Abstract: A fin cover release and deployment system designed for high G forces of gun-launched missiles. In one embodiment, a pyrotechnic actuator drives actuator arms to first release and eject the fin slot covers, followed by deployment of the fins radially outward to the steering position. Following complete ejection of the covers, the fins are driven outwardly by cam surfaces along the latch arms, followed by a spring and wedge mechanism installed interiorly of the fin steering shaft to lock the fins in the fully deployed state. In another embodiment, a motor and rotating threaded shaft replace the pyrotechnic actuator.

Abstract: A drive assembly for use with a mechanical flying or walking device comprises an articulated member (7) having first and second portions (7a, 7b) arranged such that the portions move relative to each other, and a drive mechanism (9) for imparting motion to the articulated member. The drive mechanism (9) comprises: a drive member for imparting a cyclic motion on the articulated member, and a control member for controlling, in a predetermined manner, the relative position of the first and second portions during each cycle of the cyclic motion of the articulated member. In the case of a mechanical flying device, two such drive assemblies may be provided, the articulated member of each assembly forming a wing.

Abstract: A pusher canard aircraft convertible for road use. Canard outer sections are removable and are stored within the aircraft fuselage and the outer main wing sections rotate horizontally for storage on the fuselage top. The fuselage is designed as a lifting body which gives the aircraft three lifting surfaces. The lifting body takes advantage of ground effect, resulting in a lower landing speed. In road mode the vehicle as a 2 or 4 passenger model is smaller than a full size automobile. Hydraulic motor wheels propel the aircraft/vehicle for road use. An internal combustion engine within the fuselage drives the propeller for air operation. The propeller is disengaged, not removed, for land operation and the engine is used to drive an hydraulic pump to power the motor wheels for road use. A single nose wheel or two front wheels are used for both steering in landing/taxiing and for road use. In road mode, the appearance is as much like a van than as an aircraft.

Abstract: A tail boom saddle for use with a helicopter. The helicopter has a fuselage, a main rotor assembly extending out from a forward section of the fuselage, and a plurality of main rotor blades operatively coupled to the main rotor assembly. A tail boom section of the fuselage includes a first frame member, a second frame member longitudinally spaced from the first frame member, a plurality of longerons extending between and intersecting with the first and second frame members, and a tail boom outer skin surrounding the frame members and longerons. The main rotor blades, are movable to a stowed position in which the main rotor blades extend generally rearwardly of the main rotor assembly. The tail boom saddle comprises upper and lower saddle portions adapted to exert clamping forces against the tail boom outer skin. The tail boom saddle is adapted and configured to at least assist in maintaining the main rotor blades in the stowed position. The upper saddle portion includes first and second support beams.

Abstract: A missile includes a missile body and a guide assembly mounted on the missile body. The guide assembly has a plurality of pivots and a plurality of vanes mounted on respective pivots for a swinging motion between a folded position of rest and a deployed flight position. The vanes are arranged for free pivotal motion during flight in response to forces acting thereon to determine the flight position. In the folded position of each vane, its center of gravity is situated at a greater distance from the longitudinal axis of the missile body than the pivotal axis of the respective vanes. Abutments limit the flight position of the vanes to a maximum angle between the length dimension of the vanes and the longitudinal axis of the missile body. The maximum angle is greater than 90°.

Abstract: A spacecraft such as a fly back booster or a reusable launch vehicle, or an aerospace plane has a fuselage and a set of scissors wings consisting of two main wings. Both of the main wings are rotatably mounted on the fuselage and can be yawed at opposite directions. If the spacecraft is launched vertically, both of its main wings can be yawed to be generally parallel with its fuselage so that it can connect with other vehicle or vehicles to form different launch configurations. When the spacecraft or aerospace plane is flying in the air, landing, or taking off horizontally, it can yaw both of its main wings in opposite directions to maximize its lift-to-drag ratio by optimizing the yaw angle of the main wings according to flying conditions. It can also produce desired aerodynamic characteristics such as forming a high drag configuration by adjusting the yaw angle of its main wings.

Abstract: An unmanned air vehicle includes a singular rear landing gear wheel on the aft end of the fuselage. Port and starboard wings with rear facing propellers are retractable to the aft of the fuselage. Upon retraction, the propellers may freewheel and a reversible motor-generator is provided to convert the freewheeling propeller energy into electric power. Photovoltaic cells also provide electric power to the unmanned air vehicle. Port and starboard nose fairings are control surfaces for the vehicle. The port and starboard nose fairings also include landing gear wheels. A method of flying an unmanned air vehicle includes retracting port and starboard wings to achieve a ballistic dive.

Abstract: An STOL aircraft structure has a variable-attitude, variable-area wing in addition to a traditional airfoil. The variable wing has an angle of attack that varies from 0° to a predetermined angle far in excess of the stall angle. The variable wing area can be adjusted from 0% to 100% by a roller furling arrangement. The aircraft structure operates during takeoff by deploying the variable wing with an attitude exceeding the stall angle, applying thrust to the aircraft so that the variable wing generates reaction lift and the aircraft attains a predetermined altitude, and stowing the variable wing so that the traditional airfoil is the primary lifting surface. Those steps are reversed for landing.

Abstract: A missile or projectile tail section includes an outflow device and a number of deployable fins. The outflow device may be a base bleed device that includes a slow-burning propellant which fills the vacuum created by the projectile's motion through the air. Use of the outflow device may allow the projectile range to be extended by up to 20%. The fins are stowed canted relative to planes that include the axis of the tail section. By canting or tilting the fins relative to the axis of the tail section, increased space is made in the tail section for the outflow device. Although the fins are stowed canted relative to the tail section, they may be configured so as to be deployed such that the axis of the tail section is substantially within the planes of the fins.

Abstract: An unmanned flying vehicle comprises an autonomous flying wing having at least two wing portions arranged substantially symmetrically about a center portion. Each wing portion is pivotally attached to each adjoining portion such that the wing portions are foldable for storage and openable for deployment. A preferred form is the so-called seagull wing having four wing portions. The vehicles may be programmable from a mother aircraft whilst being borne to a deployment zone using a data link which may be wireless.

Abstract: A road/air vehicle is able to quickly and easily convert between two configurations, air configuration and road configuration, to facilitate practical operation as both an aircraft and as an automobile. In air configuration the craft includes two laterally symmetrically flight surfaces; a smaller forward canard wing, generally horizontally disposed and a larger rearward main wing generally horizontally disposed with fin surfaces, generally vertically disposed, at each tip. Control surfaces on the main wing, the canard wing and the tip fins severally provide roll control, pitch control and yaw control in flight. The wheels/undercarriage are of a laterally symmetrical rectangular pattern, with the lateral distance between the two forward wheels and the two rearward wheels being similar. The forward wheels are steerable for ground operations. A suitable powerplant drives the rear wheels for ground operations. A second suitable powerplant provides direct atmospheric thrust for flight operations.

Abstract: The apparatus of the invention allows flight vehicle and/or guided munition wings and control surfaces to be secured in a retracted and locked position prior to the launch by a control surface retainer. An electro-mechanical differential control system preferably releases the control surface retainer, extends the control surfaces, and servo controls the control surfaces subsequent to launch. The invention also provides a method for guiding a flight vehicle and/or guided munition by releasing the flight vehicle's and/or guided munition's control surface from a control surface retainer, extending the flight vehicle's and/or guided munition's wing/control surface assembly using a wing/control surface actuation system, and controlling the flight vehicle's and/or guided munition's control surfaces using a wing/control surface actuation system.

Abstract: Described is a rudder blade mounting arrangement (10) for a missile comprising a rudder blade (12) and a mounting element (16) for the rudder blade. The rudder blade (12) is displaceable about a rudder blade axis member (36) of the mounting element (16) between a retracted inactive position and a deployed active position. The rudder blade foot (14) of the rudder blade (12) is connected in positively locking relationship to the rudder blade axis member (36) in such a way that, in the deployed active position of the rudder blade (12), the rudder blade foot (14) is forced against a front face (62) of a side portion (24) of the mounting element (16).

Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state.

Abstract: Disclosed is a spacecraft carrying a number of pods, each containing an aircraft that has been folded to fit in the pod. Each aircraft has a vertical stabilizer and outboard wing-portions that fold around fore-and-aft axes. Each aircraft also has a fuselage that folds around a lateral axis. The spacecraft releases one or more of the pods into an atmosphere. Each of the pods is configured with an ablative heat shield and parachutes to protect its aircraft when the pod descends through the atmosphere. The pod releases its aircraft at a desired altitude or location, and the aircraft unfolds while free-falling. The aircraft then acquires and follows a flight path, and activates scientific experiments and instruments that it carries. The aircraft relays results and readings from the experiments and instruments to the spacecraft, which in turn relays the results and readings to a mission command center.

Abstract: Pyrotechnic actuator cover/fin release system designed for high G forces of gun-launched-systems. As safety feature, system allows the pyrotechnic actuator to be installed as one of the last steps of the final testing sequence and removed safely on disassembly. A first cam action develops initial ejection. Subsequently firing the pyrotechnic pushes both the fins and the covers outward via a second cam surface. The release system both holds covers securely latched until commanded to release and then unlatches covers prior to pushing them open. The cover eject sequence results in the flight forward edge of cover being kicked into air stream. Thereafter the cover is lifted and rotates about its aft release hinge until, at about 30 degrees of rotation, the hinge disengages. The fins then are driven into the fully deployed state by a spring and piston/wedge mechanism on the actuator shaft.

Abstract: Disclosed is a spacecraft carrying a number of pods, each containing an aircraft that has been folded to fit in the pod. Each aircraft has a vertical stabilizer and outboard wing-portions that fold around fore-and-aft axes. Each aircraft also has a fuselage that folds around a lateral axis. The spacecraft releases one or more of the pods into an atmosphere. Each of the pods is configured with an ablative heat shield and parachutes to protect its aircraft when the pod descends through the atmosphere. The pod releases its aircraft at a desired altitude or location, and the aircraft unfolds while free-falling. The aircraft then acquires and follows a flight path, and activates scientific experiments and instruments that it carries. The aircraft relays results and readings from the experiments and instruments to the spacecraft, which in turn relays the results and readings to a mission command center.

Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state.

Abstract: A locking and unlocking mechanism for moveable control fins extending from the surface of a missile. The locking mechanism includes a pin extending thru the outer surface of the missile into an opening provided in the movable fin. A link is pivotally connected between each of the pins and a slide member disposed internally of the missile and carried by a guide. The links are in a close to dead center position when the pins are extended into the openings in each of the fins. A striker assembly is disposed within the slide member and includes a rod carrying a hammer which is spring loaded spaced from the slide member when the pins are in their extend position.

Abstract: A payload carrying device which is inserted into a remote area of interest by means of a projectile carrier to obtain data, or the like, from the remote area. The device has counter rotating main blades as well as tail blades carried on a tail rotor. The particular payload is carried in a canister which may also include a power source, a command and control unit and a motor, if hover or lateral flight is desired. The pitch of the tail blades is variable as well as their orientation around an axis, the combination of which generates a thrust vector in a particular direction for controlled lateral flight.

Abstract: A deployable wing that is folded so as to fit into a carrier such as an airplane that is released and automatically with the aid of parachutes to deploy and fly a given distance without assistance other than steering to reach a given destination and a propeller driven by a gas powered engine is actuated to propel the wing an extended distance. A guard is disposed adjacent to the propeller to assure that the lines of the parachutes do not get tangled into the propeller blades.

Abstract: In an adjusting apparatus for control surfaces of a missile the control surfaces 2, 3 are displaceable by adjusting motors 5, 6 by way of thrust spindles 15. To afford a compact structure and a low weight the stators 7 of the adjusting motors 5, 6 are arranged directly in a carrier housing 4 and the thrust spindle 15 engages into a female thread 14 of the motor shaft 9.

Abstract: The openings in the fabric ribs of a deployable wing made from fabric sail material is automatically closed by use of a zipper mounted adjacent each of the openings that is actuated by movement of the cross spars of the deployable wing which serves to prevent the airfoil surface to the wing to bulge and cause a drag to the deployable wing when in flight.

Abstract: A compact, aerodynamic wing assembly constructed and arranged so as to withstand a force due to acceleration in at least one direction includes at least two wing segments, each of the wing segments having a span-wise axis, and a airfoil cross section normal to the span axis. The wing segments are preferably disposed mutually adjacent and end to end. For each pair of wing segments, the wing further includes a pivot assembly fixedly attached to the wing segments at an end of each of the wing segments along the span-wise axis. The pivot assembly forms an articulation axis for relative movement between each the pair of wing segments, such that the wing assembly converts, upon a predetermined stimulus, from a stowed configuration characterized by nested wing segments, to a deployed configuration characterized by a substantially uninterrupted aerodynamic surface.

Abstract: A transformable gun launched aero vehicle having a ballistic projectile configuration and an aeroplane configuration includes a cylinder forming a shell of the vehicle in the ballistic projectile configuration and wings deployable from the cylinder. The wings are capable of achieving sufficient lift for sustained flight in the aeroplane configuration. The cylinder forms a fuselage of the vehicle in the aeroplane configuration. A wing includes plural rib elements, plural inflatable tubes where each tube is braced by the plural rib elements, and a wind shell disposed around the plural inflatable tubes and the plural rib elements. The vehicle includes an inflatable tail section that is inflated while the vehicle is in the aeroplane configuration. The vehicle includes a parachute that is reversibly deployable from a nose portion of the vehicle. The vehicle includes at least one landing rod. Each landing rod is reversibly extendable from the vehicle.

Abstract: A wing fold actuation system (24) is provided for folding an outboard wing section (18) relative to an inboard wing section (16) between a deployed position (20) and a stored position (22). The system (24) includes an actuator (26) in the form of a geared rotary actuator (30) in combination with a four-bar linkage (32). A locking mechanism (28) is provided to lock the outboard wing section (18) in the deployed position (20), and includes a catch on the outboard wing section (18) that is engageable with a rotary latch (42) on the inboard wing section (16). A timing transmission (46) connects the rotary actuator (30) with the rotary latch (42) to time the rotation of the rotary latch (42) with respect to the movement of the outboard wing section (18) between the deployed and stored positions (20,22).

Abstract: An airborne pneumatic launch tube ejection system to described for launching an aerospace vehicle/payload into orbit. The system can be installed in a jet transport aircraft without requiring structural modifications.

Abstract: An apparatus that permits a rotatable wing to be operated in three modes: a first orientation mode, a second orientation mode, and a mode in which the wing rotates (called the rotating mode). The apparatus permits the wing to be stowed and used in both fixed-wing flight and rotary wing flight. The apparatus may be a component of an aircraft capable of fixed-wing flight with a fuselage oriented generally in the direction of flight. In the first orientation mode, the wing is generally parallel to the orientation of the fuselage, providing a relatively compact stowage configuration. In the second orientation mode, the wing is generally perpendicular to the orientation of the fuselage. The first orientation mode thus facilitates stowage of the wing during stowed flight of such an aircraft under power of a host aircraft, the second orientation mode facilitates fixed-wing flight, and the rotating mode facilitates rotating-wing flight. The wing may be started into auto-driven (i.e.

Abstract: A vehicle that combines the freedom and swiftness of flight with the utility of surface travel. A simple, light weight, safe and stable conveyance with positive yaw-roll coupling, special safety features, no fold wing stowage and a unique single power source. It can be built using common tools and techniques with readily available materials at a cost competitive with the family automobile.

Abstract: A retention and deployment mechanism for pivotable guide fins on bombs or missiles includes a cup shaped yoke slidably mounted on a shaft. The device is mounted in a central region of the bomb tail and engages tabs on each of the fins. The tabs are held between a retaining flange and pusher arms extending radially from the yoke. The retaining flange prevents pivoting of the fins until desired. A drive spring causes the yoke to slide axially, and the pusher arms push on the fins to cause pivoting to the deployed position. The yoke includes a head end with a cone shaped recess. Four balls seated in holes in the shaft contact the cone shaped recess to prevent movement of the yoke. A pin disposed in a bore in the shaft hold the balls in the seats. The pin includes a groove, and is movable by a spring to a position where the balls fall into the groove, thus releasing the yoke. A lanyard is attached to the aircraft and extends through aligned holes in the shaft and pin to retain the pin in position.

Abstract: A guided missile (12), in particular a projectile which can be fired through a propellent charge gas pressure, having rudder blades (18) which cross each other and which can be pivoted open to steer the missile (12). Each rudder blade (18) is mounted in a guide slot (22) which is closed at the front end by an end portion (26). Each end portion (26) has a spoiler end face (28). Each end portion (26) projects radially beyond the lateral longitudinal ribs (24). At its distal end portion (32) the associated rudder blade (18) is provided with laterally mutually opposite, narrow guide ribs (36) which project out of the rudder blade profile (34).

Abstract: To maintain control accuracy for the pivotable rudder blades (14), which lie in a combustion chamber, of a guided projectile (12) which can be fired by means of propellent charge, there is provide a mounting arrangement in which the trunnions (20) of the rudder blade holders (16) of the diametrally mutually opposite rudder blades (14) are torsionally stiffly rigidly connected through an associated coupling element (32) which is limitedly resilient in the radial direction of the guided projectile (12).

Abstract: An airborne vehicle having a deployable airfoil with an elevon wherein the deployment of the airfoil and the control of the elevon are both powered by a single servo mechanism. A shear pin prevents relative movement between the elevon and the airfoil until the airfoil is in the deployed position. A stop mechanism locks the airfoil in the deployed position, whereafter operation of the drive mechanism fractures the shear pin, thereby allowing the elevon to be controlled by the drive mechanism.

Abstract: A vehicle refueling system includes an aero vehicle and a fuel bladder system. The fuel bladder system includes a fuel bladder, a pickup loop of a predetermined loop size, a reel mechanism to retract at least one side of the pickup loop to reduce the loop size, a snag sensor to sense when the pickup loop has been hooked by the retractable hook, the snag sensor initiating the reel mechanism, a compass to sense the random orientation of the loop, a radio navigation receiver to sense a location of the loop, and a transmitter to transmit the random orientation and the location.

Abstract: A shoulder launched unmanned reconnaissance system for providing overhead visual surveillance of remote targets is disclosed. The present system includes a reconnaissance air vehicle which may be fired from a portable launcher, accelerated to flight speed, and remotely controlled using a ground control system. The vehicle is flown to the target area to enable an onboard wide angle video system to transmit video images of the target by radio or fiber optics link to the ground control system for processing and display. The ground control system enables the reconnaissance vehicle to be flown to a recovery area and to descend in a stall mode after the flight is completed for maintenance prior to reuse. The air vehicle includes collapsible wings which are deployable after launch by a spring actuated mechanism. The fuselage of the air vehicle carries an onboard video camera, an electric motor, a battery, a global positioning system receiver, flight controls, and a data link system.

Abstract: A roadable aircraft includes three symmetrically lateral flight surfaces, comprising a forward main wing generally centrally located relative to the fuselage or body, a rearwardly located stabilizing surface acting as an empennage support, and a rear stabilizer and elevator located at the rearward end of the empennage tail booms. The wheel or landing gear configuration is of a rhomboid pattern, with forward and rearward main wheels along the centerline of the craft, and left and right outboard wheels. The outboard wheels extend and retract individually to a limited degree to compensate for centrifugal forces in ground operations, and together in coordination with the main wheels for flight operations. The powerplant drives the rearward main wheel from one end of its output shaft, and the propeller from the opposite end of the output shaft.

Abstract: A wing fold (50) for an aircraft has inner wing (74) connected to the aircraft and an outer wing (76) connected to the inner wing (74) by a hinge (72). An actuator (72) is capable of rotating the outer wing (76) over ninety degrees with respect to the inner wing (74). A first reinforced elastomer panel (54) is connected between a lower surface (52) of the inner wing (74) and a lower surface (58) of the outer wing (76).

Abstract: A retractable wing assembly for a flying vehicle includes a vane support member, a wing with vanes, and a wing extending and retracting assembly. Each vane includes a base portion and an end portion and is pivotally secured to the vane support member at its base portion. The wing extending and retracting assembly includes link members and an articulating assembly. Each link member pivotally connects two of the vanes together between the base portions and end portions of the two vanes. The articulating assembly is secured to a vehicle body and mechanically coupled to the vane support member and at least one of the vanes. The articulating assembly is manipulable to reposition the vane support member relative to the vehicle body while simultaneously spreading the end portions of the vanes apart from each other.

Abstract: Pairs of aerofins used for stabilization and control of missile flight are deployed through shared longitudinal slots provided in the missile body. Before launch, the pairs of aerofins, each pair comprised of a canard and a deflector, are retained in a folded position by a releasable latch mechanism within the missile body. The deflectors are mounted in a laterally displaced position from the longitudinal slots and are constrained from sliding into alignment with the slots by the presence of the folded canards. When the canards are released by the latch mechanism and permitted to extend outward to their deployed positions, the deflectors are able to laterally shift, effectively displacing the canards in the alignment position and subsequently deploying. The latch mechanism is designed to simultaneously release all the canards following missile launch, with biasing torsional springs operating to urge the canards outward through the associated slots to the extended position upon release.

Abstract: Once the rotor of a rotary-wing aircraft is held stationary in an indicated position, the method comprises steps consisting in placing the collective pitch control stick in a first predefined position corresponding to a first inclination of the blades about their longitudinal axes, in placing the cyclic pitch control stick in a second predefined position corresponding to a nose-up position of the rotary-wing aircraft, in modifying the length of the control system to cause the inclination of the blades about their longitudinal axes to go to a second value that is different from said first inclination value, in holding a rotary swashplate stationary by placing at least three locking connection rods between the rotary swashplate and a member integral in terms of rotation with a rotor mast, and in folding the blades by rotating each of them about a corresponding coupling pin for coupling it to a coupling member for coupling the blade to a rotor hub.

Abstract: An aircraft landing assist system comprised of a preformed and prepacked parawing-bag and fuselage housing and deployment is described. In case of emergency the system can be deployed automatically, manually, or by means of explosive charge. After deployment the open doors and the self inflated parawing-bag catch the on rushing air forcing the nose of the aircraft up. This helps increase the glide ratio and decrease the velocity of the aircraft. Control of the aircraft remains through the use of the upper wing surfaces and tail assembly. Upon landing the system helps extend the time of, and surface area of impact. Drains are provided in the aft section of the parawing-bag(s) to release rain or snow.

Abstract: The present invention is directed to a unique foldable winglet assembly adaptable for use with an aircraft for maximizing the wing span of the aircraft during cruise operation while reducing wing bending moment during extreme flight maneuvers. A foldable winglet is pivotally joined to the aircraft wing and is rotatable during flight between a retracted position and a fully extended position. An actuator is mounted on the aircraft wing and attached to the foldable winglet. When the aircraft reaches cruise operation, the actuator can be manually or automatically energized to pivot the winglet from a substantially vertical, retracted position to a fully extended position wherein the winglet becomes an extension of the wing. During cruise, the wing and winglet form an enlarged wing that serves to maximize lift of the aircraft.

Abstract: An aircraft with a variable forward-sweep wing and the method of configuring the wing in an optimal position for a desired flight regime. The variable forward-sweep wing is positionable from an essentially unswept position to a full-forward sweep position. In the unswept position the wing is approximately orthogonal to a fuselage centerline, while in the full-forward sweep position the wing has approximately a delta wing planform. Moreover, as the wing position changes from the unswept position to the full-forward sweep position the trailing edge becomes the leading edge. In addition, the aforementioned apparatus may be used in a method to configure the aircraft for flight in a desired flight regime. This method includes moving the wing to an optimal position for the desired flight regime.

Abstract: A fixed wing aircraft that can be automatically and rapidly converted to a roadway vehicle within seconds while driving in the highway, comprising a one-piece wing rotatably mounted on top of the fuselage. The aircraft features a 3-horizontal-surface design allowing good pitch stability and damping in a very short fuselage, stall-resistant feature and reduction in induced drag at cruise speed. The aircraft's wing is enlargeable with additional wing tip segments allowing boost in aspect ratio hence improving efficiency at high loads. The vehicle has low center of gravity, four wheels with independent suspension, nose-height leveling for take-off and landing, and anti-sway mechanism in order to prevent roll-over in a tight turn. Ground propulsion is by both a ducted fan and hydraulic rear wheel drive allowing rapid accleration in the roadable mode.

Abstract: The deployable wing of the present invention comprises an internal structure having diverging leading edge spars attached to a keel spar and cross spars to form a delta wing configuration. This internal structure is enclosed within a volume defined by a fabric sail having an upper section, a lower section, and fabric ribs disposed therebetween. This fabric sail volume is internally pressurized through a ram air intake at the nose stagnation point. This deployable wing can be folded, extracted from an aircraft and deployed in the air.

Abstract: The deployable wing of the present invention comprises an internal structure having diverging leading edge spars attached to a keel spar and cross spars to form a delta wing configuration. This internal structure is enclosed within a volume defined by a fabric sail having an upper section and a lower section. This fabric sail volume is internally pressurized through a ram air intake at the nose stagnation point. This deployable wing can be folded closed, extracted from an aircraft, deployed in the air and landed with the aid of parachutes.

Abstract: A fixed-wing four-seat light aircraft that can be easily converted to a roadway vehicle within minutes by a single person in the field, comprising a one-piece wing center panel with foldable wing tips on each sides. The whole wing unit is then rotatably mounted on top of the fuselage. The aircraft features a conventional front-engine-and-propeller lay-out, with a short fuselage for convenient roadability and garageability, with horizontal stabilizer of significant span with foldable tips for adequate flight stability. The vehicle has a low ride-height with a low center of gravity, four wheels with independent suspension, nose-height leveling for take-off and landing, and anti-sway mechanism for adequate ground handling. Ground propulsion is by automotive-style transmission driving the front wheels.

Abstract: A mechanism (100) is disclosed for deploying wing air foils about mutually perpendicular axes. Air flow initiates deployment of the wings by causing pivoting motion of a T-joint fitting (112). Meshed gear teeth between the wing (122) and the elevation plate (108) also causes the elevation plate to pivot. The axis of pivotal motion of the elevation plate (108) and the T-joint fitting (112) are offset so that the gear teeth on the elevation plate (108) causes the wing to move from the folded position to the elevated position. A pair of wings are deployed simultaneously by use of a cross shaft (134) that interconnects the elevation plates (108) of each wing deployment apparatus. A hydraulic damper (146) can be operated by the cross shaft (134) to allow control of the rate of deployment of the wings.

Abstract: An improved apparatus for unfolding and fixing missile fins which is capable of automatically unfolding the fins of a missile when launching the missile loaded in a missile launch tube, in which the fins of the missile are folded, which includes a plurality of fins fixed to a missile body, a plurality of rotation fins rotatably supported by the fixed fin, rotation stoppers elastically supported in the direction the rotation fins are unfolded, and unfolding and fixing member forwardly and rearwardly movable with respect to the fixed fins and each having a straight movement stopper elastically supported toward the rotation stopper.

Abstract: The wing deployment device is a simple mechanical device that resides in hollow of the wing and combines a primary and a secondary rotational motions to translate the wing from its stored position to its deployed position. The primary rotational motion occurs when the initial restraint holding the wing to the missile body is severed and the wing, under the influence of the spring component of the device, rotates to a position normal to the missile body axis. After the lapse of a pre-determined duration of time, the secondary rotational motion is started when the tensile force of the spring is transfered to the swivel component via the kevlar rope coupled between the spring and the swivel. As the kevlar rope that is wrapped around the cylindrical shaft component unwinds, the swivel rotates and transmits the rotational motion to the base component which is rigidly coupled to the wing and, in turn, imparts the motion to the wing, thereby engaging the wing in the secondary rotational motion to be deployed.