Abstract: The invention discloses a deployable, inflatable aerodynamic control structure for aerospace vehicles which has a desired noncircular or noncylindrical cross-section and fabrication methods therefor. In a preferred embodiment, the control structure is configured as an inflatable airfoil and includes a flexible skin and a plurality of internally disposed airfoil-shaped bulkheads or integral rib members that are arranged, spaced apart, in cross-wise fashion along the axial length of the airfoil shaped control structure. The flexible skin is fabricated as a lay up, in ordered sequence, of plural layers of elastomeric rubber material and plural ply layers of resin-impregnated yarns or fabric. The result is a fiber-reinforced pressure membrane that is flexible and compactly foldable.

Abstract: The invention is an airborne vehicle. In detail, the invention includes a main body having a longitudinal, lateral and vertical axis. A pair of wings are pivotally mounted to the main body that are movable about an axis of rotation from a retracted position to an extended position external of the main body along the lateral axis. A linkage assembly for controlling the position of the wings is mounted within the vehicle that includes a guide assembly having an open ended slot aligned with the longitudinal axis thereof. First and second links have their first ends pivotally connected to the wings at a position offset from the axis of rotation of the wings, and the second ends thereof pivotally coupled to each other.

Abstract: An aircraft having variable airframe geometry includes an elongate fuselage having top and bottom sides, a swept back, high-speed wing mounted to the top of the fuselage, and a high aspect ratio, low-speed wing pivotally mounted adjacent to the bottom of the fuselage. The low-speed wing is adapted to pivot between a slow speed flight position in which a longitudinal axis of the low-speed wing is generally perpendicular to a longitudinal axis of the fuselage, and a high-speed flight position in which the longitudinal axis of the low-speed wing is generally parallel to the longitudinal axis of the fuselage. A fairing extends from the fuselage for receiving at least a portion of the low-speed wing when pivoted into the high-speed flight position. The low-speed wing further includes landing gear.

Abstract: An airfoil is provided for an aircraft such as a helicopter, wherein the airfoil can be folded to a stowed position and unfolded to an operational position, without requiring an adjustment of the control rod assembly which lies within the airfoil. The control rod assembly (50, FIG. 2) includes inboard and outboard control rods (60, 62) with adjacent ends lying below the main axis (86) about which the foldable airfoil parts pivot, with a linkage (64) connecting the control rods. The linkage includes a long first link (90, FIG. 5) pivotally connected at a first axis (92) to an end of the inboard control rod and a second link (96) pivotally connected at a second axis (102) to the first link and at a third axis (106) to the outboard control rod. The links are constructed so they overlap in the operational position of the horizontal stabilizer, with the first, second, and third axes lying substantially along a force line (70).

Abstract: An aerodynamic lifting and control surface comprising an external box structure that encloses an internal grid whose members are parallel to the box structure. The external box structure comprises four panels connected at their comers by spring hinges. When the hinges are unconstrained, the external box structure is compressed into a flat, thin parallelogram shape. The internal grid comprises a plurality of plates connected to each other and to the external box structure by flexible hinges. Control apparatus for use with an aerodynamic vehicle is also disclosed. The control apparatus comprises at least one aerodynamic lifting and control surface that is coupled to an actuator disposed within the vehicle and connected to the aerodynamic lifting and control surface for rotating it.

Abstract: A deployable diamond shaped wing for use in extending range or increasing maneuverability of guided missiles or munitions. A hardback (10) mechanism attaches the wing kit to an existing guided munition or missile (12) and the forward wing (24) is attached with a forward wing pivot (44) assembly so as to allow the forward wing (24) to rotate in the horizontal plane. The rear wing (22) is attached to a driveshaft (28) and carriage (26) with a rear wing pivot (48) that allows rear wing (22) rotation in the horizontal plane. The forward wing (24) and rear wing (22) are joined at the wingtips with a wing tip pivot pin (42) and folded laterally along the hardback (10) for storage. A motor (40) is mounted within the hardback (10) and connected to the driveshafts (28) in a manner to cause the carriages (26) to move fore and aft.

Abstract: An improved wing fold assembly for use in aircraft which provides relative rotational movement of a first wing tip about a second fixed wing including a plurality of wing tip flanges, and a plurality of fixed wing flanges wherein all of said flanges are rotatably mounted to a central shaft and wherein the improvement comprises means for selectively interlocking said wing tip flanges in relation to said fixed wing flanges to thereby lock said wing tip in position relative said fixed wing in either of a folded or faired position.

Abstract: A canard wing surface for aircraft, especially supersonic aircraft, which can be lowered and retracted flush into the fuselage of the aircraft when no longer needed. The canard is hinged to an extendible platform at or near its upper edge, so that a raising mechanism on the platform can raise the canard from a position integral with the skin of the fuselage to a fully extended position as a curved wing. The platform is extended to allow the canard to clear the fuselage, and may be rotated to adjust the angle of attack of the canard from nearly flat, for the transition to high-speed flight, to a range of low-to-medium angles of attack when used as a lift surface during takeoff and landing, to nearly vertical for use as a speed brake during the landing roll. If desired, multiple canard surfaces can be used on an aircraft, arranged along the fuselage.

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 and deployed in the air.

Abstract: A latch pin actuator (34) for use in connection with an aircraft (10) having folding wings or wing tips (12). The actuator (34) includes housing (38) mountable to a wing portion (12, 16). A latch pin (21) in the form of a hydraulic cylinder is slidably mounted within the housing (38) and on a piston (44) which is fixed to the housing (38). Variable volume fluid chambers (46, 48) are defined in the cylinder body of the latch pin (21). A primary lock member (58) is movable between locked and unlocked positions such that retraction of the latch pin (21) is prevented when the primary lock (58) is in a locked position. In preferred form, a hydraulic actuator (78) is used to move the primary lock member (58) between locked and unlocked positions and to operate a sequencing valve which delivers hydraulic pressure to a chamber (48) of the latch pin (21) after actuation of the primary lock (58).

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: Aerodynamic control apparatus for an aircraft is provided which includes a pair of control surfaces, one for each side of the aircraft, each control surface extending between a root end at the fuselage and a distant tip end. The root end of each control surface is pivotally mounted on the fuselage on a stationary hinge axis which is angularly disposed relative to the longitudinal axis of the aircraft. The hinge axis is elevated or depressed at the leading edge of the control surface relative to the trailing edge such that the hinge axis is in an oblique orientation relative to the longitudinal axis of the aircraft. An actuator enables selective movement of each control surface to any one of a range of positions between an inactive position flush with a contoured outer surface of the fuselage and a deployed position at which a tip end of the control surface is distant from the fuselage.

Abstract: A plurality of latch pins are locked into a latch position by primary locks and secondary locks. Each primary lock mechanically blocks movement of its corresponding secondary lock into the secondary lock's locked position when the primary lock is out of its locked position. The secondary locks are ganged together to cause them to move together into and out from their locked positions. A follow-up switch senses movement of the ganging mechanism. A latch pin inhibitor blocks movement of the latch pin into the latch position and is moved away to permit latching by spreading of the wing tip. The inhibitor is linked to a valve to shift the valve and thereby cause hydraulic pressure to be supplied to extend the latch pin. When the locks are in their looked positions, the secondary locks mechanically block the primary locks from moving out of their locked positions. The secondary locks are biased into their locked positions. During flight, the latch pins and locks are isolated from hydraulic pressure.

Abstract: A plurality of radially extendable/retractable lock bolts (LB) are carried by a piston head (PH). A cylinder body (CB) in which the piston head (PH) is located includes a lock-bolt cavity (52) or cavities. When the actuator is in a lock position (fully extended or fully retracted), the lock bolt or bolts (LB) are in radial alignment with the lock bolt cavity or cavities. A locking piston (LP) within the actuator is movable axially to place a bolt block (62) radially inwardly of the lock bolt or bolts (LB), to in such position block the lock bolt or bolts (LB) against a radial inward movement out from the lock bolt cavity (52) or cavities. The locking piston (LP) includes a piston face (60) against which hydraulic fluid pressure may be directed, to move the locking piston (LP) axially, for retracting the bolt block (62) out from its position radially inwardly of the lock bolt or bolts (LB).

Abstract: A folding wing assembly for use on an aircraft is disclosed. The folding wing assembly includes inboard and outboard wing sections which are pivotally interconnected such that the outboard wing section may pivot between folded and unfolded positions. A fairing unit is further pivotally interconnected to both the wing sections and extends chordwise across the wing assembly. The fairing unit is provided with a seal extending chordwise across an inner spanwise end of the fairing. The seat is adapted to engage the underside of a sealing flange attached to the upper surface of the inboard wing section. The other spanwise end of the fairing is adapted to engage a seal carried by the outboard wing section when the outboard wing section is in its fully unfolded position.

Abstract: A foldable, multisectional air foil with apparatus enabling it to fold or curl up or down about the body of a craft; and to a system to maintain air foil rigidity during flight. This system includes three separate assemblages which may be used in combination: sliding spar, continuous strap and cable pressure. The former includes apparatus for a sliding segmented spar within a segmented spar built into the air foil sections, which allows the air foil to fold when the joints of both spars are aligned yet provides sufficient rigidity when said joints are offset. The continuous strap assemblage provides for the air foil to be encircled by continuous yet segmented straps, each section of which contains hinging and locking mechanisms allowing the air foil sections to fold and unfold yet which--when locked into place as a continuous strap--provide structural strength to the air foil whole.

Abstract: A folding wing tip (14) on an aircraft (2) carries a lug (16) that moves into alignment with lugs (6, 10) on the inboard wing portion (4) as the wings spread. The lug (16) pivots an inhibitor (28) that is interconnected by linkage to a valve spool (122). The pivoting of the inhibitor (28) causes the spool (122) to shift its position so that a sense port is brought into communication with a return port. Return pressure in the sense port indicates a spread wing condition. When the wing tip (14) is folded, springs move the inhibitor (28) and the valve spool (122) back to their original positions. This communicates the sense port with a pressure port to indicate a folded wing condition. The spool (122) is preferably also biased into its original position by fluid pressure. In addition, the lug (16) has a cam (92) that engages a roller (84) carried by the inhibitor (28) when the wing tip (14) is moved into a folded position.

Abstract: An aircraft wing pivot structure is described which provides a flexible ring attached to the aircraft wing at flexible wing attachment points by spherical bearings. The ring is attached to the fuselage of the aircraft by pins fixed to the fuselage and fittings partially enclosing sliding shoes formed at the bottom edge of the ring to allow rotation of the wing. The wing is locked in the flight position by retractable pins connected to the primary fuselage attachment fittings. The ring is a unitary stainless structure which accepts wing strains induced by flight loads by flexing at the wing attachment points. The use of a flexible ring eliminates truss-like members mounted on spherical bearings used in conventional designs. The elimination of a substantial number of components by the use of a flexible ring substantially reduces the weight of the aircraft and improves the reliability.

Abstract: A device, particularly a missile, includes a body having an appendage, e.g., a wing, normally folded in an inoperative position and to be unfolded to an operative position when the body is accelerated in the direction of the longitudinal axis of the body. The appendage is pivotally mounted about a first pivot axis extending perpendicularly to the longitudinal axis of the body, and also about a second pivot axis extending parallel to the longitudinal axis of the body. The center of gravity of the appendage is outwardly of the first pivot axis in the folded condition of the appendage such that the acceleration of the body produces a moment pivotting the appendage about the first pivot axis.

Abstract: An articulated wing has a fore wing portion and after wing portion connected to an articulate axis support structure which extends along the length of the wing and separates the two wing portions. Control actuators separately connect the fore and after wing portions to the articulate wing support structure in order to provide separate angular positioning capabilities for the two wing portions. Further, the articulate wing support structure itself may be rotated with respect to the mechanism it is attached to. These and other flexible controls over the wing attitude and size allow the wing to provide a number of force vector amplitudes as well as directions for any given fluid flow direction and velocity.

Abstract: A segmented variable sweep wing for an aircraft has a plurality of wing segments. A structural device movably affixes the wing segments to the fuselage of the aircraft adjacent each other at their root areas. The structural device moves the segments conjointly to a power position where the segments are perpendicular to the fuselage and spaced from each other. The structural device also moves the segments conjointly to a cruise position wherein the segments are swept back at an angle with the fuselage and in abutment with each other thereby forming a unitary continuous surface airfoil.

Abstract: An improved actuator system is provided for safe displacement of a folding wing section of an aircraft between a folded storage position and a deployed position for normal flight operations. The actuator system comprises an electrohydraulic actuator forming part of a mechanical linkage between an outboard folding wing section and an adjacent inboard wing section. The electrohydraulic actuator is adapted to be reversibly driven either electrically or hydraulically to displace the outboard wing section, and includes an improved brake unit for automatically retaining the outboard wing section in place upon interruption of drive power input to the actuator. The actuator system further includes an improved latch pin unit adapted for electric or hydraulic powered operation to positively lock the outboard wing section in the deployed position.

Abstract: An on-demand wing vortex control system includes a pair of retractable pas which extend forward through slots in the leading edges of the strake and main wing at their junction. When not in use, the device is retracted in a stowed position, thus having zero impact on the cruise efficiency and observability characteristics designed into the aircraft. The panels extend forward from the strake and wing, providing an added leading edge airfoil surface when in the deployed position. Both panels are slideably and rotatably affixed to the aircraft. A front panel is affixed to and supported within the strake, while a rear panel is affixed and supported within the main wing. The planform of each panel is symmetrically identical, and the movements of the panels are mechanically coordinated so that the exposed planform shape represented by the combined overlapping panels are symmetrical about a line which bisects the strake/wing junction angle.

Abstract: A folding wing structure for improved missile aerodynamic performance and manuverability with a minimum payload space requirement which comprises a leading edge spar and at least one trailing edge spar spaced apart from each other by a plurality of transverse ribs, the spars being approximately parallel to each other with the ribs positioned along the spars to divide the structure into a series of parallelograms. The spars and ribs are pivotally joined together with the spars being further pivotally joined to an air frame of an aerodynamic vehicle or missile. In a folded position the spars and rib structure collapse to occupy a minimal amount of volume in a recessed area of the air frame. A spring or piston member secured to at least one, spar forces the spars apart and out from the fuselage to an erected wing position at predetermined sweep angles relative to the fuselage.

Abstract: An airborne body possessing stabilizing fins or control surfaces, wherein each stabilizing fin is displaceable about an associated bearing axle between a retracted inoperative position and a position of flight in which it is unfolded from the airborne body. An arrangement is associated with each stabilizing fin or control surface, which arrangement is provided for the damping or cushioning of the extending movement of the respective stabilizing fin from the inoperative position into the flying position and for the latching of the stabilizing fin in the flying position, while inhibiting and rebounding of the fin.

Abstract: A deflated airbag is located on the outside of a missile or other vehicle beneath a folded, pivotally mounted airfoil member prior to launch, and a supply of pressurized gas is connected to the interior of the airbag via a suitable valve. After launch, or after lowering of a launch platform in the case of launch from an aircraft, an actuator such as an acceleration sensing device or timing device opens the valve, supplying gas to inflate the bag and simultaneously urge the airfoil into an extended, working position. After the airfoil is locked in its extended position, the airbag rapidly deflates and may be dropped off or retracted. Where more than one airfoil is to be deployed, separate airbags are located beneath each of the folded airfoils and a common gas supply is connected to all of the airbags.

Abstract: A latch pin and locking system for use in connection with an aircraft having folding wings or wing tips. The system includes a plurality of individual latch pin units, each of which has a pin that is hydraulically driven in extension and retraction. When extended, the pins cooperatively lock wing tip hinge structure which prevents wing tip folding movement. Each latch pin unit has a locking body that prevents pin retraction of its respective pin after extension thereof for wing tip locking. The locking bodies of all of the latch pin units are drivingly interlinked, so that all lock and/or unlock as a single network. The network is driven by a single power drive unit. In the event any one locking body in the network fails, the network is broken, and thereby provides an indication that maintenance is required.

Abstract: A twist canister for conducting conduits between two members rotatable with respect to each other through a predetermined angle about an axis. The conduits are pre-flexed an angular amount equal to one half of the predetermined angle when the members are at the extreme of the rotational angle with respect to each other. The conduits are flexed only one half of the predetermined angle during rotation of the members through the total predetermined angle. The conduits are placed generally in a plane parallel to the axis to minimize the space required for the canister.

Abstract: This invention involves a simple but radical approach to airplane design. Many advantages and benefits result therefrom including improved flight efficiency, better handling and control response, less tail area required, increased safety, increased utility of airplanes, and reduced ground handling and hangar facility requirements. A solution is provided for the inherent problems of combining the utility of a surface conveyance with the freedom and swiftness of flight.

Abstract: A double-pivoting deployment system for aerosurfaces, such as wings or fins, for use on aerospace vehicles. Each aerosurface has an inner segment and an outer segment. The inner segment is pivotally connected at a first axis of rotation to the support structure of the aerospace vehicle. An outer side portion of the inner segment is pivotally connected at a second axis of rotation to an inner side portion of the outer segment. In operation, the outer segment is stowed adjacent to the body of the aerospace vehicle such that the surface plane of the outer segment is longitudinally aligned with the longitudinal axis of the aerospace vehicle, and the aerosurface span is longitudinally aligned with, the longitudinal axis of the aerospace vehicle. From the stowed position, the outer segment is first rotated substantially 90.degree.

Abstract: A wing which is extendable from an airborne body. The wing includes a base spar which is actuatable through the operation of a power element, a nose spar which has one of the end sections thereof supported for pivotal movement about a bearing axis located on the airborne body and at least one lamella or sheet metal element which extends at least approximately in parallel with the nose spar in every angular position thereof, which has one end section thereof pivotably supported on the base spar by means of a lamella axis. A stabilizing element is supported for pivoting about a connecting axis at the second end section of the nose spar which is distant from the first end section, and extends through contact or positioning elements at the second end section of the at least one lamella element distant from the associated lamella axis.

Abstract: A Variable Geometry Remotely Piloted Vehicle (VG-RPV) has a main fuselage portion supporting at one end main wing panels and a forward fuselage portion. In the stowed position, the main wings and forward fuselage portion are laterally adjacent the main fuselage. This provides compact volume of small dimensions for stowage inside a canister. When deployed for flight, the wings are inclined at a large angle to the main fuselage, and a fuselage forebody is positioned upstream of the main fuselage, to establish a vehicle center of gravity adjacent to the deployed wings. Folding panels are mounted on chordwise hinges at the tip of the main wing panels. These panels overlap the main wing panels in the stowed configuration, inside the canister or on deck, and extend the span and area of the deployed main panels in the flight configuration. In-flight deployment is provided to launch the VG-RPV with a reduced span and area with the folding panels placed under the main panels.

Abstract: An aircraft including a fuselage and a double wing unit which is pivotably mounted onto the fuselage and arranged to selectably assume a first orientation, generally parallel to the fuselage, during storage and transport and a second orientation, generally perpendicular to the fuselage, for flight.

Abstract: An apparatus and method for increasing the angle of attack operating range of an aircraft is disclosed. The invention comprises a pair of substantially vertical tip fins. Each vertical tip fin has a main portion and an aft portion. The main portion is securely connected to the tip of the airplane wing and has a swept back leading edge. The aft portion comprises a substantially vertical aileron hingedly connected to the main portion of the tip fin for controlling the roll of the aircraft at high angles of attack. A hinge line is formed at the hinged connection which is swept back. The sweeping back of the leading edge and the hinge line is such that at high angles of attack the oncoming airflow becomes nearly perpendicular to the leading edge and the hinge line, thereby increasing the perforamnce of the vertical tip fin when deflected.

Abstract: A vehicle chassis is supported on front and rear wheels for road and runway engagement. A propeller assembly is disposed between the front and rear wheels and faces the rear. Wing assemblies on opposite sides of the chassis are foldable along the sides of the chassis to form side panels for the road form of the vehicle. A tail assembly on the chassis is shiftable forwardly and rearwardly and has a pair of vertical stabilizers connected together at the top by a horizontal laterally extending stabilizer. A pressure regulated retractable stabilizing wheel is provided between the front and rear wheels and is arranged to engage a runway and provide stabilizing functions for take off and landing.

Abstract: A mechanism (10) for limiting rotation of a rotatably mounted first shaft (12) in accordance with the invention includes a housing (28) in which the first shaft is rotatably supported; a torque input (14) coupled to the first shaft; and a torque output (18) coupled to the first shaft; a second shaft (30) rotatably supported by the housing and movable between a first axial position in which the second shaft does not engage the first shaft and a second axial position in which the second shaft engages the first shaft; at least one member (32) attached to the second shaft which projects radially from the second shaft; and the housing having an inner cavity (42) with at least one surface (70) which engages the at least one member which projects radially at first and second angular positions of the shafts to provide for a limited degree of angular rotation of the shafts when the second shaft is in the second axial position.

Abstract: An unfoldable wing which is extendable from an airborne body, wherein the wing includes a nose spar which has one end segment thereof pivotable about a bearing axis which is located on the airborne body, and a motive arrangement equipped with an energy accumulator or storage for effectuating the extension of the nose spar about the associated bearing axis. On the airborne body there is provided a base spar having a first end segment in proximity to the bearing axis for the nose spar, and with the base spar being oriented at least approximately parallel with the longitudinal axis of the airborne body, whereby the base spar is displaceable along its longitudinal direction and is operatively connectable or, essentially, operatively connected with the energy accumulator and with the nose spar for effectuating the extension of the nose spar.

Abstract: An alignment mechanism for independently adjusting the deployable aerosurfaces of an aerospace vehicle in both the stowed and deployed positions. The alignment mechanism includes a guide means having a slot with both a constant width portion and a variable width portion. A slide, interconnected to the deployable aerosurfaces, is pivotally engaged to the guide means so that it travels along the length of the slot. The slide is capable of pivotal movement when the slide is engaged in the slot's variable width portion and incapable of pivotal movement when it is engaged in the slot's constant width portion. An actuator is employed to selectively position the slide along the slot.

Abstract: A two-stage earth-to-orbit transport includes an orbiter vehicle and a pair of boosters, each having a depolyable oblique wing located along a longitudinal axis of the booster. The wing is deployed in an oblique disposition in supersonic and hypersonic speeds, and disposed at 90.degree. for subsonic speeds encountered during entry. The oblique wing is driven axially and rotated by means of a turret mounted on rails.

Abstract: A decoy aircraft construction of compact format during transport and able to form a decoy model of an aircraft on disposition on an airfield has the form of a rectilinear box blank having six primary panels joined at edges so as to form a box on bringing together free edges thereof. The panels have hinged to each of one or more thereof a single secondary panel or a secondary panel complex formed in turn of a plurality of panels hinged together. No secondary panel or secondary panel complex of the construction when folded at its hinges has overall dimensions greater than those of the primary panels. The location and shape of the secondary panel(s) and secondary panel complex(es) are such that on dismantling to a flat format, the primary panels of the box with the secondary panel(s) and secondary panel complex(es) housed therein, the secondary panel(s) and secondary panel complex(es) augment the flat format by unfolding to impart to it a three dimensional shape simulating that of an aircraft construction.

Abstract: A projectile, an airborne body or a missile, such as an article of ammunition, having extendable wings, whereby a wing covering is provided to extend between a front spar which is extendable through the action of a power element, and a rear spar which is retractable with its outer end against the front spar, as well as providing for a specially adapted power element for this purpose. The power element has one end thereof engaging at the front spar and has its opposite end engaging against a slider which is latched to the projectile so as to be supported thereon for displacement along the longitudinal direction, and wherein the rear spar has its inner end pivotable in front of the slider in the direction of displacement thereof, and upon the slider being unlatched, is pivotable further by the slider under the action of the power element for effectuating the tensioning of the wing covering.

Abstract: A vehicle usable in the air, on water, or on ground is described. Outer wing portions are connected to a central portion by a mechanism which allows the outer wing portions to pivot about first axes for placing the outer wing portions in stored positions. The outer wing portions are also rotatable about a second axis for placing them in positions whereby they are useful as sails for driving the vehicle without the use of an engine. The wheels are capable of being pivoted to non-positions.

Abstract: A rocket-powered, air-deployed, lift-assisted booster vehicle (ALBV) is disclosed for efficiently carrying small payloads to orbital, supraorbital or suborbital altitudes and velocities. The ALBV is secured beneath a conventional carrier aircraft and dropped therefrom at launch altitude and velocity, which contributes significant total energy to the ALBV's ascent trajectory. The ALBV has wings, which generate aerodynamic lift to assist in vehicle ascent, and tail fins, which perform attitude control while the vehicle is in the sensible atmosphere. After drop launch, an innovative "vertical-S" maneuver is performed using aerodynamic control, causing the ALBV to ascend on a near-theoretical optimal trajectory. In the preferred embodiment, the wings and tail fins are jettisoned as the vehicle exits the sensible atmosphere and aerodynamic lift ceases.

Abstract: A convertible airplane to automobile and visa versa, having a fuselage and three wings, including a forward canard wing, a foldable main wing and a secondary lift wing. The foldable wing is capable of folding to a size for safely driving the automobile on a roadway. All wings are used as ground effect airfoils for roadway use.

Abstract: A flying body for subordinate-ammunition missile with extendable glide wings. The flying body or missile of the above-mentioned type has the wings pivotally retained in attachments which are arranged generally in parallel with the longitudinal axis of the missile on the casing of the fuselage of the missile, and which are equipped with longitudinal grooves each respectively stowing a retracted wing.

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 positional 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 cavity in an airframe from which an airfoil is deployed is automatically closed to reduce aerodynamic drag by a fairing element hinged to the force and aft cavity edges and resiliently deformable from an unbent aerodynamic position outside the cavity to a bent position within the cavity. The non-deployed airfoil overlies the bent fairing element and retains the fairing in a bent position against the resilient force tending to restore it to the unbent position, until airfoil deployment.

Abstract: A control surface deployment mechanism allows reliable, controlled launch of guided missiles from internal bays of high performance aircraft.

Abstract: A telescopic airfoil comprising a plurality of short wing sections, each consisting of skin and rib, with tubular spar sections attached to the rib. Each spar section is adapted to telescope with respect to the next adjoining spar section toward the root end of the airfoil. Alternate spar sections are rotatable, and intermediate spar sections are held stationary, with the end portions of adjacent spar sections overlapping, and low-friction threads connecting the overlapping spar portions. The threads at opposite ends of each spar section are of opposite hand so that rotation of the rotatable spar sections causes the entire group to be drawn together into a housing at the root end of the wing. In this way, the wing span can be reduced to less than 30% of the full span, while during extension and retraction, the spars retain their full load-carrying capability.

Abstract: A flying emergency ejection seat for endangered airman to escape from distressed aircraft and to fly cross country in the seat to sanctuary of a more favorable environment for recovery having the following existing state-of-the-art non-flying seat survival features of an airman's ejection seat including: a parachute, a rocket/catapult propelled escape seat for ejection, a survival kit for air, land, and water survival equipment, guidance controls on the escape seat and mating guides in the aircraft to direct the path of the seat ejection from the aircraft, seat/man separation device, and added on design features of this invention to make it a flying seat:shall include add-on folding wings for extension in flight to sustain the seat in flight, add-on extendable empennage for extension during ejection to stabilize and guide the direction of flight of the seat in a prone attitude, add-on actuators on the seat bucket to stretch out the airman into a physical prone head down, face forward configuration for minimum