36 results about "Swept wing" patented technology

A computer implemented method, apparatus, and computer usable program product for symmetric and anti-symmetric control of aircraft flight control surfaces to reduce wing-body loads. Commands are sent to symmetrically deploy outboard control surfaces to shift wing air-loads inboard based on airplane state and speed brake deployment. Surface rate retraction on a wing with peak loads is limited to reduce maximum loads due to wheel checkback accompanied by utilization of opposite wing control surfaces to retain roll characteristics. Airloads are shifted inboard on a swept wing to move the center of pressure forward, thereby reducing the tail load required to perform a positive gravity maneuver. In a negative gravity maneuver, speed brakes are retracted, thereby reducing the positive tail load and reducing the aft body design loads. High gain feedback commands are filtered from wing structural modes above one hertz by a set of linear and non-linear filters.

The invention discloses a tilt-rotor based on combination of four rotor wings and a fixed wing. The tilt-rotor is structurally characterized in that a first rotor wing, a second rotor wing, a third rotor wing and a fourth rotor wing are divided into two groups which are respectively symmetrically mounted on the two sides of a tilt-rotor body by two shafts; (1, 2) is a front motor group; (3, 4) is a rear motor group; a middle wing is horizontally mounted on the tilt-rotor body and is vertical to the tilt-rotor body; backswept wings on the two sides are respectively mounted on the two sides of the middle horizontal wing at a backswept angle of 50 degrees. According to the tilt-rotor disclosed by the invention, the four rotor wings and the fixed wing are enabled to share a set of power system to realize vertical takeoff and landing, hovering and cruise level flying; the front and rear tilting motor groups (1, 2) and (3, 4) share a set of tilting device to realize synchronous tilting by a tilting drive shaft, thereby simplifying a tilting structure and improving the operability and stability of the tilt-rotor.

A VTOL aircraft, preferably of the swept wing design. An arrangement of propellors and motors are individually housed within ducts which are mounted within a wing. Each individual motor support arm will run from the motor it is supporting, through the duct wall and into the wing and will be attached to a central frame structure housed in the fuselage. Covers are provided over the ducts, operable by motor means such as a servo. When the aircraft is relying on the internally housed propellors to provide lift, the covers will be open to allow air to pass through the ducts. When the aircraft is relying on airflow over the wings to provide lift these covers can be closed to provide uninterrupted airflow over the wings. The covers are designed to match the surface contour of the wing when closed.

An aircraft for transporting passengers and cargo able to efficiently handle ground operations for loading / unloading cargo and embarking / disembarking passengers at the same time. The lifting structure of the aircraft is formed by a back-swept wing and a fore-plane, the back-swept wing including winglets having a length L allowing them to act as vertical stabilizers. The propulsion system is mounted aft of the center of gravity of the aircraft and the tailcone of the fuselage is configured to act as a rear access door and as a pressure barrier.

A high performance (high L / D ratio) launch vehicle is tuned for passive or limited control re-entry. In one embodiment, the re-entry vehicle (100) includes a fuselage portion (102) and wing portions (104 and 106) extending from opposite sides thereof. Various vehicle configuration parameters are tuned to allow for passive or limited control re-entry. In particular, the swept wings have a dihedral configuration and the nose of the vehicle (100) is widened. In operation, the vehicle (100) penetrates the outer atmosphere at a high angle of attack and transitions to an aerodynamic angle of attack for substantial cross range and down range control within the lower atmosphere. The vehicle (100) thereby provides for enhanced re-entry safety while reducing propellant requirements, reducing loads and meeting human rating requirements.

The invention provides a corporate aircraft engine upper placement and front swept wing duck type layout, which belongs to the aviation field, and relates to a high lift drag ratio airplane total layout scheme. The airplane comprises a fuselage, duck wings, wings, a vertical fin, an engine and a rear body edge strip; the wing leading edge inner segment sweeps back; the wing leading edge outer segment sweeps forward, and the engine is supported on an upper surface of a rear body edge strip between a wing trailing edge and an edge strip rudder by an engine, and in the top view projection, an engine axis crosses the corner of the wing leading edge inner segment and the wing leading edge outer segment, and an elevator is arranged at the wing trailing edge, and an inner side elevating auxiliary wing is arranged at the inner side of the wing trailing edge inner side, and an outside elevating auxiliary wing is arranged at the outer side of the wing trailing edge; an edge strip rudder is arranged at the rear edge of the rear body edge strip, and a rudder is arranged at the rear edge of the vertical fin. The wing trailing edge inner segment is connected with a rear body edge strip; the edge strip rudder at the rear body edge strip trailing edge is in cracking type, and is composed of an upper rudder surface and a lower rudder surface, and the shapes of the fuselage and the wing are in smooth transition. The invention has the advantages of high rising and landing lift coefficient and high trim lift drag ratio, light structure weight, long endurance and long voyage.

The invention relates to the field of unmanned planes, and provides a tilting wing vertical taking off and landing unmanned plane with a modularized power. The tiling wing vertical taking off and landing unmanned plane comprises a main wing tilting system, a horizontal tail tilting system, and a vertical tail; the main wing tilting system comprises main wings and first airscrew power modules, and the horizontal tail tilting system comprises horizontal tails and second airscrew power modules; the main wings and the horizontal tails adopt backswept wing design; the first airscrew power modules and the second airscrew power modules are externally hung on each main wing and each horizontal tail respectively; each main wing corresponds to one or more first airscrew power modules; each horizontal tail corresponds to one second airscrew power module; and each second airscrew power module is foldable. The tilting wing vertical taking off and landing unmanned plane has the beneficial effects that airscrew power adopts modularization design, each main wing can hang two to ten airscrew power modules, and the unmanned plane of taking off weight serialization can be formed; the taking off and landing are vertical, overall arrangement of a fixed wing with high span-chord ratio is achieved, and cruising ability is high; and each main wing and each tail are of backswept wing design, stall can be avoided, and flight is steady.

A computer implemented method, apparatus, and computer usable program product for symmetric and anti-symmetric control of aircraft flight control surfaces to reduce wing-body loads. Commands are sent to symmetrically deploy outboard control surfaces to shift wing air-loads inboard based on airplane state and speed brake deployment. Surface rate retraction on a wing with peak loads is limited to reduce maximum loads due to wheel checkback accompanied by utilization of opposite wing control surfaces to retain roll characteristics. Airloads are shifted inboard on a swept wing to move the center of pressure forward, thereby reducing the tail load required to perform a positive gravity maneuver. In a negative gravity maneuver, speed brakes are retracted, thereby reducing the positive tail load and reducing the aft body design loads. High gain feedback commands are filtered from wing structural modes above one hertz by a set of linear and non-linear filters.

An aircraft is provided that is convertible in flight between a rotary wing configuration and a fixed wing configuration. In its fixed wing configuration the aircraft resembles a Blended Wing Body (BWB) having a swept wing angle β. Conversions from the fixed wing configuration to the rotary wing configuration, and vice versa, are accomplished by flipping an outboard portion of one wing through 180° to reorient the leading edge of the outboard portion by an angle of 2β to establish a reverse sweep. In its rotary configuration, the entire aircraft is rotated.

The invention relates to a novel furrow plow curved surface. The plow curved surface is of a pseudo-spherical shape; a plowshare, a plow breast and a plow wing of the plow curved surface are of a complete curved-surface sheet and have the characteristics of a chiseling plowshare, a convex breast and a swept wing; the plowshare and a plow wall are separately manufactured and are convenient to repair and replace; the resources are saved. According to the novel furrow plow curved surface, the pseudo-spherical surface with a gauss curvature being a negative constant curvature is innovatively used as the plow curved surface; the negative constant curvature K is -1 / 1600; compared with other plow curved surfaces, the plow curved surface is high in smoothness; the plow curved surface has the effect of more effectively turning and breaking the soil; the tillage resistance and the energy consumption are reduced; the problems that the gauss curvature of the current furrow plow curved surface cannot be highly integrated to be the same curvature, the tillage resistance is high, the energy consumption is high and the plow curved surface is high in soil adhesion can be solved; the novel furrow plow curved surface is simple in structure, accurate to manufacture and easy to popularize and use.

The invention relates to the technical field of horizontal tail design of an aircraft, in particular to a horizontal tail of a double-swept back full dynamic deflection aircraft. The horizontal tail comprises a horizontal tail internal side (2), a horizontal tail external side (3) and a rear segment rear sweep angle (4); the horizontal tail is characterized by further comprising a front segment rear sweep wing (1) located at the front part of the horizontal tail and a front segment rear sweep angle (5) formed by the front segment rear sweep wing (1). The horizontal tail provided by the invention can effectively inhibit airflow separation on the main wing surface of the horizontal tail, so that the stalling area of the main wing surface of the horizontal tail is reduced, the pitch control performance of the horizontal tail under large deflection is improved, and the reduction of the design area of the horizontal tail is favored.

An airborne space anti-missile system provides an offensive anti-missile system that provides a supersonic jet flying in space at 10 times the speed of ultra-high speed jet to deliver air-to-surface missiles towards launch site of an attacking missile. The launching missile is targeted prior to launching or during flight. The supersonic jet comprises: a nuclear plasma jet engine operational in thermosphere, and a stamping jet fusion vector engine or anti-material vector engine for flying in lower atmospheres, no vertical tail and rudder, a pointed wing structure; a fuselage having a length of 60 meters and height of 15 meters, a variable swept wing configuration having a 100° range of wing positions, including a forward position where the wing is disposed forwardly, and wingspan is 200 meters from the fuselage, and a full rearward swept position where wingspan is 60 meters from the fuselage; and electromagnetic space for stealth operations.

The invention provides an unmanned aerial vehicle capable of patrolling with long endurance, wide speed range and high mobility. The unmanned aerial vehicle mainly comprises a fuselage, a pair of foldable inner wing sections arranged on the two sides of the fuselage, outer wing sections which are telescopic in the spanwise direction, a pair of foldable upper V-shaped empennages arranged at the tail of the fuselage, and a pair of foldable ventral fins, and a power unit at the tail of the fuselage. The two changeable foldable wings on the two sides of the fuselage can rotate in the planes of thewings according to the use requirements, so as to realize the functions of folding and changing backswept wings; the outer wing sections which are telescopic in the spanwise direction assists in increasing the aspect ratio of the wing; the pair of foldable upper V-shaped empennages at the tail of the fuselage and the pair of foldable ventral fins are used to improve the maneuverability and have low resistance characteristics compared with conventional empennages; and the power unit is mounted at the rear section of the fuselage, and a turbojet power, piston power and turbojet / piston dual power unit can be optionally mounted to enable the unmanned aerial vehicle to fly efficiently and stably. The change of the position of the foldable wings at different speeds, the outer wing sections which are telescopic in the spanwise direction, the foldable upper V-shaped empennages, the foldable ventral fins and the tail power unit of the fuselage jointly improve the adaptability of the unmanned aerial vehicle at different speeds.

The invention relates to the field of aircraft conceptual designs, in particular to a morphing supersonic aircraft. The morphing supersonic aircraft includes a plane body, two wings (1) and an undercarriage. According to the morphing supersonic aircraft, mode translations from a subsonic flight condition to an supersonic flight condition can be achieved through a pre-transformation swept wing mechanism (2), under the conditions of subsonic flight and takeoff and landing, and leading edge high aspect ratio wings are adopted to reduce the induced resistance and increase the subsonic voyage; andunder the supersonic flight condition, tip leading edge low aspect ratio wings are adopted to reduce the wave drag, and the maneuverability can be improved. According to the morphing supersonic aircraft, aircraft can splendidly give consideration to the operating requirements of high speed and low speed, passenger cabins, cargo compartments, fuel tanks and ear compartments are all arranged in twowings (1), obvious plane body does not exist, and the weight of the plane is reduced to some degree.

The invention relates to the field of unmanned aerial vehicles and provides a drum-type storage folding-wing unmanned aerial vehicle. The drum-type storage folding-wing unmanned aerial vehicle comprises a vehicle body, a double-folding vehicle wing, a propeller and a nacelle. The unmanned aerial vehicle adopts tail-pushing design, the propeller is arranged on the tail of the vehicle body, and the nacelle is arranged on the head of the vehicle body. The double-folding vehicle wing adopts sweepback wing design and is in an X shape when being unfolded. The double-folding vehicle wing comprises a first main wing body, a first winglet body, a second main wing body, a second winglet body and two empennage bodies. The first main wing body and the second main wing body are arranged above and below the vehicle body correspondingly and connected with the vehicle body by penetrating through a rotary shaft of the vehicle body. The ends of the first main wing body and the second main wing body are connected with the first winglet body and the second winglet body through connecting shafts correspondingly, and the tails of the first main wing body and the second main wing body are integrally connected with one empennage body correspondingly. The drum-type storage folding-wing unmanned aerial vehicle has the beneficial effects that through design of the double-folding X-shaped wing, space occupied the ratio of the vehicle wing is shrunk to a great extent when the unmanned aerial vehicle is folded, and a larger vehicle wing area is provided after the unmanned aerial vehicle is unfolded; and propeller conducts tail pushing, the nacelle is located on the front portion of the vehicle body, the filling space of the nacelle is increased, and the more convenient and faster effects are achieved.

The invention discloses a variable swept wing fighter plane. The variable swept wing fighter plane comprises a plane body; a radar radome is arranged at the front end of the plane body; an airspeed tube is arranged at the front end of the radar radome; a cockpit is arranged in the part, positioned at the rear end of the radar radome, in the plane body; a dorsal fin is arranged the part, on the rear side of the cockpit, at the top of the plane body; canard wings are arranged in parts, positioned on two sides of the dorsal fin, of side edge positions of the plane body; variable swept wings are arranged on the rear sides of the canard wings; tail wings are arranged on parts, positioned on the rear sides of the variable swept wings, of two sides of the tail part of the plane body; a tail jet is arranged at the tail part, between the two tail wings, of the plane body; a vertical tail is also arranged onthe plane body part between the tail jet and the tail wings; wing roots, leading edge flaps and trailing edge flaps are arranged on the variable swept wings; the leading edge flaps and leading edge slats are connected with each other and are on the same straight line; and spoilers are arranged on the variable swept wings on the internal sides of the trailing edge flaps. The variable swept wing fighter plane has the advantages that the commissioned swept wing fighter plane can enter a swept forward wing during fighting to enhance the near-space fighting capacity of the fighter plane; and moreover, missiles can be launched from multiple angles by using a rotatable telescopic missile pylon so that the fighting capacity of the fighter plane is greatly enhanced.

The invention discloses a sweepback wing type propelling efficiency improving device. The sweepback wing type propelling efficiency improving device comprises a propeller arranged at a stern and a front guide wheel arranged in front of the propeller; the front guide wheel comprises a plurality of sweepback wing type guide vanes and arc-shaped guide pipes installed at the tips of the guide vanes, each guide vane comprises a front wing arranged in the radial direction of a stern shaft of a ship body and connected with the ship body, and a rear wing connected to the upper end of the front wing and inclined backwards. The device is relatively light in structure, convenient to machine and easy to install and position, and can be designed in a targeted mode according to a specific ship type so as to reduce appendage resistance, generate favorable pre-swirling flow, improve a wake field, improve propelling efficiency and achieve the purpose of saving energy.

The invention relates to a sweep wing actuator (10) that has a slide rail (30) in which, in a manner already known, a sliding piece (22) of a sliding arm (20) of the sweep wing actuator (10) is translationally guided and held. Said sliding arm (20) is functionally connected to an output shaft (11) of the sweep wing actuator (10) such that, by means of the sliding piece (22) and the slide rail (30), said sweep wing actuator (10) is able to open and / or close a connected sweep wing (4). According to the invention, there is a sensor (35) in the slide rail (30) that is held in a locationally fixed manner such that said sensor (35) is able to detect the existence of at least one predetermined open state of the connected sweep wing (4).

The portable variable sweepback wing device of the hybrid power underwater vehicle comprises a flow guide body, a connecting assembly used for being connected with the underwater vehicle is arranged at the bottom of the flow guide body, and horizontal wings are symmetrically arranged on the two sides of the flow guide body; a driving assembly is further arranged on the flow guide body and used for driving the two horizontal wings to be synchronously and symmetrically unfolded or folded. The requirements for power and resistance in the two modes are considered, and the contradiction between the two power modes for water power and the structure of the aircraft is relieved: in the power mode of the glider, the horizontal wing provides lift force required by sliding for the aircraft; in the power mode of propelling of the propellers, the horizontal wings are retracted into the flow guide bodies, resistance brought by the horizontal wings is eliminated, and the horizontal wings are protected.

The invention provides a morphing aircraft with variable swept wings and head deflection. The morphing aircraft comprises an aircraft head, an aircraft fuselage, a left swept wing, a right swept wing, a head deflection device and a swept wing deflection device. Wherein the head deflection device is arranged between the head of the aircraft and the fuselage of the aircraft; the sweeping wing deflection device is arranged between the left sweeping wing and the right sweeping wing; the head deflection device is used for controlling the aircraft head to deflect; and the sweeping wing deflection device is used for controlling the left sweeping wing and the right sweeping wing to sweep. According to the morphing aircraft, the streamline of the aircraft body is smooth, the deformation mechanism principle is simple and easy to achieve, and the aerodynamic performance of the aircraft in subsonic velocity and low supersonic velocity flight is improved by means of aerodynamic shape changes of the aircraft head and the swept wings.

A method of controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design-condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist.

A multirotor aircraft 10 that is adapted for vertical take-off and landing comprises a fuselage 20, a thrust producing unit assembly 30 that is provided for producing thrust in operation, and a forward-swept wing 40 that comprises a portside half wing 43 and a starboard side half wing 44. Each one of the portside and starboard side half wings 43, 44 comprises an inboard section 45 that is connected to the fuselage 20 and an outboard section 46 that forms a wing tip 71. The inboard sections 45 of the portside and starboard side half wings 43, 44 form a central wing region 80. The portside and starboard side half wings 43, 44 are respectively connected in the region of their wing tips 71 to an associated outboard wing pod 70 that supports at least two non-tiltably mounted thrust producing units 31, 32 of the thrust producing unit assembly 30.

The invention discloses a wingtip follow-up buoy of a variable swept wing water plane. The wingtip follow-up buoy of the variable swept wing water plane comprises a buoy main body, a buoy connection mechanism and a follow-up mechanism; and the buoy is located below a wing and close to the root of the wing and is connected with the wing through the buoy connection mechanism. The wingtip follow-up buoy of the variable swept wing water plane, disclosed by the invention, has the function that the buoy is always parallel to an axis of a plane body along with the change of a wing sweepback angle isrealized through the follow-up mechanism; the buoy is divided into two parts; the upper part can rotate around the wing and be connected with the follow-up mechanism; the lower part is detachable, sothat the process and use maintainability of the buoy are ensured; and the wingtip follow-up buoy is designed through a relative simple structure and very light weight, so that the buoy can always keepparallel to the plane body in a process of changing the sweepback angle by the wing, and has very strong practical application value.

The invention provides a shear variable sweepback airfoil and a design method thereof, the airfoil comprises an inner wing and an outer wing, the inner wing is fixed with a fuselage; the outer wing comprises at least three parallel beams and a plurality of wing ribs arranged among the beams, the wing ribs are connected with the beams through pin shafts, and the wing ribs and the beams rotate around the pin shafts; one end of the outer wing extends into the inner wing, each beam is assembled on a rotating shaft fixed with the inner wing, and the plurality of rotating shafts are linearly arranged along the incoming flow direction; and one beam extends into the machine body and is connected to a driving mechanism. The wing ribs are always kept parallel to the incoming flow direction in the variable sweepback process, that is, the wing sections are always kept parallel to the incoming flow direction, the good aerodynamic characteristics of the wing sections are kept, and it is guaranteed that the aircraft has the high aerodynamic efficiency and the low-resistance characteristic in the different sweepback angle states in the flight process.

The invention discloses a novel variable-sweep wing mechanism, which includes a cover plate, a base, a push block, and a spring locking pin. The sweep angle of the wing is controlled by the push block and locked by motor control; Cooperating with the spring locking pin, the cover plate and the base can be unlocked and locked when the sweep angle changes, ensuring the matching between the center of mass and the pressure center of the full spring during the change of the sweep angle, optimizing the resistance and moment characteristics of the full spring, and improving Full bombardment control efficiency.

The invention discloses a rigid-flexible coupling skin structure of a shear type variable sweepback wing, relates to the technical field of aviation, and aims to solve the problem of deformation of a shear type variable sweepback wing skin in a complex force thermal environment in the prior art. The bearing framework comprises rib plates arranged in parallel and bearing stringers connected with the rib plates, the rib plates are rotationally connected with the bearing stringers, bearing stringer lugs are arranged on the bearing stringers, close to the fuselage, between the rib plates, the stringer lugs are rotationally connected with the fuselage through pin shafts, and sliding ways are machined in the rib plates; the wall plate type skin surface piece comprises a plurality of sub surface pieces, the sub surface pieces are fixedly arranged on the two adjacent rib plates, the sub surface pieces are made of high-temperature alloy materials, and the sub surface pieces are tightly arranged. The problem of adaptive deformation of the shear type variable sweepback wing skin in a complex force thermal environment is solved.

The invention discloses a tailstock type vector differential biaxial aircraft. The tailstock type vector differential biaxial aircraft comprises a main wing, a vector motor base, a canard and an mwc flight controller. Sweepback wings are adopted as the main wing to provide main lift force. The canard is located at the front end of the main wing and used for increasing the overall stall angle of attack of the aircraft and providing lift force. The vector motor seat is arranged at the tail part of the main wing and is used for overcoming the flight resistance and self-gravity of the aircraft. The flight controller automatically detects the posture during hovering, and automatically changes the direction of the motor base and the rotating speed of the motor when the posture is abnormal, so that the motor base is stable. Characteristics of a rotor aircraft and a fixed-wing aircraft are combined, a vector technology is introduced, and a low-power engine is selected to be fixed to a vector motor base; double engines, a special airfoil profile, a moderate aspect ratio, canard wings and a wing end stabilizing surface are adopted, and the requirements for rapid small-attack-angle flight, hovering, low-speed large-attack-angle flight and rapid steering and attack angle change under a complex site can be met.