Abstract: An aircraft or spacecraft is landed with the aid of a paraglider type parachute and with a braking booster rocket which emits its jet in the landing direction. The glide number of the paraglider is selected to provide the craft for the landing with an extremely "inefficient" glide number so that the ratio of drag to lift is about 1. Thus, the total drag of the combination paraglider and craft corresponds about to the maximum forward thrust of the craft, whereby a pinpoint landing may be accomplished.

Abstract: The present variable airfoil assembly has a fixed airfoil member with a shallow recess in the top in which an adjustable airfoil member is seated snugly, when lowered, to present a convex top surface which merges smoothly with the top surface on the fixed airfoil member in front and behind. When the adjustable airfoil member is raised, the fixed airfoil member presents a top surface below it which is continuous for most of its extent to minimize air turbulence. Reinforcing ribs on the adjustable airfoil member extend down through longitudinal gaps in the top of the fixed airfoil member and are coupled to cylinder-and-piston units for raising and lowering the adjustable airfoil member. A transverse gap extending across the top of the nose of the fixed airfoil member passes adjustable filler pieces which can extend up between the nose and the front edge of the adjustable airfoil member when the latter is raised or be retracted down to permit air to flow under the adjustable airfoil member for braking purposes.

Abstract: The invention relates to a thrust reverser for the jet engine of an aircraft. According to the invention, the unlocking of the doors with a view to passage from their folded position to their extended position, is effective only after they have been previously brought into a super-retracted position with respect to the folded position and said reverser comprises stops which allow the doors to pass from the folded position to the super-retracted position only when the rpm of said engine is lower than a threshold close to idling rpm. The invention is particularly applicable to ensuring operational safety of thrust reversers.

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

Abstract: This invention generally concerns an aircraft useful for training pilots, and specifically involves providing a trainer aircraft having high to moderate aspect ratio wings with selectively operable design features that impart to the trainer aircraft the handling characteristics of a high performance, swept wing aircraft in an approach and landing configuration. In particular, the high performance swept wing aircraft characteristics are preferably imparted by selectively actuated primary and secondary speed brake mechanisms. Optimally, the primary speed brake mechanism is positioned as a function of angle of attack of the aircraft.

Abstract: A seal assembly for sealing a variable gap between the surface of a first element and a second element movable relative thereto. A seal may comprise a seal housing attached to the second element for movement therewith and having a sealing surface thereon and at least one elongated seal member carried by the housing having first and second conjugate sealing surfaces thereon, the first sealing surface for rubbing and sealing engagement with the first element surface and the second sealing surface for sliding and sealing engagement with the housing sealing surface. A biasing assembly may be carried by the housing for biasing the first and second conjugate sealing surfaces of the sealing member toward sealing engagement with the first element surface and housing sealing surface, respectively.

Abstract: A rotary wing aircraft is provided with at least one pair of vane members mounted on opposite sides of the body thereof. Each vane member includes a substantially planar flared section and a mounting section; each of such vane member mounting sections being positioned alongside such aircraft body and being rotatable about a substantially horizontal common axis passing therethrough. Such vane member flared sections extend in planes which obliquely intersect such common axis. Such vane members are selectively counter-rotatable to move such flared sections thereof into and out of alignment with the airstream moving rearwardly alongside the body of such aircraft as the same moves forwardly through the air to concurrently serve steering and banking functions and are further rotatable in unison to serve a pitching function.

Abstract: The present invention relates to a speed retarding mechanism for aerial bs launched from a high velocity vehicle and designed to provide a high drag stabilizer capable to withstand release in air stream velocities moving at 2600 feet per second. The mechanism includes a balloon consisting of a top and bottom panel joined on the perimeters and having valve openings through its bottom panel. When the load has been braked to an acceptable velocity the valve closes the openings causing the balloon to collapse and become a streamer providing a high energy impact.

Abstract: A disintegratable aerodynamic brake is disclosed for use on a re-entry vehicle for retarding vehicle speed upon re-entry. The brake is connected to the travelling vehicle and is fabricated from a refractory material and is configured to progressively fuse and disintegrate as it becomes heated by friction as the vehicle encounters increasing atmospheric resistance upon reentry thereinto, so as to retard vehicle speed.

Abstract: The present variable airfoil assembly has an adjustable airfoil member pivotally mounted in the top of a fixed airfoil member for adjustment between a fully lowered position (for minimum wind resistance) and different raised positions in which it projects up above the top surface of the fixed airfoil member to control the lift and drag. A minimum clearance between the fixed and adjustable airfoil members is provided at the front end of the adjustable airfoil member over a range of its pivotal adjustments. The variable airfoil assembly is capable of increasing the lift of the airfoil, then lowering stalling speed, and it may either replace flaps or be used in conjunction with flaps. Higher cruise speeds can be achieved as well as good low speed performance.

Abstract: A combination air brake and engine shield for a jet powered aircraft. A hydraulically operated, hinged shield member, shaped so as to conform to the surface of the aircraft fuselage when in its retracted position, may be swung outwardly therefrom so as to be disposed in front of the air intake of the jet engine powering the craft, to thereby divert any foreign objects from being drawn into the intake and damaging the engine. The same arrangement may also serve as an air brake to effect deceleration of the aircraft. Spring loaded louvers are provided in the shield to permit sufficient air to reach the engine such that problems due to cavitation are avoided.

Abstract: A brake device for retarding linear and rotative movement of a load carrying unit after ejection from an in-flight projectile, wherein a container encloses the unit and includes a plurality of slits which divide the container into sections. Each section includes a concave end portion which pivots into a position for retarding movement of the unit responsive to movement of the container through the atmosphere.

Abstract: An aircraft which produces a free vortex to provide the lift for takeoff and landing procedures has a single centrally mounted engine which supplies both the forward thrust to the aircraft and the spaced pumping action for strengthening and maintaining the free vortex. A shield on the aircraft causes the shedding of vorticity into a cavity-like region behind the shield. A vortex guiding duct extends transversely beneath the aircraft frame and has a pair of inlet openings at the ends of the cavity region. A thruster duct extends longitudinally centrally of the frame and communicates with the vortex duct. An engine is mounted in the thruster duct and supplies forward thrust for the aircraft while simultaneously pumping air from the ends of the cavity region through the vortex duct. This pumping action retains, augments and concentrates the vorticity and results in the formation of a generally circularly-shaped free vortex stretching transversely across the cavity region and through the vortex duct.

Abstract: An electrical system for actuating the inboard spoilers on the wings of an aircraft in response to the lateral control input from the pilot control wheel and to the position of the pilot speed brake lever. The pilot speed brake lever position signal being used to select the modulation provided by a three mode function generator which generates the signal that actuates the spoilers.

Abstract: A method of effecting recovery of a high speed aircraft from a condition of incipient or developed spin involves, upon entry into the condition, deploying at least one parachute coupled only to the forebody of the aircraft forward of the center of gravity, and is particularly effective in recovering from a flat spin. After recovery, the chute or chutes can be collapsed, released or retracted. The chute is deployed in response to predetermined angle of attack and yaw rate of the aircraft, which may be accomplished automatically under the control of spin condition sensing means. The chute is highly effective because of its location, and hence may be relatively small, the size of the chute, when deployed being such as to have a negligible influence on the free falling rate of sink of the aircraft.

Abstract: The present apparatus controls the position of the brake flap or air brake of an aircraft. The air brake is operated by a power amplifier including a pressure cylinder and a piston. The piston is mechanically coupled to the brake flap or air brake in such a manner that the displacement of the brake flap is about proportional to the brake flap angle. The pressure in the cylinder is controlled in response to or as a function of the brake flap angle so that the flap is positioned at the angle required for the particular braking action, whereby the force caused by the dynamic or impact pressure is maintained in equilibrium with the force exerted by the pressure piston cylinder arrangement.

Abstract: An improvement to the controllability of aircraft wherein vortex generators are connected to a control surface in front of the hinge line of the control surface so that when the control surface is deflected, the vortex generators project into the airstream on the opposite side from the deflecting control surface. The action of the vortex generators causes the airflow to remain attached to the control surface at higher angles of attack than would otherwise be possible thus increasing the lift of the airfoil and control surface.

Abstract: An aircraft spoiler system consisting of semi-circular rods disposed within the leading edge of an aircraft wing and rotatably carried thereby so that in the inactive position the substantially flat surfaces are flush with the wing surface and in its most active position the flat surfaces are at right angles to the wing surface with approximately half of the rods extending above the wing surface, acting in a manner to eliminate the lift of the wing, i.e., as spoilers. The rods are controlled by a pair of magnetic clutches which connect the spoiler rods to a rotary solenoid when a toggle switch is thrown by the pilot. The spoilers have mechanical spring returns which automatically retract them when the switch is in its "off" position or in the event of a power failure. A retro-fit mounting is provided for fitting the spoilers on existing wing section.

Abstract: An aircraft wing having a relatively thin airfoil cross section including a main body portion and a plurality of auxiliary airfoil sections disposed at the trailing edge of the wing and movable relative to the main body portion and to one another. In a normal cruise position the auxiliary sections and the main body portion form a complete airfoil having a substantially contiguous and unbroken exterior airfoil surface which preserves the high speed characteristics of the wing. At least two of the auxiliary sections comprising a leading auxiliary section and a trailing auxiliary section are movable about a common hinge member carried by the main body portion, while another auxiliary section also hingedly connected to the main body portion is positioned relative thereto in response to the position of the other auxiliary sections.

Abstract: A fixed wing is provided and includes an upwardly opening recess formed therein and extending along the trailing marginal edge portions of the wing. A flap is provided and mounted from the wing for shifting relative thereto between a first lower retracted limit position at least substantially fully received in the recess, and an elevated position displaced upwardly above the upper surface of the wing with the flap disposed at an angle of attack greater than the angle of attack of the wing.

Abstract: In a VTOL, aircraft having pairs of angularly movable jet-engine-efflux discharging vectored thrust lift and propulsion nozzles at the under side of the fuselage, a deflector door is provided to divert the hot exhaust gases that rise toward the fuselage when the aircraft is near the ground and thereby prevent such gases from approaching the engine air intakes. The deflector door swings from a retracted position to a position in which it projects downwardly and forwardly below the fuselage and it has edge blowing slots through which bleed air from the engine is blown in a downward and forward direction with a lateral fan-wise spread. This door also serves duty as an airbrake.

Abstract: An aircraft having a composite configuration comprising a conventional fuselage forebody portion which symmetrically and variformly blends into a relatively wide, substantially flat beaver-tail-like afterbody, with said afterbody having an integral pitch trimming camber and a composite pitch control device and air brake, hinged transversely thereacross and forming at least a part of its trailing edge. A pair of upper and lower airbrake panels are fitted flat-like against the upper and lower surfaces of the pitch control device. The airbrake panels are provided with control linkage which permits the panels to move parallel to the surfaces and be angularly displace relative thereto.

Abstract: A wedge-shaped, high speed airfoil having a variable geometry configuration consisting of separate, upper and lower airfoil surfaces individually and/or collectively adjustable between inner, retracted and outer, extended positions to vary the amount of airfoil surface area exposed to the free stream flow to that required for effective aircraft stabilization and/or control at selected Mach numbers while minimizing the drag and aerodynamic heating normally resulting therefrom.

Abstract: A means for attenuating the vortex created at aircraft wingtips which consists of a retractable planar surface transverse to the airstream and attached downstream of the wingtip which creates a positive pressure gradient just downstream from the wing. The positive pressure forces a break up of the rotational air flow of the vortex.

Abstract: An aircraft having a composite configuration comprising a conventional fuselage forebody portion which symmetrically and variformly blends into a relatively wide, substantially flat beaver-tail-like afterbody, with the afterbody having an integral pitch trimming camber and a composite pitch control device and air brake, hinged transversely thereacross and forming at least a part of its trailing edge. The beaver-tail afterbody is geometrically blended into and joined with the after portion of the conventional forebody through the medium of an intervening medial body defined by a geometric transition piece. The composite aircraft is further capable of fixedly accommodating any type of conventional wing configuration without the necessity for any adaptative, structural change or modification and also carries conventional propulsion units and control surface components.