179results about "Wing shapes" patented technology

The invention discloses a wide-speed-range variant high-speed aircraft aerodynamic layout, and belongs to the technical field of aircrafts, the wide-speed-range variant high-speed aircraft aerodynamic layout comprises a fuselage, the front end of the fuselage is provided with a drag reduction rod, the rear end is provided with a thrust vectoring nozzle, the left and right sides are symmetrically provided with triangular sweepback wings, and the top is provided with a supporting structure; a high-pressure capturing wing is arranged on the top of the supporting structure. The shock wave separation effect of the drag reduction rod is combined with the high-pressure capture and reflection shock wave induction mechanism of the high-pressure capture wings, so that the aircraft can achieve effective drag reduction and lift augmentation effects in different flight states, and the lift-drag ratio and adaptability of the high-speed blunt cone aircraft are remarkably improved.

A craft comprises a hull, a wing, a hydrofoil, and a control system. The wing is configured to generate upwards aero lift as air flows past the wing to facilitate wing-borne flight of the craft. The hydrofoil is configured to generate upwards hydrofoil lift during a first mode of operation as water flows past the hydrofoil to facilitate hydrofoil-borne movement of the craft through the water. While the craft is hydrofoil-borne, the control system is configured to determine the upwards aero lift generated by the wing. The control system is further configured to control the hydrofoil to generate downwards hydrofoil lift to counteract the upwards aero lift generated by the wing that maintains the hydrofoil at least partially submerged in the water while the determined upwards aero lift is below a threshold lift.

The present invention provides an extreme STOL airplane comprising: a fuselage and a wing having port and starboard wing sections. Each wing section has a body with top and bottom surfaces, leading and trailing edges, and a span, i.e., the distance between a wing section tip and root connected to the fuselage, and flap coves. Aerodynamic elements integrated into the wing sections include Fowler flaps, having leading and trailing edges and a span, flap tracks, wherein the flap tracks are external to the wing section body, extend aftward beyond the trailing edge of the wing section, and are configured to enable the Fowler flaps to rotate or deflect and to translate or extend and retract, Frise ailerons, wherein the Frise ailerons are located outboard of the Fowler flaps, and spoilerons located over the leading edge of the Fowler flaps when the flaps are in the fully extended position.

An aircraft (10) has four or more rotors (20) including a pair of first rotors (20a) and a pair of second rotors (20b, 20c), the pair of first rotors (20a) being disposed bilaterally symmetrically with a center at a position overlapping a center axis (A) of a fuselage (12) when viewed from above at a position forward of a front wing (14), the pair of second rotors (20b, 20c) being disposed bilaterally symmetrically with a center at a position overlapping the center axis (A) of the fuselage (12) when viewed from above at a position between the front wing (14) and a tail wing (16). The distance (Dy, Dz) separating the fuselage (12) and the second rotors (20b, 20c) in a width direction is longer than the distance (Dx) separating the fuselage (12) and the first rotors (20a) in the width direction.

The wide-speed-range tailless variable-structure aircraft comprises an aircraft body, the aircraft body comprises an aircraft body-fixed wing fusion body and variable-structure wing rudders, the variable-structure wing rudders are symmetrically arranged on the two sides of the aircraft body-fixed wing fusion body, and a wing body fusion body layout is integrally formed; the fuselage-fixed wing fusion body is connected with the variable-structure wing rudder through a driving mechanism, and the variable-structure wing rudder can deflect in the axial direction of the fuselage; the tail of the fuselage-fixed wing fusion body is provided with a trailing edge rudder, the trailing edge rudder of the fuselage-fixed wing fusion body achieves pitching channel control through same-direction deflection, and under the condition that the channel coupling coefficient is smaller than 1.5, rolling channel control is achieved through differential deflection. The problem that the yaw channel operation stability characteristic is insufficient under the tailless layout condition is solved, and the wide-speed-range operation performance of the aircraft is effectively improved; compared with other variable-structure aircrafts in which additional variables are introduced, the combination of the variable-structure wing rudder and the trailing edge rudder is simple and efficient, and the burden on a control system is small.

The application belongs to the field of aircraft design, and particularly relates to a military transport aircraft. The military transport aircraft comprises a fuselage (1), a ring-shaped wing (2), an engine (3), a vertical tail (4), a canard (5), a landing gear (6) and a rear cargo door (7). The ring-shaped wing (2) extends upwards and upwards from the middle floor of the fuselage, and is connected with the vertical tail (4). The fuselage is surrounded by the ring-shaped wing (2) by 360 degrees. The engine nozzle is shielded from below and from the side by the ring-shaped wing (2). The main landing gear strut is connected to the wing and can be placed in the wing after being retracted. The application improves the cruising efficiency of the military transport aircraft, reduces the structural weight, improves the airport and take-off and landing adaptability, effectively shields and protects the fuselage and the engine, and comprehensively enhances the use efficiency of the transport aircraft.

The invention relates to a wing assembly (10) in the form of a propeller of a fixed-wing aircraft or a gyroplane, or in the form of a rotor blade of a main and / or auxiliary rotor of an aircraft with wings, a helicopter, or a gyroplane, or in the form of a rotor blade of a wind turbine rotor. The wing assembly (10) comprises a main wing (12) and a leading edge slat (14) attached to it in front of the main wing (12) opposite to a flow direction (22), such that a gap (16) with a flow inlet (18) and a defined, fixed flow outlet (20) is formed between the leading edge slat (14) and the main wing (12).Viewed in a vertical cross-section along the flow direction (22), the length (D) of a section (32) of the leading edge slat (14) extending forward against the flow direction (22) beyond a length (A) of the main wing (12) is at least 20% of the total length (C) of the wing assembly (10) in the flow direction (22). It is proposed that the flow inlet (18) be larger than the flow outlet (20) so that an airflow (24) in the gap (16) creates a Bernoulli effect.

The invention relates to an engineering-oriented wave rider airfoil efficient design method. The method comprises a traditional wave rider theoretical aerodynamic shape cutting method and a wave rider airfoil shape and position layout design method for a wave rider wing, a vertical tail, a pelvic fin and other airfoils. Aiming at the problems that the traditional wave rider theoretical appearance is only suitable for a single design point and the stability and the controllability are insufficient during cross-speed-domain flight, a system solution is provided for cross-speed-domain stable flight of the hypersonic flight vehicle. According to the method, the design technology breakthrough is realized by combining the parameterized cutting technology of the traditional wave rider theoretical appearance and the multi-airfoil collaborative optimization design. Through a global parameter joint debugging algorithm, after airfoil design is completed, the aerodynamic center position variation of the waverider under different Mach numbers is reduced, trimming is easy, and engineering adaptability design of a theoretical shape is achieved.

The application provides a swept-back three-beam thin wing composite wing structure, which comprises a wing main body and an aileron installed in a wing main body mounting groove, the wing main body comprises a wing skeleton and a wing outer skin structure outside the wing skeleton; the wing skeleton comprises a longitudinal member unit and a transverse member unit, the longitudinal member unit comprises a front beam, a middle beam and a rear beam, the front beam and the middle beam and the middle beam and the rear beam are arranged at acute angles, the transverse member unit comprises a plurality of wing ribs arranged between the front beam and the middle beam, between the middle beam and the rear beam and on one side of the front beam towards the front of the fuselage; the front beam, the middle beam and the rear beam are all provided with a spar connecting head for connecting with the fuselage. The wing provided by the application adopts a three-beam structure, each wing beam has a mouth-shaped cross section, so that each wing beam forms a multi-wall form, can bear the bending moment and the torque brought by a large wing effective load, and the wing structure is light in weight, high in strength and good in integrity.

The invention discloses a wing, an aircraft, a wing design method, a storage medium and electronic equipment. The wing comprises a wing body and a control piece, and the control piece comprises a first end, a second end, a third end and a fourth end, the second end is arranged on one side of the first end, and a first surface is formed between the second end and the first end; wherein a preset angle is formed between the first surface and the upper surface of the wing body, and a preset height is formed between the first end and the second end. The wing can eliminate the head lowering pitching moment while having a larger maximum lift coefficient, and has the advantages of increasing the lift of the wing, reducing the area requirement of the wing, reducing the balancing loss of the pitching moment, being convenient to realize the balancing of the pitching moment and the like.

The aircraft includes a fuselage (24), first and second forward wings (20, 22) attached to and / or extending from opposite sides of the fuselage (24), first and second aft wings (30, 32) and a continuous aft wing span (34) defining a fixed center connection (36), a first wing connection member (42) extending between the first forward wing (20) and the first aft wing (30), and a second wing connection member (44) extending between the second forward wing (22) and the second aft wing (32). 2), wherein an aft wing span (34) is supported by a centrally located V-tail joint defined by first and second angled arms (100, 110), and first and second electric motors each having a rotor mounted on each wing (20, 22, 30, 32), each rotor pivoting between a first configuration for vertical flight and a second configuration for forward flight.

The invention relates to an aerodynamic profile body with an outer flow surface for flow through a fluid, wherein the aerodynamic profile body comprises:a first surface layer and a second surface layer, which form at least part of the outer flow surface and are designed to be flexible in an end section of the aerodynamic profile body,a connection arrangement that flexibly connects the first surface layer to the second surface layer of the profile body in the end section, andan actuator device with at least one actuator provided in an interior of the aerodynamic profile body which interacts with at least one of the surface layers in the flexible end section in such a way that the cross-section of the aerodynamic profile body in the flexible end section can be changed by the at least one actuator,characterized in thatthe outer flow surface of at least one of the surface layers in the flexible end section has, at least in sections, a surface profile that extends parallel to the direction of flow.

The invention provides a large-scale supersonic civil aircraft wing body fusion low-sonic-boom aerodynamic layout, and relates to the field of supersonic civil aircraft design, the large-scale supersonic civil aircraft wing body fusion low-sonic-boom aerodynamic layout comprises a nose, a middle fuselage, a wing body transition section, wings and a V-shaped empennage; the machine head is in a duckbilled flat shape, the upper contour line is a downward-inclined curve, the lower contour line is an upward-warping curve, the side contour line is a sharp-arch-shaped curve, the section of the head is in the shape of a combination of a triangle and an arc, the upper portion of the section of the head is a triangle with the top in arc transition, and the lower portion of the section of the head is an arc. The camber of the center line of the middle fuselage is small, and only the front section bends down slightly; the middle fuselage is connected with the roots of the wings through wing body transition sections; the wings are arranged on the two sides of the middle fuselage and adopt an arrow-shaped wing layout with a small aspect ratio, a variable dihedral angle and a variable torsion angle and a camber wing type; the V-shaped empennages are arranged on two sides of the tail end of the According to the method, the problem that a gap still exists in the fusion low-sonic-boom aerodynamic layout of the wing body of the large supersonic speed civilian aircraft is solved, and reference is provided for research on the fusion layout of the supersonic speed wing body.

The ducted wing is configured to be connected to an aircraft. The ducted wing includes jet foils arranged in an integrally continuous array. Each jet foil includes a propulsion fan, an upper wing portion, and a lower wing portion extending beyond an end of the upper wing portion. Each jet foil includes a duct formed between the upper wing portion and the lower wing portion, and the propulsion is within the duct. Further, each jet foil may have one or more flaps at a leading edge or a trailing edge of the jet foil. The jet foil may have a flap that controls either an inlet area or an outlet area of the propulsion fan, and a flap that controls so that the aircraft can operate in any of a plurality of different takeoff modes.

The invention relates to an aircraft (2) comprising a wing (4) and means (6, 30) for propelling the aircraft (2); the wing (4) having a flexible, airtight envelope (18) designed to contain air; the flexible envelope (18) being configured such that, when it contains air in a nominal inflation state, the aerodynamic profile of the flexible envelope (18) alone generates the lift of the wing (4). The aircraft (2) may be a piloted aircraft of the airplane type or an unpiloted aircraft of the drone type. Abstract figure: Fig. 1

Wing-in-ground effect (WIG) vehicles are disclosed herein. Hovercraft takeoff and landing modes are disclosed herein. Uses of WIG vehicles, including for maritime monitoring, are disclosed herein.

A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees.

The present invention relates to a split rib for securing a leading edge assembly. The rib includes a first rib portion having a first rear mounting portion for attaching the first rib portion to a wing box assembly and further having a front mounting portion opposite the first rear mounting portion. The rib further includes a second rib portion having a second rear mounting portion for attaching the second rib portion to the front mounting portion of the first rib portion.

The application discloses a kind of torsion wing structure and aircraft, it is related to the field of morphing wing technology, including linear drive device, wing rib and pressure-torsion coupling cell, wing rib and pressure-torsion coupling cell are multiple, multiple wing ribs are arranged along the wing span direction interval, and pressure-torsion coupling cell is equipped between two adjacent wing ribs;Pressure-torsion coupling cell includes intermediate connecting component and the load-bearing end block fixedly connected with the two ends of intermediate connecting component, load-bearing end block is fixedly connected with adjacent wing rib, and all wing ribs and pressure-torsion coupling cell form wing main body;The first end wing rib of wing main body is used to be fixedly connected with fuselage;Two load-bearing end blocks of pressure-torsion coupling cell are connected with linear drive device;Linear drive device can make the two load-bearing end blocks of each pressure-torsion coupling cell approach each other or away from each other, to make intermediate connecting component torsion deformation and drive wing rib around wing span torsion by load-bearing end block.The application has the effect of "lightweight-structure simplification-aerodynamic efficiency-high life-low maintenance cost".

The present invention provides an unmanned aerial vehicle and an aircraft wing structure that can prevent airflow separation at the wingtips and facilitates the manufacturing of the wing body. [Solution] The unmanned aerial vehicle of this disclosure comprises an airframe and a main wing. The main wing has a pair of left and right wing body members connected to the airframe at the wing root and extending in the wingspan direction toward the wingtip, and at least one movable wing member provided on the trailing edge of the wing body members and displaceable relative to the wing body members. The at least one movable wing member has a wing root portion located toward the wing root and a wingtip portion located toward the wingtip. The wingtip portion has a smaller lift coefficient than the wing root portion.

The invention relates to the technical field of aircrafts, and discloses an aircraft flight control device which comprises a longitudinal arm and a vertical empennage, the vertical empennage is arranged on the lower side of the tail of the longitudinal arm, and a plurality of lift propellers are further arranged on the upper side of the longitudinal arm in the front-back direction. The longitudinal arms are arranged in the front-back direction of the aircraft; when the aircraft flies forward and lowers the head, the cross section of the longitudinal arm and the horizontal plane is a standard airfoil profile, the projection of the standard airfoil profile on the cross section is the cross section of the arm, and the connecting surface of the vertical empennage and the longitudinal arm is in a vertical empennage type. The aircraft has the advantages of reducing the resistance of the longitudinal arms during forward flight, reducing the course control burden of a power system during high-speed forward flight and the like, and solves the problems that the course control capability is weak, course control is easy to oscillate or diverge, and the maximum forward flight speed is limited.

The invention relates to an aircraft wing and to an aircraft comprising such an aircraft wing. The aircraft wing comprises a wing structure supporting a wing cover having an outer aerodynamic surface forming part of an airfoil profile of the wing and a recess stepped back from the wing airfoil profile, and a spoiler device comprising a spoiler coupled to the wing structure by a spoiler actuation mechanism for moving the spoiler between a retracted position and a deployed position, the spoiler having a surface following the outer profile of the wing airfoil profile and the spoiler being fully accommodated in the recess when the spoiler is in the retracted position, and wherein the spoiler surface extends away from the wing cover when the spoiler is in the deployed position.

The invention discloses a high-aerodynamic-efficiency fusion type wingtip winglet. The wingtip winglet comprises a fusion wing root section, a torsion main section and a wingtip rectification section which are connected in sequence; the wingtip winglet adopts a spanwise variable thickness modified NACA laminar flow airfoil, the relative thickness of a wing root is 12%-15%, the relative thickness of a wingtip is 6%-8%, the wingtip winglet is linearly and gradually changed in the spanwise direction, the radius of the front edge of the wingtip winglet is 0.8%-1.2% of chord length, the rear edge of the wingtip winglet is in forward pressure gradient transition, and the maximum thickness of the wingtip winglet is located at the position of 35%-40% of the chord length; the wingtip winglet main body is of a multi-wall multi-closed-chamber integrated bearing structure and comprises a front beam, a rear beam, an upper skin and a lower skin, and at least three main closed chambers are formed; the high-aerodynamic-efficiency fusion type wingtip winglet has the advantages of being excellent in aerodynamic performance, light in weight, fast to install and adjust and high in universality, and is suitable for civil airliners, transport aircrafts and high-end fixed-wing unmanned aerial vehicles.

The invention belongs to the technical field of aircraft structure design, and particularly relates to a winglet structure. A winglet upper wall plate is installed on the upper side of a wing box section butt joint rib, a winglet upper wing surface covering cap is arranged at the position, close to a wing box section, of the winglet upper wall plate, a winglet lower wall plate is installed on the lower side of the wing box section butt joint rib, and a winglet front beam and a wing box section front edge partition plate are installed on the front side of the wing box section butt joint rib. The winglet rear beam and the wing box section rear edge partition plate are mounted on the rear side of the wing box section butt joint rib; the winglet front edge partition plate is connected with the winglet front beam, the front edge skin is connected with the winglet front edge partition plate, the winglet front beam and the wing box section front edge partition plate, and a front edge covering cap is arranged at the position, close to the wing box section, of the front edge skin. The winglet rear edge comprises a winglet rear edge partition plate, and the winglet rear edge partition plate is connected with the winglet rear beam; the winglet tip is located at the position away from the wing box section and connected with the winglet upper wall plate, the winglet lower wall plate and the leading edge skin.

An aircraft 310 has a pair of swept wings 314A meeting at a central region 312. Each wing has an inner wing section 326A containing an integrated payload fuselage (fig.1,20); a thinner thickness oute

Propulsion assembly for an aircraft, comprising a turbomachine (1), an attachment strut (40) and a structural element (10) carrying the turbomachine (1) by the attachment strut (40), the turbomachine having at least one rotating part (30) rotating about an axis of rotation (A), the rotating part (30) being arranged upstream of the structural element (10) and of the attachment strut (40) so that the air jet exiting from the rotating part (30) impacts the structural element (10) and the attachment strut (40) in the wake thereof, the leading edge of the structural element (10) and / or of the attachment strut (40) locally comprising at least one acoustic attenuation device (50, 60, 70, 80) arranged at least partially in the wake of the rotating part (30), the acoustic attenuation device being a partial modification of the structure and / or of the profile of the leading edge (11).

An aircraft capable of transonic flight is equipped with a slotted airfoil to significantly improve the cruise performance during flight. The aircraft includes a plurality of slotted airfoils uniquely configured to maximize natural laminar flow across the aircraft wings. In addition to reduced wing drag, the unique configuration minimizes shocks at various conditions over the course of a flight. Each slotted airfoil includes a fore element, an after element, and a slot disposed between the fore element and aft element. The aft element is maneuverable relative to the fore element. The slot is configured to promote a substantially constant air flow field onto the aft element during all flight angles of attack.

In a first aspect of the present invention there is provided a blade for a wind turbine. The blade extends from a blade root defining a radial position r=0 to a blade tip defining a radial position r=R. The blade comprises a windward side and a leeward side which meet at a leading edge and a trailing edge to define an airfoil profile. A chord is the distance between the leading and trailing edges, and a relative thickness is the ratio of thickness to chord. The airfoil profile has a thickness being the greatest distance between the windward and leeward sides orthogonal to the chord. The blade comprises a connection point located at a first radial position (r1) between the blade root and the blade tip for connection of one or more blade connecting members for being connected between the connection point and a corresponding connection point on a neighbouring blade. The thickness and / or the relative thickness of the blade is substantially constant or has a local minimum within an inboard portion of the blade between the blade root and the connection point.

The invention relates to the technical field of ground effect aircrafts, in particular to a tilt rotor type vertical take-off and landing ground effect aircraft. Comprising a fuselage, gull-shaped wings are symmetrically arranged on the two sides of the fuselage, empennages are arranged on the rear portion of the fuselage, winglets are arranged at the side ends, away from the fuselage, of the gull-shaped wings, and buoys are arranged below the joints of the gull-shaped wings and the winglets; the multi-rotor synchronous tilting mechanism penetrates through the gull-shaped wings and the interior of the fuselage. By arranging the tilting rotors and the gull-shaped wings with the small aspect ratio, more stable airflow distribution can be formed in the flight process, the flight response is good under various meteorological conditions on the sea, and during low-speed flight, the design of the gull-shaped wings can effectively reduce the induced resistance of the wings and increase the lift force, so that the stability and maneuverability of the aircraft are improved.

An aircraft that includes a canard having a leading edge and a trailing edge, a forward swept and fixed wing having a trailing edge, and a plurality of tilt rotor submodules, a dovetail, and a T-tail. The plurality of tilt rotor submodules are coupled to the trailing edge of the forward swept and fixed wing. The dovetail is attached to an underside of a fuselage. The T-tail is located above the dovetail. A horizontal plane of the T-tail is at a height that is higher than a horizonal plane of the forward swept and fixed wing.