Abstract: A translational braking device for a projectile on its trajectory. The device has at least two air brakes made in the form of flaps that are moved in a plane perpendicular to the axis of the projectile to increase the aerodynamic drag of the projectile. Each flap has at least two closed grooves, extending essentially parallel to a direction that is perpendicular to the axis of the projectile, each groove cooperating with a rod that is fixed with respect to the projectile.

Abstract: An ejection seat having a blast protection system comprising an inflatable curtain stowed on the ejection seat and deployable to at least substantially envelop an occupant of the seat.

Abstract: A super-pressured high-altitude airship flies in the stratosphere, is propelled against the wind by the power obtained through the photovoltaic conversion of the sunlight, and is used for a large-scale LTA (light-than-air) platform for environmental observation, telecommunication relay, etc. This airship has a super-pressure structure which has a pressure-resistant gas bag in an envelope capable of enduring the rise of internal pressure by allowing no in-flow or out-flow of gas from or to, respectively, the outside atmosphere at the mission altitude. A solar cell is installed on an upper external surface of the envelope. A ventilation space is provided between an installation surface of the solar cell and the gas bag to block the heat transfer from the solar cell to the buoyant gas in the envelope. A fan is provided to forcibly circulate the outside atmospheric air in this ventilation space.

Abstract: The excess space and weight capacity of a conventional geosynchronous-transfer launch vehicle is used to deploy satellites to a low-earth orbit (LEO). In a preferred embodiment, an orbit-transfer vehicle provides the navigation, propulsion, and control systems required to transport a payload satellite from a geosynchronous-transfer orbit (GTO) to a predetermined low-earth orbit. Upon entering low-earth orbit, the payload satellite is released from the orbit-transfer vehicle. To reduce the fuel requirements for this deployment via the orbit-transfer vehicle, a preferred embodiment includes aerobraking to bring the satellite into a low-earth orbit.

Abstract: A deicer comprises a skin heating means immediately subjacent an outer skin overlying an apex of a leading edge, and a skin deflection means immediately subjacent the outer skin chordwise aft of the apex. The skin heating means prevents the formation of ice over the apex and the skin deflection means deflects the outer skin to expulse ice formed chordwise aft of the apex. A controller controls the heating and deflection cycles to minimize power consumption of the deicer.

Abstract: A mixed compression supersonic inlet system is provided which includes an external cowl, and an axisymmetric centerbody which preferably translates fore and aft. The centerbody of the inlet system is further provided with indexing segments which circumferentially rotate to provide longitudinal grooves or channels located on the outer periphery of the centerbody and which increase the effective flow area of the inlet. As the indexing segments rotate circumferentially, the channel width varies. The centerbody may also be provided with indexing segments formed of a first and second portion having hinged joints which slide forward and aft in a groove. One end of the indexing segment is hinged to the non-translating section of a translating centerbody. The indexing segments are positioned over a longitudinal channel. As the translating centerbody is translated forward, the hinges of the indexing segment slide in their respective grooves to expose the channel.

Abstract: A tether having the special technical feature of multiple primary load-bearing lines and normally slack secondary lines. These primary and secondary lines are connected together with knotless, slipless interconnections so the tether maintains high strength and some of the lines can be cut without failure of the tether when it is operated near the ultimate failure load of the material from which it is constructed. This tether can safely carry load hundreds of times longer than prior art tethers in harsh environments where a single-line tether experiences a substantial risk of failure. The specific industrial applications of an electrodynamic tether system to deorbit satellites and a low Earth orbit to lunar surface tether transport system are all part of the general innovative concept of the invention.

Abstract: An advertising placard (20) having a substrate (30) and coloration material (34) is utilized to provide an unobtrusive and nondistracting advertisement on internal viewing surfaces (22) in commercial aircraft passenger cabins (24). The substrate (30) is preferably thin and transparent, and the coloration material (34) preferably has substantially the same color hue as the viewing surface (22) to which it is applied. Further, the coloration material (34) preferably has a color lightness within approximately &Dgr;7 of the color lightness of the viewing surface (22).

Abstract: A spacecraft propulsion module (16) that includes an outer cylindrical housing (20), an end wall (22) and a specialized internal structure (50) that is capable of supporting various spacecraft components (110, 112, 124), to provide different levels of spacecraft complexity for different missions. The internal structure (50) within the housing (20) includes a plurality of inner walls (52-58) defining an "eggcrate" structure. The plurality of inner walls (52-58) includes a first pair of walls (52, 54), extending in one direction and a second pair of walls (56, 58) extending in a substantially orthogonal direction to define a center compartment (76) surrounded by a plurality of perimeter compartments (60-74). The inner walls (52-58) and the outer housing (20) define support surfaces on which can be mounted different spacecraft components, such as propellant tanks (110), pressurant tanks (168), life support tanks (126), control, guidance, navigation and communication avionics (124), batteries (112), etc.

Abstract: Control moment gyros in an array are rotated to reorient a satellite. A pseudo inverse control is employed that adds a term to a Moore-Penrose pseudo inverse to prevent a singularity.

Abstract: An aircraft overspeed protection system produces proportional and integral commands for input to an autopilot controlling the aircraft. The proportional and integral commands are produced by comparing actual monitored speed of the aircraft with a target speed from a target speed selector. The target speed selector selects as the target speed a trigger speed above a nominal maximum operating airspeed of the aircraft until the trigger speed is reached by the aircraft. When the trigger speed is reached by the aircraft, the overspeed control goes into Overspeed Protect Command active mode and the target speed selector selects a new target speed below the nominal maximum operating speed of the aircraft. The overspeed protection system remains in Overspeed Protect Command active mode until the pilot takes a positive action by selecting a new autopilot mode or by disengaging the autopilot.

Abstract: A modular kite system using flexible attachment means to join a variety of flat wings to a three-dimensional center section or fuselage, which itself can be of various configurations. Hook and loop fasteners are used to position movable cross spar sleeves along the wings which adjust the flexibility of the cross spar(s).

Abstract: An artificial satellite equipped with roll, yaw and pitch rudders (4, 4', 5) to impose on it rotational forces around its three axes due to the resistance of the rarefied air which surrounds the satellite (compensation for the dynamic inertia of rotating objects onboard the satellite can also be ensured). This invention applies to low-orbit satellites.

Abstract: A wave energy receiving platform installed to track in alignment within a look angle of the sun or a wave energy beaming platform, using holographic windows recorded according to time related positions of the platforms as zone plates to concentrate the wave energy in energy converters, and to columnate light for energy beaming, one embodiment utilizing a circular holographic window for "spot" insolation and a dish-shaped reflector for photovoltaic power assimilation and microwave transmission, a second embodiment utilizing a rectilinear-shaped holographic window for "bar"-shaped beaming and an elongated reflector for photovoltaic power assimilation and microwave transmission, a rectilinear Stirling cycle engine directly operating a rectilinear alternator for generating electrical power, the photovoltaic power synchronized therewith for in-house operation and primary propulsion.