Abstract: A guard shield is provided as a protective security device in the cockpit of an aircraft to prevent instruments in the aircraft control panel from being removed by thieves. The guard shield is formed of a flat, laterally expansive, rigid plate with a pair of parallel slots defined in its lower edge. The slots extend upwardly into the interior of the plate and terminate in blind ends. The slots are laterally spaced from each other a distance equal to the distance of the separation of the steering columns for the steering yokes utilized by the pilot and copilot. The guard shield is mounted so as to rest upon the steering columns with the steering columns residing at the upper extremities of the slots in the blind ends thereof. A locking mechanism is employed to hold the guard shield closely adjacent to the surface of the instrument control panel, so as to prevent the removal of instruments therefrom.

Abstract: An active noise control subassembly for an aircraft engine. An aircraft engine noise radiating panel is bendably vibratable to generate a canceling noise generally opposite in phase to at least a portion of the discrete tonal noise produced by the engine. A piezoceramic actuator plate is vibratable by an applied electric AC signal. The plate is connected to the panel such that vibrations in the plate cause bending vibrations in the panel and such that the plate is compressively prestressed along the panel when the panel is free of bending vibrations. The compressive prestressing increases the amplitude of the canceling noise before the critical tensile stress level of the plate is reached. Preferably, a positive electric DC bias is also applied to the plate in its poling direction to increase the amplitude of the canceling noise before the sum of the AC signal and DC bias exceeds the depolarization voltage in a direction opposite to the poling direction.

Abstract: Apparatus and a method are provided for converting a three pilot aircraft cockpit to a two pilot aircraft cockpit including relocating, without change, some control instruments from their existing positions to new instrument panels within reach of the remaining two crew members, the captain or pilot and first officer or copilot, modifying other control instruments for pilot workload reduction, and including the addition of a monitoring means to the cockpit for providing visual caution indicators responsive to caution indicators among the repositioned control instruments that are not within direct sight of the remaining two crew members.

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: The working apparatus comprises a manipulator 1 having three axes, a working unit 10, 20, and a universal coupling 7 for connecting the manipulator 1 and the working unit 10, 20. The working unit 10, 20 has a working portion 12, 22 for rotatably and surface contacting an objective working surface 19, 79. The universal coupling 7 is rotatable about any two axes. The manipulator 401 may be secured to a hatch opening portion 410 of an aircraft by means of a holding jig 406.

Abstract: There is described a vehicle door assembly with shear layer control for controlling the airflow in and around an aperture in the vehicle fuselage. The vehicle door assembly consists of an upper door and a lower door, both slidably mounted to the exterior surface of the vehicle fuselage. In addition, an inner door is slidably mounted beneath the upper door. Beneath the inner door is an aperture assembly having an aperture opening positionable to be substantially flush with the exterior surface of the vehicle fuselage. Also provided are means for positioning the aperture assembly in an upward and downward direction in relation to the vehicle fuselage.

Abstract: An unmanned, remotely controlled microwave-powered aircraft for use as a stationary communications platform. The aircraft is generally a flying wing with a large, flat inner wing having a rectenna on the underside. Rectennas may also be provided on the underside of the wings, the combined output from the rectenna being used to provide power to two electric motors housed within torpedo-shaped nacelles which drive two rear propellers. The rectenna converts a microwave signal at 35 GHz generated by a ground power station utilizing dual gyrotrons and a 34-meter diameter antenna dish. The aircraft has a preferred airfoil cross section throughout and is constructed of lightweight but strong materials in order to provide an enhanced flying time of several months. A power management and distribution system manages the DC power produced by the rectenna to supply power to the flight controls, propulsion system and payload.

Abstract: A device for supporting and guiding a collimator, particularly for a collimator designed to be installed on the ceiling of an aircraft. A collimator follows a complex predefined trajectory in a three-dimensional space (X, Y, Z ) with up to six degrees of freedom, between a given operational position and a stored position. The device includes a first structure (3) attached to the aircraft having three guiding grooves, a first central groove (30) following a plane trajectory in a first plane (X, Y), and two lateral grooves (31, 32) on opposite sides of the central groove which follow second and third trajectories located in two planes perpendicular to the first plane. A second structure (4) rigidly attached to the collimator (1) moves along grooves by means of rollers (8a, 8b, 9a, 9b, 10), the number and shape of which enable the second structure to have six degrees of freedom along the complex trajectory.

Abstract: Devices and means to conduct indoor model aircraft flight, in an indoor/enclosed space using radio controlled model aircrafts. The aircraft is controlled by available multi channel radio control transmitter/receiver set and available micro size servo motors for control of aircraft surfaces and electric motor. The indoor/enclosed space is lighted, provide with upward air flow, marked by laser light beams and separated from public by transparent barrier to provide a controlled space for engaging in flight of model aircrafts.

Abstract: An aerodynamic vane is mounted on the fuselage of an aircraft for purposes such as sensing the angle of attack of an aircraft. The vane is attached to a fuselage mounting hub by means of a deformable hinge member and a weakened linear portion of the vane which is designed to give way under the force of impact of an object striking the vane. Should an object such as a bird strike the vane, the vane will separate from the hub along the weakened linear portion without the main body of the vane shattering. The hinge member, while it will deform under the impact, retains the vane to the fuselage so that it cannot fly into the engine or otherwise cause damage to the aircraft.

Abstract: A sensor has a sensing region that responds to a surface property by producing an output signal. The sensor has a spatially distributed shape or sensitivity so that the output decreases away from a central part of the sensor, and thus the outputs of plural sensors combined have finite spatial transform as well as high roll off in spatial frequency. Preferably the output decreases to zero at edges of the sensor, and conditions of continuity or vanishing may be imposed on first or higher order derivatives. An edge sensor suitable for mounting at the edge of the structure has its weight function obtained by processes of reflecting and inverting the weight function at an edge. A sensor system employs plural such sensors and edge sensors to produce bounded spatial transfer functions for characterizing the structure. Embodiments of piezeoelectric, resistive, capacitive and thermal sensors are described.

Abstract: An avionic tray has a base plate for supporting a line replaceable unit (LRU) and a plenum beneath and substantially coextensive in length with the base plate to provide for discharge of coolant air from the plenum into the LRU. The base plate has an opening leading to the plenum and the cylindrical casing of a motor driven fan is coupled to the base over the hole for air from the fan to be discharged into the plenum. The outlet end of a ram tube is coupled coaxially with the fan casing to increase the volume that would be delivered without the ram tube. The inlet end of the ram tube is preferably cut at an angle relative to a plane to which the axis of the tube is perpendicular so the inlet is elliptical rather than circular. The fan is mounted to a special transition adapter in some cases. The adapter is configured to provide a clearance space for cables that run out of the rear side of a connector block on whose front side connector prongs on the LRU are inserted.

Abstract: An improved flight control system with an enhanced unified graphic mistrim indicator where the flight control computer provides signals to a single mistrim indicator wherein the signals represent the status of the control surfaces of the aircraft and the mistrim indicator displays a single movable reference marker, which is caused to be translated vertically in the event of pitch mistrim, is caused to be rotated right or left in the case of roll mistrim conditions, is caused to be translated right or left in the case of yaw mistrim conditions or is caused to be moved in a combination of ways either translating vertically, horizontally or rotating in order to represent a combination of pitch, roll or yaw mistrim.

Abstract: A device and method is disclosed whereby a protective cover is positioned on the upper surface of an aircraft wing. The cover comprises a lightweight, ultraviolet stabilized material which is resistant to propagation of tears and does not absorb water. Cover material, overhanging the leading or trailing edges of the wing, is locally cutout in the area of protuberances to assist in providing a form fit when a plurality of cinch straps, attached to the leading and trailing edges, are tightened under the wing. Additional straps may be employed to secure the cover to the fuselage. The cover, when tightened, prevents significant ingress of air, protecting the upper surface.

Abstract: The oscillations found to occur in the cavities of an structural frame moving through a fluid are substantially eliminated by the adoption of perturbation elements located at the leading edge of the cavity and reflecting any remaining oscillations out of the cavity at the trailing edge. The perturbation elements may take the form of multiple pins of various shape and geometrical arrangement which prevents the generation and growth of vortices causing acoustic oscillations. The reflection of remaining oscillations out of the cavity may be accomplished by ramping the trailing edge of the cavity.

Abstract: Bird droppings on the propellers and tail sections of parked aircraft are substantially prevented by mounting the present apparatus on the horizontal surfaces thereof which normally present suitable bird perches, the present apparatus having one or more upwardly extending peaked portions which provide no approximately horizontal perchable surface to birds, thereby substantially eliminating accumulation of bird droppings on the supporting structural components of the aircraft.

Abstract: An avionics display device having a stowable rotatable locking handle disposed therein for facilitating quick and easy installation and/or removal of the display device.

Abstract: A method of converting diatomic oxygen to a free-radical version such that the combination of the two can produce ozone. It is widely held that the ozone layer is becoming depleted as ever increasing levels of chloroflourocarbons become present at that altitude. It is believed that even though such ozone-destroying chemicals will be banned by the year two-thousand their effects will be felt long after. A method for combating the depletion of ozone would not only be of tremendous value to the environment but it would also herald the advent of technology serving to function on a world-wide scale. The method for producing free-radical oxygen would simply involve using coherent ultra-violet light produced by a laser mounted on a satellite; the satellite being in geo-synchronous orbit about the location where ozone depletion is evident(i.e. Antarctica). When the ultra-violet light hits available atmospheric oxygen it should act to break the oxygen-oxygen bond to produce ozone.

Abstract: A pivoting wire deflection and severance (PWDS) system that provides protection against wire/cable strikes for aircraft, especially helicopters, having external, belly-mounted gun systems that are pivotable in the elevational plane. The PWDS system is operative to protect against wire/cable strikes with the gun system in a forward stowed flight position and with the gun system pivoted to any position within the predetermined elevation angle of the gun system. The PWDS system includes a hard mounted wire cutter and a pivotable deflector member. The wire cutter includes upper and lower cutting jaws disposed in a housing and operative to sever wires/cables. The wire cutter housing is mounted in combination with the gun system so that the wire cutter provides protection against wire/cable strikes with the gun system in the forward stowed flight position. The deflector member is an elongated structure having first and second ends.

Abstract: A device and method is disclosed whereby a protective cover is positioned on the upper surface of an aircraft wing. The cover comprises a lightweight, ultraviolet stabilized material which is resistant to propagation of tears and does not absorb water. Cover material, overhanging the leading or trailing edges of the wing, is locally out-out in the area of protuberances to assist in providing a form-fit when a plurality of cinch straps, attached to the leading and trailing edges, are tightened under the wing. Additional straps may be employed to secure the cover to the fuselage. The cover, when tightened, prevents significant ingress of air, protecting the upper surface.

Abstract: The invention provides an array of standard infrared aiming lights mounted n an aircraft and used occasionally by pilots wearing infrared goggles to enhance perception of terrain features on low flying missions.

Abstract: In a process and an apparatus for the avoidance of bird impacts on airplanes by means of at least one light-flashes generating light source on an airplane, for which the frequency of the generated light flashes is varied through at least one cycle, the flash frequency is varied dependent upon the speed and/or the altitude and/or the acceleration of the airplane in order to provide an optimal flash frequency range for all take-off and landing phases and at the same time to be independent of a load and the type of airplane.

Abstract: A method of supplying power to a device such as a lunar rover located on a planetary surface is provided according to the present invention. At least one, and preferably three, laser satellites are set in orbit around the planet. Each satellite contains a nuclear reactor for generating electrical power. This electrical power is converted into a laser beam which is passed through an amplifying array and directed toward the device such as a lunar rover. The received laser beam is then converted into electrical power for use by the device.

Abstract: Devices and means to suspend scaled flying crafts during test and training flights, in a controlled environment space with a cable/string from a high point in the space, consisting of an electrical slack sensor on the cable/string and a radio controlled electrical system to automatically adjust the slack in the cable/string with the help of an electrically driven winch, permitting the flying craft to fly safely and freely under its own power.

Abstract: A streamlined housing for supporting a multi-dimensional electromagnetic transducer array is attached to an aircraft fuselage via a pivot support. The streamlined housing is supported by the pivot support in a torsionally unrestrained manner allowing a plane containing the longitudinal axis and pivot axis of the housing to remain substantially parallel to the plane of an incident airstream. Static aeroelastic stability is provided by mounting to the aft portion of the streamlined housing one or more rigidly attached stabilizer fins. Dynamic aeroelastic stability is provided by incorporating within the streamlined housing an adjustable ballast weight.

Abstract: Highly-conducting plasma plumes are ejected across the interplanetary magnetic field from a situs that is moving relative to the solar wind, such as a spacecraft or an astral body, such as the moon, having no magnetosphere that excludes the solar wind. Discrete plasma plumes are generated by plasma guns at the situs extending in opposite directions to one another and at an angle, preferably orthogonal, to the magnetic field direction of the solar wind plasma. The opposed plumes are separately electrically connected to their source by a low impedance connection. The relative movement between the plasma plumes and the solar wind plasma creates a voltage drop across the plumes which is tapped by placing the desired electrical load between the electrical connections of the plumes to their sources. A portion of the energy produced may be used in generating the plasma plumes for sustained operation.

Abstract: A vehicle propulsion system for accelerating a vehicle along a desired travel path in the atmosphere, space, or aerospace includes a trail laying device for laying a trail of fuel along at least part of the desired travel path at high altitude. The vehicle itself has one or more inlets arranged to ingest fuel from the trail into a combustion chamber where the fuel is ignited and burnt to provide thrust before being expelled via an exhaust. The trail of fuel is laid in a similar manner to a condensation trail of a jet aircraft, but with suitable propellant additives for providing the desired fuel mixture to the trailing vehicle. The vehicle includes an auxiliary propulsion system for propelling the vehicle when outside the fuel trail.

Abstract: An aircraft having magnetic suspension systems adapted to be used as a winged surface effect aircraft, as a conventional type aircraft and as an aircraft of vertical take-off. A winged surface effect aircraft is provided with a magnetic suspension system having electromagnets adapted for magnetic interaction with a composite run-way utilizing an eddy current to support the rear portion of winged surface effect aircraft laterally in relation to the run-way while the front portion is supported by and rides on an air cushion developed by forward thrust between the wing and ground. The propelling units of the surface effect aircraft are adapted to hover the front portion and to propel the aircraft along the run-way while the rear portion of aircraft is magnetically supported by the magnetic suspension system. The winged surface effect aircraft can be adapted to be propelled over the ground surface as a conventional type aircraft when the electromagnets are disengaged.

Abstract: An apparatus for attaching to a steering column, column or instrument panel, e.g., an aircraft yoke column, having a two-part clamp to so attach, an arm movably connected to the clamp, and an information display movably connected to the arm. In a presently preferred embodiment, any circular column of 3/4" to 7/8" diameter can be attached to. The movement of both the arm and information display is upwardly or downwardly such that the overall effect is that the display can be moved inwardly or outwardly. The connections of the arm to the clamp and/or of the arm to the information display can be a joint or a hinge. The information display can be a video display, e.g., a moving map computer or a display screen for such a computer, or, a clipboard or ring binder; the video display and clipboard are presently preferred.

Abstract: An improved mounting and carrying assembly for avionics displays including a swing handle with edge mounted sliding spring latches thereon for cooperating with holding pins disposed on a side of the display bezel that is not the front or viewing side.

Abstract: An avionic tray for supporting an avionic equipment box including a flat bottom section having an opening for communicating with an air plenum chamber and a pair of side rails, of unitary construction with the bottom section, extending upwardly at right angles to and at the lateral edges of the bottom section. A pair of vertically spaced and inwardly projecting back plate support tabs are formed in each side rail, the tabs defining flat surface lying in a plane perpendicular to the bottom section and the side rails. A back plate, having an opening for receiving a connector, is rivited to the support tabs and the bottom section to position the back plate and its associated connector precisely at right angles to the side rails and the bottom section.

Abstract: A stabilization system for a towed aerodynamic body 1. The body is provided with two, contra-rotating tubular shrouds 3, 4 each fitted with a set of vanes 5, 6. When the towed body is disturbed by the towing aircraft's wake, the gyroscopic inertia caused by rotation of the shrouds exerts a damping effect on the subsequent oscillatory motion of the towed body. In one embodiment, the shrouds are coupled by wheels which constrain the shrouds to rotate in opposite senses. Hence gyroscopic precession effects due to each rotating shroud cancel.

Abstract: A climatic heat aircraft protective (CHAP) screen that has been designed to protect various types of aircraft, and especially helicopters, from the adverse effects of direct exposure to sunlight while being relatively insensitive to wind conditions. The CHAP screen is specifically designed for various aircraft types to facilitate easy and rapid deployment and removal of the CHAP screen utilizing only the flight crew of the aircraft. The CHAP screen includes a porous screen canopy having overhanging portions and flap portions that are operative to reflect direct sunlight while allowing air to pass therethrough. The CHAP screen also includes a containment bag affixed to the underside of the porous screen canopy that is used to compactly stow the porous screen canopy prior to deployment and to secure the CHAP screen to the rotor head assembly of a helicopter during deployment.

Abstract: Aircraft ventilating visor systems have small tubes insertable in openings into fresh air wing conduits at the interfaces of wings and cabins near the upper portions of windshields in high wing aircraft. Existing pull-open, push-closed turnable air directors are removed and replaced with hollow tubes which supply air to hollow visors. Thin louver-controlled openings along lower edges of the visors control and direct air supplied to front seat occupants.Larger central openings in the rear faces, when the visors are in the down position, are controlled by directional louvers to supply air axially through the aircraft between the front seats to passengers in rear seats. An outside air temperature gauge in mounted axially in one of the connecting tubes. The hollow visors are made of clear see-through, tough, plastic material, and have guides into which removable amber glare-reducing plates are fitted.

Abstract: A flight vehicle includes a fuselage 10 having a consumable fuel supply 18,12, main wings 12 each with an elevon 14 and a pair of jettisonable foreplanes 16. The foreplanes provide lift at take-off and during transonic flight and, at higher supersonic speeds they are jettisoned.

Abstract: A preassembled air data sensor probe and air data transducer assembly has permanently connected flexible tubing coupling the air data transducer fittings and the sensor fittings. The flexible tubing permits the air data sensor and air data transducer to be installed into an air vehicle after having been preassembled and pretested for leaks at the factory. The permanently attached assembly avoids the need for calibration or pressure checks after installation on the aircraft. The preassembled flexible tubing permits manipulation of the transducer to mount it into the proper location even in tight quarters. The flexible tubing can have a section that acts as a drain trap for accumulating ingested water.

Abstract: An avionic tray for supporting an avionic equipment box including a flat bottom section having an opening for communicating with an air plenum chamber and a pair of side rails, of unitary construction with the bottom section, extending upwardly at right angles to and at the lateral edges of the bottom section. A pair of vertically spaced and inwardly projecting back plate support tabs are formed in each side rail, the tabs defining flat surface lying in a plane perpendicular to the bottom section and the side rails. A back plate, having an opening for receiving a connector, is rivited to the support tabs and the bottom section to position the back plate and its associated connector precisely at right angles to the side rails and the bottom section.

Abstract: A flame and heat-resistant cover for airplane pitot tubes comprises a woven tube of fire-resistant fibers. The front of the tube is gathered and it is sown with a fire-resistant, non-abrasive thread.

Abstract: A metal container stores a VTOL aircraft during shipment to a sea vessel or large vehicle where it then functions as a portable weather-tight hangar which can be secured in available deck space. When on board a ship's deck, the walls of the container unfold so that the structure may be converted to a take-off and landing pad that provides an exhaust system for the hot lift engine gases that eliminates the hazard to ship's crew, prevents heat damage to the deck and eliminates "suck down" effects characteristic of certain VTOL aircraft configurations. Triangular panels are removably secured together to form the cover of the container; and when unfolded and flattened, these panels are inserted in the corners of the unfolded structure so as to extend the heat shield.

Abstract: An improved aerodynamic vane is used for sensing the angle of attack of an aircraft during yawed flight. Left and right sensors are rotatably mounted to opposite sides of the fuselage of the aircraft and rotate in the air flow to a position indicative of the angle of attack of the aircraft. Each sensor consists of an arm rotatably attached at one end to the aircraft with a vane at the other end of the arm, which vane is canted at an angle with respect to the axis of rotation of the arm. The vanes on the sensors on the opposite sides of the aircraft are both canted down or up as to cause the sensors to take similar angular positions during yawed flight.

Abstract: This invention relates to a shroud or flexible wall cover which is adapted to be placed onto the nacelle of an aircraft engine. The shroud is positioned to cover the nacelle discharge port through which hot, high velocity exhaust gases normally are discharged. The formation of a provisional closure across the exhaust gas discharge port precludes the entry of fumes and/or mist from inadvertently spilled fuel entering the discharge port and igniting when coming into contact with hot engine parts. The shroud is provisionally placed into operating position immediately prior to a transfer of fuel from a fueling vehicle into the wind tanks of the aircraft.

Abstract: A system for pressurizing an electronic enclosure, such as for example a waveguide located in an unheated, unpressurized region of an aircraft, uses air from a pressurized, heated region of the aircraft and a chiller comprised of a lightweight, thermally conducting body thermally coupled to the atmosphere outside the aircraft.

Abstract: Aircraft engine deactivation apparatus for stopping an aircraft engine while the aircraft is on the ground. The apparatus is for safety purposes and is used to prevent a detected object from coming into contact with an engine driven propeller or a jet propulsion intake. A detector, preferably an infra-red radiation sensor, detects an object or person within a selected distance and within a seleced area about the engine. Upon detection, a mechanical engine deactivator, such as brake calipers engageable with the engine flywheel, or an electronic deactivator, such as an electronic switch operable to ground magnetos, shuts down the engine. A by-pass switch renders the system inoperable, when desired.

Abstract: In an aero-optical interface for an aircraft optical aperture, the separation of the upstream boundary layer from the edge of the aperture creates a region of turbulance which persists downstream over the full area of the aperture. This invention promotes an early develpment of a steady velocity profile at the upstream aperture edge which is approximately the same as a stable, self-similar shear flow velocity profile over the entire aperture. This is accomplished by thickening the boundary layer upstream of the aperture, and blowing a curtain of air across the aperture from its upstream edge at the point of separation of the boundary flow. This produces a shear flow region foot that causes the overall velocity profile to be equal to a stable self-similar free shear layer.

Abstract: An aircraft flight dynamics indicator utilize an artificial horizon and a plurality of indicators to establish climb and descent indexes wherein safe flight may be maintained during ascent and descent by cuing aircraft attitude to a visibly perceptive change in aircraft motion related to the pitch at a given air speed.

Abstract: A sun visor system for use in the controlled manipulation of a sun visor on a transportation device to shield or filter light from an occupant of the vehicle. The visor system includes a rail structure having a pair of rail segments with operatively confronting segment ends defining a space therebetween. A gate structure is operatively associated with the rail segments, is configurable in the space between the rail segments in a closed condition, and is actuable to an open condition permitting removal of the sun visor by moving the same past one of the segment ends.

Abstract: A Pitot static tube cover made out of a rigid material skeleton covered with a ceramic braid. A cross-bar with holes is provided so that the Pitot static tube cover may be mounted or dismounted by a pole from the ground.

Abstract: A system for controlling fluid turbulence inside and just outside of a cay adjacent to an opening in a wall, the wall having a forward lip which defines the leading edge of the opening and an aft lip having a leading edge which defines the trailing edge of the opening, the forward lip terminating in a sharp edge lying generally in the plane of the outer surface of the wall. The aft lip has a length of 10 to 50% of the length of the opening and extends into the opening at an angle of 30 to 60 degrees to terminate in an arcuate portion having a radius of 2 to 6% of the length of the opening.

Abstract: A buffering portion of boundary layer flow along a flight vehicle surface diverted into an internal cavity at a downstream edge of a surface mounted window isolating recirculating flow of the diverted fluid through the cavity while it is cooled therewithin. Outflow of the cooled buffering fluid from at an upstream edge of the window is conducted into the buffering portion of the boundary layer flow to cool the window and prevent damage thereof by aerodynamically generated heating of the surface under high velocity flight conditions.

Abstract: This invention relates to aircraft and specifically to devices for disconnecting the winds in a rapid manner. The frame of the wings is atached to the frame of the fuselage with exploding bolts. The skin of the wings is secured to the skin of the fuselage with rivets that also explode or a burnable tape is placed under the skin to sever the skin. A control arrangement is provided that simultaneously ignites the exploding bolts and the rivets or the tape to disconnect the wings from the fuselage.