Abstract: The invention is a cable restraint system for an aircraft having first and second main landing gears equally spaced from the longitudinal axis of the aircraft; the system for securing the aircraft from movement during engine run-up testing when the aircraft is positioned such that the main landing gears are in front of and the longitudinal axis thereof is aligned with a ground attachment fitting mounted to the ground. In detail, the system includes first and second coupling members. First and second cables having first and second ends, have their first ends attachable to the ground attachment fitting and the second ends attached to the first and second coupling members, respectively. A third cable is attached by its ends to the first and second coupling members. Fourth and fifth cables having first and second ends, are attached by their first ends to the first and second coupling members and attachable by their second ends main landing gears.

Abstract: Vehicle arresting beds, for installation at the ends of aircraft runways, are effective to safely decelerate aircraft entering the bed. The arresting bed is assembled of a large number of blocks of cellular concrete having predetermined compressive gradient strength, so that aircraft landing gear is subjected to drag forces effective to slow a variety of types of aircraft, while providing deceleration within a safe range of values. An arresting bed typically includes an entry region of a depth increasing from 9 to 24 inches formed of blocks having a first compressive gradient strength. A second region, which may be tapered into the first region and increase in depth to 30 inches, is formed of blocks having a greater compressive gradient strength. An aircraft thus experiences increasing drag forces while it travels through the bed, to provide an arresting capability suitable for a variety of aircraft.

Abstract: This specification relates to a blockerless thrust reverser for an aircraft having a podded nacelle housing a turbofan engine which produces core flow and a fan exit stream. Reverse thrust is obtained by diverting the fan exit stream into an annular slot formed in an outer wall of the nacelle where it is turned and discharged forward. The fan exit stream is directed into the annular slot by injecting high pressure streams of core flow into the fan exit stream at positions which are upstream of and adjacent to the annular slot. Reverse thrust is selectively obtained by a control means which selectively opens and closes the annular slot and the core jet injectors.

Abstract: An adjustable chock for radio-controlled model airplanes, having two affixed restraining members that can adjustably seat against the front and rear side of model airplanes landing gear, thus preventing its unintentional movement.

Abstract: A system for automatically controlling the braking of an aircraft to a desired setting upon landing or during a rejected takeoff. The inputs to the control system are airplane acceleration and airplane pitch. The output from the control system is an electric current which is sent to a hydraulic servo valve. This valve meters hydraulic pressure to the brakes.

Abstract: For braking a gyroplane rotor, a unit is proposed which comprises a disk brake equipped with a hydraulic actuator (26), which is integrated and has force amplification, as well as a mechanical transmission (54) connecting a control member such as a handle or lever (52) to the said actuator. The amplification effect is obtained by the section difference between a control piston (34) of the actuator directly connected to the mechanical transmission and a free piston (28) of the actuator by which the braking force is exerted.

Abstract: The invention comprises a restratining tie down apparatus for tieing down a movable abject, such as an aircraft, in a straight line connection between the stationary object and the aircraft. The restraining tie down apparatus has a storage compartment or container which is adapted to be fixed upright in the ground with with an opening at the top which is flush with the top surface of the ground. A tie down device is removably mounted within the container. The tie down device has a frame with a pair of side panels and a spool is rotatably mounted between the side panels. An elongated flexible belt is wound on the spool with its inner end attached to the spool and its outer end having a hook attached thereto. A second hook is attached to the frame of the tie down device. A spring is mounted to the frame with one end attached to the frame and its other end attached to the spool to urge the spool to rotate on the frame in a direction to wind the belt onto the spool.

Abstract: A way to make model/experimental planes crash proof by a shock absorbing harness mounted over the body of the plane, which does not significantly affect the flying abilities and qualities of the model/experimental.The harness protects against collision with ground or other objects by strategically placing shock absorbing structures on the body of the aircraft. These structures are protruding from the overall outer dimension of the model/experimental aircraft and are the ones to first hit external objects and the ground. These shock absorbing structures are made of material that is light and provides the resiliency and cushion against the impact to the model/experimental body. The design is such that they add very little weight and drag to the model/experimental aircraft. The structures are made of thin wires and resemble an inverted question mark in its basic configuration.

Abstract: A restraint device for an aircraft having a plurality of covered wheels with tires thereon, comprised of a base plate upon which is mounted a vertical restraint member attached to the side portion of the base plate. Positioned atop the vertical restraint is a landing gear strut attachment fitting which accepts the landing gear strut while adequately clearing the wheel fairing device.

Abstract: A launcher for radio controlled flights of a model airplane, which releases the previously restrained model airplane upon the depression of a foot pedal thereof, thereby eliminating the need for any person to place his or her head in or nearby the exhaust stream of the operating engine at takeoff time, supporting: rotatable, releasible, restraining, spaced, arms, which, when raised, obstruct the forward motion of the model airplane, via the stabilizers thereof; the foot pedal; and a linkage system interconnecting the foot pedal with the rotatable, releasible, restraining, spaced arms.

Abstract: A system for arresting movement of an aircraft traveling off the end of a runway at high speeds. Rigid, friable, fire resistant foam boards, preferably phenolic foam, are connected to form a panel, and a plurality of layers comprised of stacked panels are adhered to a base surface. The panels are formed from unfaced foam boards, the compressive strength of the stack of boards being less than the force exerted by the landing gear of the aircraft to allow the boards to be crushed by the landing gear.

Abstract: A safety device for an emergency landing of an aircraft has a runaway. A unit for retarding the speed of the aircraft is mounted in the runway and includes a plurality of rows of juxtaposed rotary bearing members, each of which is provided with a friction surface, a plurality of rotatable shafts, each of which carries each row of the rotary bearing members, and a hydraulic unit provided in each row of the rotary bearing members. A unit for braking the speed of the aircraft is fixed in the runway downstream of the retarding unit and includes a plurality of rows of juxtaposed stationary bearing members, each of which is provided with a friction surface. A unit for supporting and guiding the aircraft to move on the runway includes a base slidable on the retarding unit and the braking unit and a preventing unit for preventing the aircraft from being released from the base after the aircraft lands on the base. The safety device further includes a fire-retarding fluid provided in the runway.

Abstract: An aircraft speedbrake is integrated into a jet engine exhaust nozzle. A first set of nozzle flaps which are normally out of the airstream, are extended into the airstream to create drag on the airframe and thereby act as speedbrakes. A second set of nozzle flaps are opened when the first set of nozzle flaps are extended into the airstream, to simultaneously spoil the thrust of the engine.

Abstract: An aircraft capture system, e.g. for a radio-controlled pilotless aircraft (19), having at the homing station a boom arrangement (13) mounted for rotation about a vertical hinge axis (A--A) and having appreciable flexibility under forces acting perpendicular to the hinge axis while being substantially inflexible under forces acting parallel to the hinge axis. The flexibility of the boom arrangement cushions the aircraft against shock when an arrester hook (33) deployed from the aircraft engages the boom arrangement via an arrester wire (15) attached to the boom arrangement.

Abstract: An apparatus for controlling the rate of deceleration of a moving body. The apparatus has a cable or net for engaging a moving body and tape connected to the cable or net. The tape is wound onto a reel at the start of a deceleration and is unwindable from the reel during the deceleration so that unwinding the tape from the reel causes a corresponding rotation of the reel. A pump is operatively connected to the reel so that rotation of the reel causes pumping of a hydraulic fluid at a rate which increases as the rate of rotation of the reel increases. A control valve disposed across the discharge of the pump varies pressure drop across the control valve. A brake is provided for applying a braking force to the reel, and an actuator is provided for varying the braking force applied by the braking means in response to the pressure drop.

Abstract: Safety restraining apparatus for a model airplane under power comprising an inverted U-shaped member having a hinged member mounted on the top. The hinged member consists of a pair of spaced arms and legs which limit motion of the hinged member to one direction when the U-shaped member is inserted into the ground. The aircraft with propeller turning is restrained by the hinged member coming into contact with the horizontal stabilizers. The aircraft is released for take off by withdrawing the airplane permitting the hinged member to drop to ground under gravity to be out of the way. One advantage of this invention is that the arms drop out of the way when the airplane is withdrawn. Another advantage of this design is that once the device is mounted in the ground it can be reused any number of times without removing it from the ground. Thus, for a full day of flying, for example, the device is installed, used repeatedly, and then removed when the equipment is to be put away and the area is left.

Abstract: An elemental net for a multiple element aircraft arresting net system. The elemental net has a single upper horizontal strap, several vertical straps having top ends and bottom ends, and at least two lower horizontal straps. The top ends of the vertical straps are directly affixed to the upper horizontal strap at spaced intervals along the upper horizontal strap. The bottom ends of the vertical straps are alternatingly affixed to one of the lower horizontal straps so that the lower horizontal straps are free to move relative to each other to a significant degree and so that lifting of one vertical strap will tend to lift only one of the lower horizontal straps in the vicinity of the vertical strap being lifted. The present invention provides a variable window which is free to expand or contract during aircraft engagement, permitting easier penetration of the net by a greater mix of aircraft.

Abstract: An aeronautical drogue having a canopy and support members connecting the canopy to a connector provides for essentially constant drag at variable speeds by aerodynamic pressure modulation through controllably venting the canopy by constructing the canopy of a plurality of separate elastic bands positioned side by side the elastic bands being connected at spaced intervals by flexible connections.

Abstract: The present invention relates to a point landing method for a flying object, e.g., an aircraft (manned or unmanned), a helicopter, a missile, in a location which may be stationary, e.g., a ground plot or the roof of a building or a moving one, e.g., a car, ship, train.

Abstract: A shipboard mounted apparatus for the retrieval of air vehicles, including remotely piloted, or automonous, unmanned vehicles, which includes a deployable lifting device such as a ram-air parachute which is secured through a tow line to the ship traveling upwind therebelow. A capturing device such as a ribbon parachute which may be annular is also movably secured to the tow line immediately below the ram-air parachute and may include a homing beacon therein such that capture of an air vehicle is achieved by it traveling into and collapsing this ribbon parachute. A winch is secured to the ship therebelow and is attached to the lower end of the tow line to control the inward and outward movement of the extended tow line. Once an air vehicle is captured in the ribbon parachute, the tow line is pulled in by the winch allowing the collapsed ribbon parachute and the captured air vehicle to be drawn into the ship to thereby be received by a landing net preferably of an open mesh nylon webbing.

Abstract: A deceleration sled to decelerate and safely contain a launched test miss. The sled has crushable honeycomb which absorbs the initial impact of the missile as the sled accelerates along a track to the same speed as the missile. As the deceleration sled is pushed down the rails, forming shoes on both sides of the sled engage flat metal plates. The forming shoes roll the flat plates into a "U" shape. The energy required to roll these plates can be changed by varying their thickness.

Abstract: A webbing system is disclosed for use as an aircraft barricade wherein a rality of rectangularly-shaped engaging loops are arranged in an alternating, multi-planar array and suspended across a landing area in the path of an approaching aircraft upon an assembly of support loops stretched between a pair of stanchions and connected on either side to an energy absorbing device. Slidably connected along upper and lower horizontal components of the support loops, the engaging loops are free to move laterally along the support loops toward the longitudinal axis of the aircraft when penetrated by the fuselage so that the aircraft is ensnared about its wings by the loops with equalized loading and its forward motion arrested.

Abstract: The common problems of nose diving and rolling over of airborne craft are sought to be overcome according to this invention by providing a safety device consisting of collapsible cover atop the fuselage, the cover being adapted to be opened or closed by the pilot of the craft.

Abstract: Apparatus and method for recovering and arresting an aircraft or other vele. A boom is swivelly connected to a support structure via braking mechanism. The boom is pivotally connected to the brake mechanism such that it can also pivot in a second, different plane intersecting the plane of rotation of the brake mechanism. A shear pin prevents pivoting of the boom in the second plane until the boom has experienced a predetermined load in that plane. The distal end of the boom distant from the brake mechanism is provided with structure for engaging the aircraft. When the aircraft is flown at and captured by the boom, the weight and motion of the aircraft breaks the shear pin, causing the boom to move in the second plane until engaged by a stop. This rapid change in position of the engaging end of the boom in the second plane prevents the aircraft from pendulating about the boom.

Abstract: Takeoff, flying, normal landing and emergency landing of aircraft (including space/reentry vehicles as well as airplanes) is improved in respect of minimum speed limits and necessary runway lengths by a control system comprising aspiration of ambient air in a direction counter-current to the relative wind direction established by motion of the craft, these effects preferably further supplemented by a cushioning and sheltering effect established by a grooved runway.

Abstract: A woven fabric belt having a coating of polyurethane on each face and extending through the interstices of the fabric. The polyurethane is the reaction product of a polypropylene ether glycol of 4,4'-methylene di(cyclohexylene isocyanate) cured with p,p'-methylene dianiline and having at least one face of said belt covered with the polyurethane having walnut shell powder incorporated therein.

Abstract: This invention provides a safety device for quickly arresting the movement of vehicles such as aeroplanes and motor cars by forming a retarding bed of crushable material adjacent to a vehicle track. A foam is formed from an aminoplast resin composition and layed down in a bed adjacent to the vehicle track where it is cured in situ to produce a non-resilient cured foam body having a compressive strength between 15 and 50 p.s.i. and a density from 0.25 to 10 pounds per cubic foot.