas for beam formation and tracking in communications systems, is now also used for satellite active attitude determination and control. A spinning satellite (100) is nadir oriented and precessed at orbit rate using magnetic torquing determined through use of an on-board stored magnetic field model (520) and attitude and orbit estimates (212). A Kalman filter (211) predicts parameters (202, 203) associated with a received signal (204) impinging on the satellite's wide angle beam antenna (201). The antenna system measures the error between the parameter predictions and observed values and sends appropriate error signals (207) to the Kalman filter for updating its estimation procedures.

Abstract: The helicopter pad for use on trains comprising a flat surface having an area suitable for the receipt of helicopter skids, a plurality of structural members connected to the flat surface and to the frame of a railroad car, and a ladder extending from the flat surface to the frame of the railroad car. The ladder serves to provide access to the flat surface. The flat surface has a strength suitable for supporting the weight of the helicopter. The flat surface is of high friction material. The railroad car is a transfer car for a unit train having an underlying conveyor system. The flat surface is positioned above a lift portion of the conveyor system on the transfer car. An extensible portion of this flat surface increases the area of the flat surface. This extensible portion is selectively actuable. The flat surface is free of protrusions extending thereabove.

Abstract: A convertible airplane to automobile and visa versa, having a fuselage and three wings, including a forward canard wing, a foldable main wing and a secondary lift wing. The foldable wing is capable of folding to a size for safely driving the automobile on a roadway. All wings are used as ground effect airfoils for roadway use.

Abstract: A fixed wing aircraft that can be converted to an automotive vehicle, comprising a generally rectangular planform fuselage having four wheels as in conventional automobile practice, and a telescopic wing which retracts into a housing in the roof of the fuselage. Telescopic horizontal and vertical stabilizers are provided at the rear end of the fuselage, as well as a retractable pusher propeller that is driven by an engine mounted on the front end of the fuselage. Both the propeller and the rear wheels are connected by a transmission box to the engine, so that either can be driven to operate the vehicle as an aircraft or as an automobile. On take-off, the rear wheels are partially retracted so as to place the aircraft at a proper angle of attack at the same time that the elevators are raised by pulling back on the control wheel. The control wheel is also connected to both the front wheels and the ailerons, and when turned 90.degree.

Abstract: A landing flap system in an aircraft wing, includes an upper and a lower track and a drive for a tandem, flap moving carriage, being composed of an inner carriage having a plurality of rollers for running on the upper track and an outer carriage having at least two rollers for running on the lower track; a hinge pin interconnects the carriages and connects them to the landing flap; a second hinge connects the outer carriage to the landing flap; a thrust and tension rod hingedly connects the outer carriage to the drive; and further rollers are arranged at an acute angle to an axis that extends vertically to such axes and to an axis that is parallel to the longer internal axis of the craft, the further rollers balancing the carriages.

Abstract: The improvements of the organization and operation has to do with an adhesive that temporarily bonds the internal surfaces of two flexible envelopes equidistantly spaced from each other over the entire surfaces facing each other, the space between the walls bonded together separates upon pressurization of a foam between the walls dispersed by a hollow perforated hoop tube to disperse the foam under pressure evenly, while acting as an anchor of the flexible double wall to the deployment cylinder interior and gas and plastic catalysts reservoir within the container, on the end of the container are flanges as standards for interconnecting modules, hatches, and space craft; multiple function of deployment container offering perimeter as protective shield.

Abstract: A multipurpose modular spacecraft is adaptable quickly and easily for performing a variety of short- and long-range space missions, such as on-orbit maintenance missions and the like. The multipurpose modular spacecraft comprises a fully integrated short-range space vehicle including one or more relatively small modular propulsion sets which provide propulsion capability for relatively short-range missions and close-in maneuvering requirements. Longer-range propulsion capability is provided by a comparatively larger propulsion module designed for removable nested mounting within an open-sided chamber in the short-range vehicle. Relatively simple and easily operated latch mechanisms retain the propulsion sets and the propulsion module on the short-range space vehicle in preselected positions with relatively simple electrical fittings connected together to provide a control interface with the short-range space vehicle.

Abstract: A modular space station having a central enclosed area is erected in earth orbit from modules transported by a reusable space shuttle or an expendable rocket. The modules have panels which extend outwardly to join the modules together in spaced relation to form a complete enclosure about a common interior volume with the panels and modules forming the walls of the common enclosure. When two modules are so joined a single space station unit is created with a common central area having approximately the same volume as the modules. The single space station units serve as building blocks which may be joined in various configurations to create increasingly larger space station units having a plurality of enclosed central areas. The modules and central areas created thereby serve as usable space for various purposes and capable of being equipped for life support. Passageways allow occupant communication between the modules and the central enclosure.

Abstract: An improved aircraft ejection seat system is described which embodies a forward leaning position for an occupant of the aircraft providing enhanced acceleration tolerance for an occupant during ejection from the cockpit, comprising a platform supporting at a rearward end thereof a seat having a seat back and seat pan sized and configured for accommodating the occupant, a forwardly disposed cowling integral with and faired to the platform for providing windblast protection to the occupant, a solid or cushioned upright wall member disposed centrally of the platform and extending between the seat and cowling and supporting an inclined chest plate for supporting the chest of the occupant in the forward leaning position, a head rest and a shield disposed near the upper end of the plate for shielding the occupant's head upon ejection from the aircraft, and a restraint harness for holding the occupant in the forward leaning position against the plate upon ejection from the aircraft.

Abstract: A high-altitude balloon having prestrained gores made from an asymmetrical gore pattern. The invention includes the balloon, the method of assembling the balloon, and a table specially designed to implement the method. The method can be used to assemble balloons of varying shapes and sizes, within a determinable range of ratios of gore width to gore length. The method involves cutting and sealing edges of a pair of flexible plastic sheets along a straight edge of a table, then inverting the seam so formed until it is aligned with a curved index line on the surface of the table. The curved index line is longer than the seam created along the straight edge so stretching is required during inverting. Successsively cutting, joining and inverting pairs of sheets in this manner produces a balloon with a plurality of symmetrical gores that give the balloon a predetermined shape when inflated.