Abstract: A flexible rotary coupling is provided to transfer rotary power across the wingfold access of a folding wing aircraft. The flexible rotary coupling has a step-up gear box on the inboard wing section to increase the rotational velocity of the flexible coupling. The outboard wing section has a step-down gear box to decrease the rotational velocity of the flexible coupling to that of the step-up gear box input. In this way, substantial rotational power can be transferred across the wingfold axis through the flexible coupling axis with a thin, highly flexible shaft. A guide mechanism is provided to store excess shaft length when the wing is in the unfolded (i.e., straight) position.

Abstract: The control surface drive has three shafts. The shafts are rotatably coupled by four universal joints. Mechanisms are provided to guide the shafts as outboard wing sections are moved between folded and unfolded positions. Rotary coupling between the inboard and outboard control surface drives is maintained during folding motion of the outboard wing sections.

Abstract: The invention relates to an aircraft structure to make possible take-off and landing on a pilot's feet. The aircraft structure according to the invention can be regarded as a category between kite-shaped aircraft structures and light structures. The gist of the aircraft structure of the invention consists in providing freely supported or outerly reinforced wings (12) adapted to be moved by a pilot (15) actuated mechanism, in their own plane during flight.

Abstract: A method for sealing a gap between an aircraft fuselage and a wing turntable mounted thereon while in the inflight position. A seal element having wing attached and fuselage attached sections is positioned in the gap and each section is configured to have forward and rearward portions in the direction of rotation of the wing from the inflight to a storage position the forward motion of the fuselage attached section being at least 1% less thick in a direction generally parallel to an axis of rotation of the wing than the rearward portion of the fuselage attached section.

Abstract: An over-center locking mechanism is provided for a guided missile foldable wing structure which ensures stable reliable and non-reversible locking of the foldable wing. A pyrotechnic actuator is connected to the mechanism and, upon firing, quickly operates the mechanism to a deployed condition.

Abstract: A fin (1) suitable for stabilizing the flight of a projectile for example, is formed with an integral cantilever spring member (4). The fin (1) is rotatable about a pivot (3) from an initial stowed position (not shown) to a deployed position. The spring (4) is initially retained against the fin (1) but when it is released, the fin is forced outwards to its deployed position by the action of the spring (4), the free end of the spring moving into engagement with a surface (7) to retain the fin in the deployed position.

Abstract: A mechanism for rotating a missile control surface 6 about an axis 26 from the illustrated stowed position within the missile to a deployed position in which it extends radially from the missile axis M--M and for then turning the surface about radial axis 13 so as to steer the missile. A single drive motor 22 is coupled by worm 20 to a bevel gear 18 mounted in a bracket 12, the bracket being turnable about axis 13 with respect to a fixed support 10. The control surface 6 is fixed via arm 23 to a bevel gear 24, which gear is mounted to the bracket 12 for rotation about axis 26 and is engaged with gear 18. While the surface 6 is stowed, a sprung locking pin 14 carried by the bracket 12 is held in engagement with support 10 by gear 18 so that rotation of the motor 22 rotates gear 18 with respect to bracket 12 and hence rotates gear 24 along with arm 23 and control surface 6 about axis 26.

Abstract: An aircraft has a geometrically transformable pilot compartment, and further parts including a fuselage boom, wings and tail, wherein at least one of these parts are movable between an unfolded position in which it is ready for flying and a folded position in which it is accommodated in the pilot compartment.

Abstract: A manned space entry vehicle having pivotally mounted wings which remain stored during space travel and become deployed to a forward-swept configuration after entry in the atmosphere. A radar antenna is mounted in the forward portion of the wing so that it is protected from excessive heat when the wing remains in a stored position during early reentry into the atmosphere. When the wings are deployed, the radar antenna maintains an operative position. The mean aerodynamic center of the deployed wings is transversely aligned with the center of gravity of the vehicle so as to increase the stability of the vehicle. The basic vehicle shape is intended to produce the least reflective radar cross section as it passes over threatening areas in a nose down attitude.

Abstract: A foldable missile wing is deployed by means of an overcenter linkage powered by a torsion spring assembly capable of exerting a generally linear bias on the linkage over its full range of motion. A separate lock linkage maintains the foldable wing in a deployed position until release actuation of the lock linkage occurs thereby enabling wing deployment.

Abstract: A mechanism and method for folding the wing of a tilt-rotor aircraft, hav a rotatable load bearing member cooperatively disposed between a high point of the fuselage and the tilt-rotor wing, and a plurality of locking, load bearing pin joints disposed between the fuselage and the tilt-rotor wing, concentric to the rotatable load bearing member, and wherein the tilt-rotor wing may be stored by rotating the tilt-rotor wing, as a single segment, about the rotatable load bearing member, to a position substantially parallel to the fuselage, and wherein the wing may be locked in the flight configuration and the storage configuration with the same pin joints.

Abstract: A remotely piloted vehicle is provided with single surface membranous airls controllable in flight. The airfoils are selectively deployed from a stowed position on either side within the fuselage by spars attached to the leading edges. Pivotal members attached to the root edges of the airfoils are positioned to regulate twist distribution, angle of attack, root camber ratio and root camber distribution.

Abstract: A self-erecting wing structure for increased missile performance and maneuverability without significant sacrifice of payload space includes a wing pivotally attached to an air frame in a retracted position in which the wing is both rotated about its spanwise axis relative to an erected position and pivoted forward alongside the air frame. Rotational components enable passing air to swing the wing to the erected position when it is released from the retracted position during flight. A secondary wing surface is included that automatically deploys to increase wing area.

Abstract: A projectile possessing extendable wings or fins which are adapted to be pivoted radially outwardly of the projectile. The wing or fin includes a flexible covering and a tensioning device; for example, a strut arrangement, and with the wing or fin being displaceable from a retracted position prior to launch of the projectile to an outwardly extended position in which the applicable covering portion is tensioned by the tensioning device so as to thereby provide a stable, predetermined aerodynamically defined wing or fin configuration.

Abstract: The deployment of folded down wings in an aircraft following, for example, rocket assisted launching from the container is carried out through gas pressure springs with strong attenuation in the final phase, the springs being releasably coupled to the wings for being jettisoned upon completion of deployment.

Abstract: The invention concerns a missile body having a first flight guide and stabilization means mounted on the missile body and a second guide and stabilization means mounted on the missile body in front of the first guide and stabilization means with respect to the direction of flight. The second guide and stabilization means comprise a plurality of wings which are folded inwardly (collapsed inwardly, pivoted inwardly) into the missile body when in their inoperative position. These wings can be pivoted or slid outwardly when in their operative position by means of a collapsed expandable body which is expanded by means of pressurized gas. The pressurized gas is stored in a pressurized gas cylinder mounted within the missile body. The expandable body expands in a radial direction and thereby exerts a force on the wings which causes them to either pivot about a rotatable axis or to move in a radial direction outwardly of the missile body.

Abstract: A foldable wing or airfoil, which is especially but not exclusively adapted for a projectile, and which incorporates interengaging telescopable fin sections. A nose in the foldable wing, which is hingable in the region of one end through a pivot in a longitudinal groove, has a chamber opening facing away from its leading edge and which is located between the wing part surfaces for receiving the interlocking fin sections, which sections are profiled in U-shaped configuration. The chamber also receives a base or root spar which is hinged in the region of its leading end in the chamber, and wherein the front ends of the fin sections straddle the root spar and are each hinged along the root spar offset relative to each other.

Abstract: An improved auto-plane has been invented which has been adapted for air travel and road travel using a Pusher type design. The present invention auto-plane has two main wings which are cut approximately parallel to an imaginary fuselage centerline at about two-thirds the distance in from the wing's outer tip to the imaginary centerline, one of the two main wings being hinged along its cut and above its top surface at a height sufficient to allow both of the two wings to be folded inward 180.degree. with one resting atop the other. The auto-plane includes a rear stabilizer system which can be retracted forward to reduce the overall length for road use, a Pusher type propeller, and a Pusher type aviation engine which is located within the fuselage to drive the propeller. Landing wheels are located on the underside of the fuselage in an aviation landing relationship, e.g. tricycle, and aviation controls are located within the fuselage to control the aviation engine, propeller and elevons and rudders.

Abstract: A glider comprising a pair of wings having overlapped forward, inner root portions that are freely pivotally connected and tailfins on rearward, outer portions of the wings. The tailfins are angularly offset from the general longitudinal axes of the wings so as to have an airfoil liftout angle of attack to the relative wind during flight which causes the wings to swing out to an extended configuration.

Abstract: Unmanned missile with strongly backswept wing unit, in particular delta wings, which is transported in a container and is launched from the container by means of an auxiliary drive after release of a lock, and which during cruise flight is drivable by a propeller engine, lateral force surfaces (25) being deployable for stabilization of the missile during cruise flight, from retraction spaces (26) in the region of the wing root of the delta wings, and further a friction clutch (64, 65) is provided at the missile which, without supply of energy from the outside, couples the standing propeller 6 with the drive motor (7) running in the container, after leaving the container.

Abstract: An erectable wing structure for a supersonic airframe that is stowable within the body of the airframe includes a housing defining an elongated cavity in which is mounted a wing supporting strut assembly having an elongated leading edge strut pivoted at one end within the stowable cavity and including a trailing strut that is foldable and pivotally connected at one end to the cavity structure and at the other end to the outer end of the leading edge strut and including a single layer of fabric stretched between the strut and clamped between the strut structure made up of separable, mirror image, strut links.

Abstract: Air, Land and Sea vehicle is convertible between aircraft form, road vehicle form and boat form. The conversion between aircraft form and road vehicle forms having (4) four tires as an automobile as well as a roadable vehicle structure that are movable outwardly for highway usage, and inwardly into stored position for the aircraft form or boat form, and having storage for the wing and tail assemblies which has a foldable section for this purpose. For conversion between aircraft form and boat forms, the apparatus has a retractable or extendable water propeller as propelling means in the water, and parts arranged for steering. The wings and tail assemblies are moved inwardly into stored position including auto and aero tires moved inwardly into their water-leak-proof compartments.

Abstract: What is proposed by the invention is a fin deployment mechanism for missiles in which a fin member can be extended from or retracted to the contour of a missile by means of a rotary to linear motion transmission system employing a rotatable screw shaft having respective adjacent portions embodying a left hand and a right hand thread for supporting respective ones of a pair of screw nuts, each of which are provided with a cam slot for receiving a cam follower mounted on the fin member, or fin supporting member, so that when the screw shaft rotates the screw nuts are caused to move therealong in mutually opposite directions and via the cooperation between the cam slots and the cam followers the fin is caused to rotate through a given angle. In each of the extreme positions of the fin member a locking engagement is effected for retaining such positions in a locked condition.

Abstract: Canards are pivotally mounted on the fuselage of a variable sweep wing jet aircraft and project laterally with respect to the fuselage forwardly of the wings. The canards are positioned and configured to produce pitch control moments about the center of gravity. Thrust-vectoring devices extend from the jet engines of the aircraft for varying the thrust direction of such engines. A control system is mounted in the fuselage and extends to the wings, the canards and the thrust-vectoring devices for controlling the wings in angular positions relative to the fuselage, controlling the canards in rotary position relative to the fuselage and controlling the thrust-vectoring devices to control the thrust direction. The positions are controlled in coordination to overcome pitch departure, deep stall and spin, which might otherwise occur due to lack of nose-down pitch power, while also optimizing supersonic cruise and transonic maneuver performance of the aircraft.

Abstract: A self-erecting collapsible wing for an airframe includes a telescoping strut assembly including a leading strut and a trailing strut each pivoted at an inner end to fixed pins on a base support structure of a wing housing within a slot in the airframe for retraction to a colinear position within the housing and spring biased to an outward fully deployed position. A releasable cover conforming to the curvature of the airframe is normally latched in position over the slot when the wing is in the collapsed position within the wing housing and is jettisoned to permit automatic self-erection of the wing.

Abstract: A pair of canards (18, 20) are mounted to the fuselage (22) of an aircraft (10). Each canard is mounted to the fuselage by a hinge (44) for vertical swinging movement. Connected to the hinge (44) is a trunnion (72) about which the canard rotates for incidence adjustment. The hinge (44) for each canard is independently powered by a drive motor (58) enabling the canards (18, 20) to be vertically moved either symmetrically or asymmetrically. Incidence is changed by a rotary actuator housed within the trunnion (72) for each canard. The rotary actuator for each canard is independently operable enabling the canards (18, 20) to be symmetrically or asymmetrically rotated.

Abstract: A rollable airfoil, and aircraft for utilizing the airfoil. The airfoil is made of an upper skin having a cambered configuration and formed of a material having sufficient elasticity that the camber can be broken and the skin rolled into a coil. The lower skin is straight to provide the desired flat under surface of an airfoil, and to pull the edges of the upper skin towards each other to assist in maintaining the camber. The lower skin is stretchable to allow the upper skin to be flattened for rolling. A filler material, such as an expanded plastic, can fill the space between the upper skin and lower skin to dampen vibration.

Abstract: An unmanned aircraft vehicle to be launched from a container is provided with a rocket engine for launching and a propeller drive for cruising; the wings can be folded to the body of the vehicle and will be deployed as the vehicle leaves the launching container. The propeller is freely rotatable, even if the vehicle is still in the launching container. The rocket engine is releasably connected to at least one point on the propeller drive and in symmetrical relation to maintain the propeller drive coaxial to the propeller shaft, and to react rocket thrust directly into the propeller drive.

Abstract: A moveable wing aircraft including a quick release, attachment mechanism carrying the aircraft on a bomb rack or other carrier and a mechanism for deploying the moveable wing from its captive carry position to its extended free flight position are disclosed. The aircraft includes an elongate fuselage, a portion of the top surface of which is substantially flat in order to accommodate the moveable wing. The moveable wing is positionable between a captive carry position in which it is aligned with the longitudinal axis of the fuselage and an extended free flight position. The single, moveable wing is pivoted around a central point from its captive carry position to its extended free flight position such that it is substantially perpendicular to the aircraft fuselage. The quick release mechanism extends through apertures in the wing in its captive carry position and is spring biased to retract through the wing and into the aircraft fuselage when released from the bomb rack or other carrier.

Abstract: A rotor having airfoil-section shaped blades is set into a fluid stream. Over a connection-or-transmission means a propeller is connected to the rotor. The fluid stream whereinto the rotor is set gives airflow energy to the rotor and revolves the rotor. The propeller is driven by the rotor over the connection-or transmission means. Since the propeller is revolved by the rotor in the fluid stream, the propeller provides a thrust. The thrust may be used to lift a weight or to drive a member. A suitable application of the arrangement is for example, to transform a multi-bladed helicopter into a gliding craft which descends under a gliding angle towards the surface of the earth, when the helicopter has a complete engine failure. Auto-rotation accidents can thereby become prevented. The device is also applicable to drive a vehicle or to lift a weight. Variable means can be applied to obtain variable thrusts in flying craft to improve their efficiencies or change from one flight-system to another flight system.

Abstract: In an ammunition unit in the form of a shell (1), projectile or the like which is fin-stabilized, an extendable fin is utilized which is intended to be retracted during firing in a barrel or the like and to be extended as soon as the shell or the like has left the barrel. The extendable fin is intended to increase the stability of the ammunition unit in the ballistic trajectory. The extendable fin consists of two fin parts (4' and 4") supported separately in relation to each other and which in their extended positions are joined together and form the fin.

Abstract: A vehicle or craft is provided for propeller propulsion with start assist by a releasable rocket engine. The craft is launched from a silo of square-shaped cross-section containing the starter motor for the propeller, whose engine is started while the craft is still in the silo. Diagonally opposed corners of the silo are provided with rails, in which run guides on rudder fins of the craft. The wings are pivoted to the fuselage for deployment whereby the wing tips do not move forward. The rocket engine is jettisoned shortly after take-off by simple disengagement. Parts of the wings and/or the rear of the fuselage may be jettisoned shortly before the craft reaches the target area.

Abstract: A displacement mechanism for effecting both rotary movement of a movable member (for example a fin) with respect to a fixed member (for example a flight vehicle body) from a first, inoperative position to a second, operative position about a longitudinal axis and axial movement of the movable member along that axis to effect subsequent locking in the second position, comprises a fluid operated vane motor to effect rotation and a fluid operated piston/cylinder arrangement to effect the axial movement. Preferably the vane motor and the piston/cylinder arrangement are closely integrated one with another.

Abstract: A flying device capable of carrying man, which contains a wing, a fuselage, and means such as cables for attaching the wing to the fuselage so that the fuselage is suspended below the wing. The fuselage contains a propulsion unit and normally does not have wings for creating a lifting force as in ordinary aircraft.

Abstract: An attachable airfoil for use on an airborne vehicle or payload having a plurality of joined, nestable sections which can expand from a collapsed, streamlined position adjacent the vehicle or payload to a fully extended airfoil configuration. In addition, the airfoil incorporates therein a movable control surface which by appropriate remote actuation can be utilized to provide controlled flight of the airborne vehicle or payload.

Abstract: The specification describes an aerodynamic structure having lift for use on an aerodyne. The structure comprises first and second essentially identical planar sections hingedly connected at their roots to one another at dihedral angles. The sections are moveable in unison to vary the angle between each section and its transverse axis.

Abstract: The guard retains the cable on a pulley of a cable control system that indes another pulley mounted on a pivotable radius arm for swingable movement relative to it. Usually, the swingable pulley is linked to a third pulley mounted on a hinged structural member which itself swings with the radius arm to and from `closed` or `open` positions. When the arc is wide, i.e. around 180.degree., conventionally mounted guards engage and bind the swinging cable. The present guard is an elongate member pivotally mounted on the radius arm. In the `closed` position, a retaining flange formed on the guard moves for cable retaining purposes into close proximity with the fixed pulley and the proximity or clearance can be adjustably fixed and locked by an eccentric stop. During the `opening` swing, the cable engages the guard which then pivots sufficiently to prevent the undesired binding. The pivotal range of the guard is restricted by a pin and slot arrangement.

Abstract: The apparatus is convertible between road vehicle and aircraft forms having wing and tail assemblies as well as propelling structure that are movable outwardly for the flying form and movable inwardly in stored position for the road vehicle form. All of the parts of the apparatus remain intact in both the road and flying forms. Storage for the wing and tail assemblies and the propelling structure is in side and end compartments, and the wing and tail assemblies have foldable sections for this purpose. The apparatus has a pair of front wheels and a pair of rear wheels, the latter wheels being movable between a narrowed rearward position for road use which allows storage of the wings in the side compartments and a forward widened position for aircraft use. The tail assembly is supported on a slide mechanism which extends downward in a forward longitudinal direction whereby the tail assembly is lowered as it is moved forwardly for storage in the rear compartment.

Abstract: A helicopter has main rotor blades foldable over its tail cone and a tail rotor pylon which is foldable about a tail cone vertical hinge from its fore-and-aft flight position through an angle approaching 180.degree. to lie alongside the tail cone. Tail rotor pitch control mechanism includes a cable which extends across the foldable hinged members, direction change pulleys for the cable and an improved 4-bar linkage system which controls the movement of the pulleys within a small envelope circle and maintains a constant tension on the cable throughout the full fold cycle.

Abstract: A method wherein a propeller driven, hydrazine powered aircraft is remotely piloted through rarefied atmosphere of a selected planet, including the planet Earth, and employed as a communication platform for a telemetry system provided for relaying information relating to features characterizing the surface of the planet.

Abstract: A surface vehicle has two wings, which are hinged to a wing core along axes extending along the wing center axis, to change the angle of attack, so that the trailing wing edges as extending towards the rear in converging configuration remain in a common plane and close the plenum chamber with reference to the (hypothetical) mirror image of the wing construction.

Abstract: An airplane includes a wing having the configuration of an equilateral triangle and covered with a flexible membrane which is provided with free trailing edges. The wing is secured by pivot brackets to the top of supports placed at the center of gravity of the airplane body as to pivot right and left alternatively to obtain a self-balancing of flight like the action of a flying kite, such that it is safe and easy to control the airplane during takeoff, landing and sustained flight while increasing the lifting force.

Abstract: A folding airfoil for an aircraft in which the wing or stabilizer airfoil n be folded and contained entirely within the fuselage of the aircraft. The airfoil comprises a series of elongated sheet metal channel sections of generally C-shaped cross section with the cross sectional dimension of successive channels decreasing so that each can nest entirely within an adjacent channel.

Abstract: The stowable airfoil structure is a tapered, high aspect ratio, retractable and foldable wing for aircraft which provides minimum aerodynamic drag during launch and minimum space for ground storage. The airfoil utilizes a forward leading edge box section to which is attached a plurality of spanwise channels hinged together for movement in a chordwise direction. Retraction of these elements takes place by the utilization of suitable actuators so as to move the hinged elements forwardly in a nested position thereby substantially reducing the width of the wing or airfoil which is then folded to lie along side the fuselage of an aircraft.

Abstract: A foot-launched passenger carrying wing capable of flight including a frame, a flexible wing covering the frame, a keel, a bracket slidable on the keel, cross brace members pivotally attached to the bracket at one end and to leading edge members of the frame at the other end, and cables connecting the parts to provide an operative structure when the bracket is moved in one direction to extend the frame into flying condition and to collapse the frame when the bracket is moved in the opposite direction. Movement of the bracket also adjusts the billow of the sail and the dihedral of the frame. The wing sail is attached to the leading edge members along their entire length and to the keel along a portion of the rearward end thereof. An arrangement is provided to adjust the bracket before or during flight to provide different billow and dihedral conditions.

Abstract: An aircraft that is designed to additionally be able to travel along a railroad track so that it can get into a heart of a city, instead of terminating at an airport located some distance away from the city; the aircraft including wings which can be folded inwardly adjacent the side of the aircraft fuselage so that it requires approximately a same width of clearance as a conventional railroad train, and the railroad tracks being additionally fitted with a system of channel rails welded on top of the oid railroad track so that the airplane can travel thereupon.