Abstract: The tape for connecting a landing aircraft to a rotary energy absorber, which is arresting it includes at least two longitudinal sections, a leading section and a trailing section. The leading section absorbs the impact shock when the aircraft is first arrested. It, therefore, has longitudinal filaments with a relatively low modulus of elasticity and is, therefore, made of a material, such as nylon, which can absorb considerable impact stress without breaking. The trailing section of the tape is brought into action during the runout of the tape to gradually stop the aircraft. It has longitudinal filaments with a relatively high modulus of elasticity and extremely high tensile strength. Such modulus of elasticity is accordingly above 12.times.10.sup.6 PSI with a tensile strength of at least about 10 grams per denier of 400,000 PSI. A satisfactory trailing section material is, for example, an ultra-high tenacity synthetic fiber, such as Kevlar. Kevlar is the trademark of E. I. DuPont de Nemours & Co.

Abstract: A deck for landing an arrested RPV has a row of substantially parallel elastic stringers deployed between a pair of open bed trailers. The stringers are attached to longitudinal rails on the trailers and to wind-up winches for tensioning the stringers. A pendant or net is attached across one of the trailers between a pair of stanchions and is connected to energy absorbers on the other trailer for arresting the landing RPV and dropping it down on the deck. Protruding elements of the RPV slide down inbetween the stringers to protect them from damage as the larger body and wing portions are caught on the stringers.

Abstract: The hydraulic energy absorbing device of U.S. Pat. Re. 28,736 is adapted to serve as a variable torque hydraulic clutch for a flywheel catapult by mobilizing the fixed array of annular vanes disposed about the rotor blades and mounting them on an output shaft. The torque transmission through the device is controlled by the degree of enclosure of the input rotor blade ring by a channel-shaped shroud, which is mounted in an annular recess in the toroidal flow-control ring disposed in an annular cavity in the casing.

Abstract: The shuttle for launching an RPV is connected to a launching tube by a motion and high speed-multiplying pulley and cable assembly. The telescopic launching tube assembly is connected between and parallel to a pair of elongated arms of a sealed U-shaped tubular assembly connected by a manifold to which the telescopic tube and shuttle are latched back against the force of compressed air stored in the U-shaped receiver. The release of the latch is damped to minimize acceleration forces on the launched RPV. The receiver and launching tubes are mounted on an elongated base whose rear end is rotatably connected to an anchor plate and the front end of the tubular assembly is adjustably mounted upon the front of the base on an adjustable jack support.

Abstract: A fluid-operated energy absorber has an annular axle shaft and bearing assembly connected to the rotor shaft adjacent to a hollow compartment in the base of the rotor shaft. The annular assembly is interconnected by segmented plates. Opposite rotor vanes on each axle are disposed on different sides of the segmented plates. A pair of cam plates in the hollow shaft compartment engage cranks on the inner ends of the axle shafts for varying the angle of the vanes. The cam plates are actuated by a control rod extending out through the hollow center of the rotor shaft, which is pushed or pulled by a lead screw on the outer end of the rotor shaft to vary the angle of the vanes.

Abstract: A rocket-powered vehicle is held latched at the starting end of its guide track while a high steam pressure is built up within the rocket casings through probes inserted into the nozzles which also seal them. When the latch is released, the rockets move off the probes to unblock the nozzles whereby the rockets propel the vehicle down the track to launch the flying device.

Abstract: Various modifications are disclosed of the composite aircraft, which is the subject of U.S. Pat. No. 3,856,236 by this same inventor. The control console is supported from the center of the upper rotating balloon sphere instead of its south pole to reduce the periodic motion of the console about its point of attachment to the sphere. The console is supported from the center of an inner framework through a tapered indentation in the bottom of the sphere. A lift command control system determines the angle of attack of each wing about the periphery of the sphere to provide the force required to generate movement of the sphere in a preselected direction. If the wing experiences a gust, the force reaction compels the wing to seek a different angle of attack to keep the new force in balance with the command force exerted by the control on the wing to automatically provide gust control. A pneumatic lift command control system is illustrated.

Abstract: A pneumatic launching apparatus for a lightweight aircraft has a battery of three pneumatic tubes mounted upon a hydraulic piston and cylinder assembly. A launching tube is mounted on the central pneumatic tube, which blows it away from it in a manner similar to that in which a tubular paper cover is blown off a drinking straw. The outer tubes provide additional storage for compressed air and support the outer ends of a launching carriage, which slides over them. The aircraft is mounted on the carriage by a pair of brackets which react against the aircraft in a forward-moving direction. Restraining shock absorbers are mounted across the front ends of the outer tubular rails in the path of movement of the carriage for arresting it. The pressure is exhausted from the system just before the carriage strikes the shock absorbers either by uncovering perforations in the central tubular rail or actuating a dump valve in the pneumatic system.