91results about How to "Reduce induced drag" patented technology

Systems and methods for providing variable geometry winglets to an aircraft are disclosed. In one embodiment, a winglet includes a base portion configured to attach to a wing. The winglet further includes a body portion. In turn, the body portion includes at least one of a deflectable control surface, a shape memory alloy (SMA) bending plate, and a SMA torque tube. The base portion is configured to attach to the wing such that the body portion projects at an upward angle from the wing.

The invention provides an unmanned aerial vehicle with variable sweepbacks and spans of wings, which comprises a vehicle body, the wings and a tail wing, wherein a cross beam is arranged in the middle of the vehicle body; a mechanism for controlling sweepback changes is arranged between the wings and the cross beam; the mechanism for controlling sweepback changes is a four-bar linkage mechanism which comprises a stepping motor, a driving rod and a pushing rod; and the wings include main wings and auxiliary wings. The auxiliary wings can freely move in or out of the main wings by means of relative displacement between the rack and the gear, resulting in the changes of span. Further, the main and the auxiliary wings are provided with friction wheels to achieve the limiting and vibration-reducing effects. The mechanism for controlling sweepback changes has a small size and light weight and can meet the requirements for unmanned aerial vehicles. Besides, the span change is achieved by therelative displacement between the rack and the gear, the running is stable, and no response lag influence exists.

The invention provides an airplane with a combined-wing layout of a flying wing and forward-swept wings. The airplane is characterized in that thin-wing type vertical columns A and B are additionally arranged at the 70% wingspan positions of the outer sides of two side wings of a flying-wing airplane with backward-swept wings, a thin-wing type vertical column C is additionally arranged at the tail part of the flying-wing airplane, and horizontal forward-swept wings are additionally arranged at the top ends of the three thin-wing type vertical columns A, B and C so as to form the combined-wing layout of the flying wing and the forward-swept wings; elevators are arranged on the horizontal forward-swept wings and a rudder is arranged on the vertical column C; a duct type air inlet channel is adopted on the upper wing surface of the flying wing, and cracking type drag rudders are distributed at the thin-wing type vertical columns A and B. The airplane provided by the invention has the advantages that under the condition that the structure strength is effectively guaranteed, the effective aspect ratio of the wings is increased, the induced drag is reduced, the lift-drag characteristics of the airplane are improved, the stealth performance of the airplane is improved, direct-force control of the airplane in the vertical direction is realized and the detecting accuracy under the maneuvering condition is improved.

The invention provides a drag-reducing device of a anti-rolling fin of a ship wing flap, comprising a fin and a wing flap, wherein one end of the fin is provided with a fin shaft; one end of the wing flap is provided with a wing flap fin shaft; the fin shaft and the wing flap fin shaft are connected with a ship hull; the upper fin surface at the free end of the fin is provided with an upper fin surface baffle, and the lower fin surface at the free end of the fin is provided with a lower fin surface baffle; the upper wing flap fin surface at the free end of the wing flap is provided with an upper wing flap fin surface baffle, and the lower wing flap fin surface at the free end of the wing flap is provided with a lower wing flap fin surface baffle. The invention has simple structure and easy installation and realization and can effectively reduce the induced resistance of a fin stabilizer, enhance the lift efficiency of the anti-rolling fin of the wing flap, prevent a water flow medium cavitation phenomenon from generation and enhance the anti-rolling effect of the anti-rolling fin of the wing flap and the safety and the economy of ship navigation.

A wing for an aircraft includes a non-balanced lift gradient because as a result of at least one propeller slipstream flowing onto the wing the induced drag of the wing is increased. To reduce the increased induced drag, the wing comprises a first region with a reduced local wing camber and / or reduced local twist, and a second region with an increased local wing camber and / or increased local twist. The first region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move upwards. The second region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move downwards.

The invention discloses an inclined fixed wing unmanned plane. The inclined fixed wing unmanned plane comprises a plane body and a wing inclined mechanism which can incline the wings, wherein the two sides of the plane body are provided with at least one pair of wings, and the tail of the plane body is also provided with a tail wing; and each wing is fixedly provided with a power device, each power device is connected with a screw propeller, the wings and the power devices are fixedly arranged together and can simultaneously move, and the rotation surfaces of the screw propellers are perpendicular to the horizontal planes of the wings all the time. The inclined fixed wing unmanned plane adopting the technical scheme can vertically take off and land and can realize high the cruising speed and power utilization efficiency and reasonable structure of a fixed wing plane; as the preferred technical scheme, the wings are both provided with subsidiary wings which are controlled by the wing inclined mechanism, and the power devices are all fixedly arranged on the middle parts of the wings; and the wings have enough rigidity and intensity, the wings are prevented from deforming because the power devices are fixedly arranged, and the localization of the wings is exact in revolution and fixation.

The invention provides a multi-rotor wing unmanned aerial vehicle, and a system and a flight control method thereof. The unmanned aerial vehicle comprises a machine frame and a horizontal driving device; a main rotor swing and a main rotor swing motor which is connected with the main rotor swing are arranged on the machine frame; the rotating axis direction of the main rotor swing is perpendicular to the horizontal plane of the machine frame; the horizontal driving device is arranged below the machine frame, and the direction of the driving force provided by the horizontal driving device is perpendicular to the rotating axis direction of the main rotor wing, wherein the main rotor wing motor and the horizontal driving device are both connected with a flight control board. No matter the multi-rotor wing unmanned aerial vehicle is in a hovering state or a running state, the attitude angle of the multi-rotor wing unmanned aerial vehicle is kept near zero all the time, and the problem of instantaneous height falling of the unmanned aerial vehicle caused by the inclining of the attitude angle can be avoided; the running power can be provided by the horizontal driving device without relying on the inclining of an attitude; therefore, the attitude of the unmanned aerial vehicle is stilled kept horizontally in the running process.

The invention discloses a vertical take-off and landing fixed wing long-endurance air vehicle. The vertical take-off and landing fixed wing long-endurance air vehicle comprises a fuselage in horizontal position in flight; the head part of the fuselage is provided with a pair of canard type wings; the tail part of the fuselage is provided with a pair of wings; a vertical empennage is arranged below the tail part of the fuselage; the lower parts of the wings are provided with at least two pairs of distributed power plants, wherein the number of the power plants is even, and the revolving shafts of the power plants are arranged along the axis of the fuselage; the head part of the fuselage is provided with a vertically distributed through hole; and an elevating control power plant is arranged in the through hole, and the revolving shaft of the elevating control power plant is arranged in vertical. According to the vertical take-off and landing fixed wing long-endurance air vehicle, the elevating control power plant is used for changing rotating aped of variable pitch propellers and elevating control moment force needed by screw pitch output in the whole flight envelope; the number of fixed pitch propellers is larger, and rotating speed of each propeller can be controlled individually, so that rolling and yaw control adjustable minimum pulse-width is smaller, and control accuracy is higher.

An aircraft (40). The aircraft (40) comprises a propulsion system comprising a pair of internal combustion engines (10) each driving an electrical power generator (56), each electrical power generator (56) being electrically coupled to a plurality of electrically driven propulsors (46). The propulsors (46) are located forward of a leading edge (45) of the wings (44) such that an airstream generated by the propulsors flows over the wings (44) in use. Each internal combustion engine (10) and electrical generator (56) is mounted on a respective wing (44) outboard of a centre of thrust (70) of the propulsors (46) on that wing (44).

The present invention discloses a high-aspect-ratio wing frame architecture design method and relates to the technical field of aircrafts. The design method comprises a rigid wing optimization step and an elastic wing optimization step. The rigid wing optimization step comprises generating an initial population of the wing architecture, performing lift-drag ratio calculation to obtain a local optimal solution, then carrying out optimizing calculation, performing lift-drag ratio calculation on the local optimal solution and comparing with the local optimal solution obtained after the initial population is subjected to the lift-drag ratio calculation, and finally judging the globally optimal solution; and the elastic wing optimization step comprises calculating the aerodynamic load borne by an elastic wing during an flight, then calculating the elastic deformation of the wing, solving the true form of the wing structure under elastic balance at the flight state through multiple iterative computations to obtain the flight load after the elastic deformation and acquire the twist angle of a wing profile architecture, and thus completing the design of the wing frame architecture. The wings designed through the high-aspect-ratio wing frame architecture design method have good geometrical aerodynamic twist angle distribution, the lift distribution is better, the smaller induced resistance can be produced, the best lift-drag ratio is obtained, and thus the cruising efficiency is improved.

The invention relates to a composite material air propeller and a preparation die and a preparation method thereof. The composite material air propeller comprises an upper wall plate and a lower wall plate, wherein the upper surface and the lower surface of the upper wall plate are respectively an upper wall plate outer appearance surface and an upper wall plate inner appearance surface; the upper surface and the lower surface of the lower wall plate are respectively a lower wall plate inner appearance surface and a lower wall plate outer appearance surface; the upper wall plate outer appearance surface and the upper wall plate inner appearance surface are fixedly connected with each other through peripheral glue to form a composite material air propeller whole body; and a cavity is formed inside the composite material air propeller whole body. The composite material air propeller is of a split type structure, and the composite material air propeller is hollow; therefore, the composite material air propeller is simple in structure, easy to manufacture, low in cost and light in weight and has the structural characteristic that the tip is bent up, so that the inducing resistance of the composite material air propeller is greatly reduced; and the composite material air propeller is very favorable for application and development of multi-rotor-wing aircrafts.

The invention belongs to the field of general aircrafts, and particularly relates to an electrodynamic multi-rotor helicopter. The electrodynamic multi-rotor helicopter comprises a fuselage, power rotors, a rotor support arm, a undercarriage, an electric supply system and a flight control system, wherein even power rotors are arranged above the fuselage, each power rotor is installed on the upper part of the fuselage through the rotor support arm, the undercarriage is arranged at the lower part of the fuselage, the electric supply system and the flight control system are respectively installed in a battery cabin and a cockpit in the fuselage; the structures of the power rotors are the same, and the power rotor comprises a screw propeller, a drive motor and fairings; the drive motor is installed on the fuselage through the rotor support arm, the screw propeller is connected with the output end of the drive motor, and fairings are respectively arranged at the lower end of the drive motor and the upper end of the drive motor above the screw propeller. The helicopter disclosed by the invention is compact in structure, flexible in movement, and large in lift-weight ratio, and has the advantages of being strong in adaptability, safe and reliable, economical, environment-friendly, simple in control, and low in maintenance charge.

The invention relates to a wind turbine blade with a split winglet at the apex, which belongs to the field of wind power generation and comprises a winglet (1), a root connecting part (2) and a main blade (3), wherein the winglet (1) is composed of n sub wings, n is 2 or 3, and all the sub wings are trapezoid-shaped with the same taper and sweepback (12), the n sub wings are provided with different anhedrals; the root connecting part (2) extends out of a main blade apex (11) and is an irregular sphere in shape by taking the wing section of the main blade apex as the standard; the irregular sphere wraps the main blade apex (11) and is connected with the sub wings. According to the invention, the spanwise flow of the blade apex can be reduced, the vortice density of the blade apex without the winglet is dispersed, the induced resistance exerted by the blade apex vortex to the blade is weakened, and the purposes of improving the aerodynamic performance of the wind turbine and restraining the effect of the blade vortex in wake flow are realized, so that the aerodynamic performance is brought into play to the greatest degree.

The invention relates to a primary and secondary aircraft with wing tips connected in parallel. The primary and secondary aircraft is a high-aspect-ratio subsonic aircraft composed of a primary aircraft (1) and two secondary aircrafts (2) through a connecting mechanism (3), wherein the two secondary aircrafts (2) are symmetrically mounted at two sides of the primary aircraft (1); the primary aircraft (1) is of a high-aspect-ratio subsonic layout form; the two secondary aircrafts (2) are respectively positioned at the left and right wing tips of the primary aircraft (1) and are of a straight wing layout form; and the connecting mechanism (3) is positioned between a primary wing tip (4) and secondary wing tips (5) and is connected with the primary aircraft (1) and the secondary aircraft (2)by adopting a slide rail or a link mechanism. The secondary aircrafts (2) can independently complete corresponding flight missions by virtue of self-power, thereby being favorable for reducing the damage risk of the primary aircraft (1), reducing the using cost and being favorable for improving the using cost-effectiveness ratio of the unmanned aerial vehicle.

The flapping-wing fling water automobile includes engine, double-blade air screw propeller, right and left hydraulic screw propellers, right and left wings, control system, safety lifesaving equipment, and four-wheel undercarriage, hanging damper and fuselage, with the wings being connected to the fuselage via mechanical and hydraulic mechanism. The present automobile is one traffic facility for land, water and air use simultaneously, and has high efficiency and maneuverability. Its wings may be folded for land running.

The invention discloses a flying wing type aircraft with a variable wing outer wing sweep back angle and a tiltable small wing. The flying wing type aircraft with the variable wing outer wing sweep back angle and the tiltable small wing comprises an inner wing leading edge, outer wing leading edges, small wings, outer wing trailing edges, an inner wing trailing edge and elevons; outer wings are arranged on the two sides of an inner wing; the small wings are arranged at the tips of the outer wings; the outer wings and the small wings all adopt flexible skin structures; first acting mechanisms are arranged between the outer wings and the inner wing; and second acting mechanisms are arranged between the small wings and the outer wings. The flying wing type aircraft with the variable wing outer wing sweep back angle and the tiltable small wing has the advantages that higher lift drag characteristic of the aircraft is guaranteed, the reachable maximum flying speed of the flying wing type aircraft is increased, and meanwhile, the drag in each speed stage is reduced so that the aircraft can preferably develop the efficiency on a fighter plane.

The invention discloses a high-invisibility lifting-body configuration aircraft without a horizontal tail. The high- invisibility lifting-body configuration aircraft comprises a fuselage(1), a left main wing (21) and a right main wing (22) on both sides of the fuselage (1), a nozzle (3) located on the rear part of the fuselage, and air inlet ducts (41,42)located on the side parts of the fuselage (1), wherein a left winglet (51) is arranged at one end, away from the fuselage (1), of the left main wing (21), and a right winglet (52) is arranged at one end, away from the fuselage (1), of the right main wing (21); the appearance of the left winglet (51) is the same as the appearance of the right winglet (52); the camber angle of left winglet (51) is parallel to the camber angle of the lip of the air inlet duct (41) on the left part of the fuselage (1); and the camber angle of the right winglet (52) is parallel to the camber angle of the lip of the air inlet duct (42) on the right part of the fuselage (1). The high-invisibility lifting-body configuration aircraft without the horizontal tail disclosed by the invention is high in aerodynamic performance and good in invisibility effect.

The invention relates to a technology of an electromagnetic driving aerodynamic vehicle provided with tandem wings, and belongs to the technical field of direct drive between vehicle dynamic devices and wing hub of rotors. The technology of the electromagnetic driving aerodynamic vehicle provided with the tandem wings is mainly applied in spacecraft vehicles and aims at improving aerodynamic efficiency of flight vehicles, at the same time solves the practical application problems of the flight vehicles. The technology of the electromagnetic driving aerodynamic vehicle provided with the tandem wings comprises an electromagnetic driving aerodynamic device provided with the tandem wings. The electromagnetic driving aerodynamic device provided with the tandem wings comprises the tandem wings, a magnetic suspension supporting system, an electromagnetic motor driving system, a duct and a machine frame. The electromagnetic driving aerodynamic device provided with the tandem wings is characterized in that a rotating magnetic field driven by electric energy through the electromagnetic motor driving system directly drives the tandem wings, which are supported and confined by the magnetic suspension supporting system, to generate lifting force by moving in the annular duct formed between the inner wall and the outer wall of the duct, so that the flight vehicle gains lifting force or thrust. The electromagnetic driving aerodynamic vehicle provided with the tandem wings has properties of full electric drive, acetabuliform integrated wing body, vertical lift, safe low altitude flight, high-efficient overload, and long hang time.

The invention discloses a sea-land-air-submarine multi-purpose unmanned platform shared by hub ducts, which can be switched among land, flight and overwater / underwater modes and provides a powerful tool for reconnaissance and rescue. The sea-land-air-submarine multi-purpose unmanned platform shared by the hub ducts comprises a machine body, a control module, four duct servo mechanisms and four duct power mechanisms. The four duct servo mechanisms are in one-to-one correspondence with the four duct power mechanisms; each duct servo mechanism is used for controlling the posture of the duct powermechanism corresponding to the duct servo mechanism; each duct power mechanism is connected with the machine body through a duct servo mechanism, the four duct power mechanisms are distributed on themachine body in a rectangular shape, the duct servo mechanisms are used for controlling the posture of the ducts to be switched among the transverse mode, the vertical mode and the longitudinal mode,so that the unmanned platform can be switched among the land mode, the flight mode and the overwater / underwater mode.

The invention relates to a vertical V-surface grid plate comprising an upper guide plate, a plurality of V-surface wing plates, a warp reinforcing plate and a lower guide plate. Each V-surface wing plate has a high span-chord ratio and has a receding angle. The V-surface wing plates are disposed at equal intervals between the upper guide plate and the lower guide plate and are arranged backward at equal intervals; the warp reinforcing plate is connected with the V-surface wing plate, forming a grid whole. The vertical V-surface grid plate is suitable for fishing vessels different in total tonnage, is good in extensibility, is higher in hydropower efficiency and meets the needs of surface, middle and bottom trawling operations.

The invention discloses an air inlet cavity of an FSAE racing car. The air inlet cavity comprises an air inlet pipe, a pressure stabilizing cavity, air inlet manifolds and a manifold mounting surface, wherein one end of the air inlet pipe is connected with the pressure stabilizing cavity; the tops of the four air inlet manifolds which are parallel to one another are connected with the bottom of the pressure stabilizing cavity; the bottoms of the air inlet manifolds are connected with the manifold mounting surface; the manifold mounting surface is used for be assembled with an engine; the air inlet pipe comprises a throttle valve mounting surface, a compression pipe, a flow-limiting valve and a diffusion pipe; the throttle valve mounting surface is arranged at one end of the compression pipe; the other end of the compression pipe is connected with one end of the flow-limiting valve; one end of the diffusion pipe is connected with the other end of the flow-limiting valve; the other end of the diffusion pipe is connected with the pressure stabilizing cavity; and the throttle valve mounting surface is used for being assembled with a throttle valve. According to the air inlet cavity disclosed by the invention, by enlarging openings of two air inlet manifolds at the outer side, the air inflow is more uniform, and the defect that the air inflow of the two air inlet manifolds positioned at the outer side is insufficient is overcome; a low-pressure area and vortex at the flow-limiting valve and a corner are reduced, and the induced resistance of a connected part is reduced; the phenomenon of blow-by of various cylinders is inhibited; and meanwhile, the lengths of the air inlet manifolds are also increased.

The invention relates to a vertical V-shaped grid screen plate. The vertical V-shaped grid screen plate is composed of an upper guide plate, V-shaped wing plates which are large in aspect ratio and have receding angles, steel warp reinforcing plates and a lower guide plate. The V-shaped wing plates which are large in aspect ratio and have the receding angles are arranged between the upper guide plate and the lower guide plate, the upper ends and the lower ends of the wing plates are connected with the upper guide plate and the lower guide plate at angles of wedges of the front ends of the upper guide plate and the lower guide plate, the wing plates are arranged backwards in parallel at equal intervals, the steel warp reinforcing plates are arranged between the upper guide plate and the lower guide plate and connected with the wing plates to form a screen plate body of a small-aspect-ratio structure, and the whole screen plate body is in a grid mode. The vertical V-shaped grid screen plate has high obstacle crossing capacity and lodging resistance and has the advantages of being high in expansionary force and suitable for fishing boats of different gross tons and water work on different water layers.

The invention provides a novel wind turbine blade which comprises a main blade body, a blade tip extension segment and symmetrical little wings. The blade tip extension segment is connected with the main blade body and the symmetrical little wings respectively. The chord length of the blade tip extension segment is in smooth transition from the blade tip chord length to the little wing root chord length. The symmetrical little wings comprise the first little wing and the second little wing. The first little wing and the second little wing are symmetrical to each other. Both the first little wing and the second little wing are provided with lifting airfoils. Both the suction surface of the first little wing and the suction surface of the second little wing face a wind turbine body. The novel wind turbine blade has the advantages that the blade tip vortex is reduced, the blade stress is balanced, the pneumatic efficiency of the wind turbine is improved, the blade root waving moment is lowered, the requirement for the strength level of all components of the wind turbine is lowered, the reliability degree of the components of the wind turbine is increased, and the power generation cost of the wind turbine is reduced.

The invention relates to an upright grid type net plate which comprises an upper flow guide plate, a plurality of wing plates with large span-chord ratios, steel warp reinforcement plates and a lower flow guide plate. The upright grid type net plate is characterized in that the wing plates with the large span-chord ratios are arranged between the upper flow guide plate and the lower flow guide plate, the upper ends and the lower ends of the wing plates with the large span-chord ratios are connected with the upper flow guide plate and the lower flow guide plate along angles of wedges at the front end of the upper flow guide plate and the front end of the lower flow guide plate, are equidistantly rearwards arrayed and are parallel to one another, the steel warp reinforcement plates are arranged between the upper flow guide plate and the lower flow guide plate and are connected and combined with the various wing plates to form a net plate body which is of a structure with a small span-chord ratio, and the upright grid type net plate is integrally in a grid form. The upright grid type net plate has the advantages that merits of low induced drag and high lift-drag ratios of the wing plates with the large span-chord ratios can be sufficiently played, and the upright grid type net plate is applicable to fishing boats with different gross tons and operation on water of different water layers and is high in water power efficiency.

The invention relates to an inflatable wing based on oblique-swept gas beams, and can be applied to the field of aircrafts. The method specifically comprises the following steps: determining basic parameters of the oblique-swept gas beam inflatable wing; adjusting the section airfoil of the main oblique-swept gas beam; on the basis of the rounded two-dimensional airfoil profile, obtaining a single three-dimensional main oblique-swept gas beam, constructing a plurality of closely-arranged gas chambers through an array, forming a multi-oblique-swept gas beam structural body, and intercepting a multi-gas-beam entity according to the elongation; making the outer surface skin of the oblique-swept gas beam inflatable wing extracted and constructed through multiple oblique-swept gas beam entities; selecting a projection plane, and bridging an airfoil surface corrugated air chamber intersection line with a projection line on the projection plane to form an inflatable wing internal air chamber brace; and performing curved surface filling according to an airfoil profile end face sideline and an internal brace sideline, and finally forming end faces of two ends of a wingtip and a wingroot of the inflatable wing. The inflatable wing based on oblique-swept gas beams has more ideal lift-drag characteristic and flutter performance, and the aerodynamic performance is obviously improved.

The invention relates to an upright hook-surface grid-type screen which is composed of an upper diversion plate, a plurality of high-aspect-ratio hook-surface wing plates, drag-steel reinforcing plates and a lower diversion plate. The upright hook-surface grid-type screen is characterized in that the high-aspect-ratio hook-surface wing plates are arranged between the upper diversion plate and the lower diversion plate and are parallelly, backwardly and equidistantly arrayed starting from outer arcs of the front end of the upper diversion plate and the lower diversion plate, and the drag-steel reinforcing plates are connected with the high-aspect-ratio hook-surface wing plates to integrally form a grid type. The low-aspect-ratio upright hook-surface grid-type screen is formed by combination of the high-aspect-ratio hook-surface wing plates, thereby being better in stability and recovery performance, higher in hydrodynamic efficiency and suitable for use of different fishing boats different in gross ton and water operation different in drainage layer.

The invention discloses a flying-wing aircraft joined frying wing configuration structure which comprises a front wing, a jointed wing and a back wing, wherein the front wing is a high-span-chord-ratio backswept wing; the wingtips on both sides of the front wing are connected with the cambered jointed wing bottom; the top of the jointed wing is connected with wingtips on both sides of the back wing; the front wing, jointed wing and back wing are connected end to end to constitute an isosceles-trapezoid frame structure; the back wing is positioned above the front wing; the back wing comprises a back wing unswept airfoil in the middle and back wing sweptforward wings which are connected in a bilateral symmetry way; the extended surface of the tail of the back end of the front wing is symmetrically provided with front wing control blades; the extended surface of the tail of the back end of the back swept forward wing is provided with a back wing swept forward wing control blade; and the extended surface of the tail of the back end of the back wing unswept airfoil is provided with a back wing unswept airfoil control blade. The joined frying wing configuration structure has the advantages of high controllability, high static stability and favorable maneuvering performance, and solves the problem of control of the flying-wing aircraft.

The invention belongs to the field of wind power generation, and discloses a blade tip winglet, a wind turbine blade and a blade synergy calculation method. The blade tip winglet is arranged at the end part of the wind turbine blade and is used for increasing a power coefficient by reducing induced drag of the wind turbine blade. The blade tip winglet comprises a connecting section and a blade tipsection, and further comprises an arc-shaped section used for smoothly connecting the connecting section with the blade tip section in a transition mode, wherein a sweepback wing structure is formedon the windward side of the blade tip section; parameters of the blade tip section are defined, wherein the parameters comprise a mounting angle, height, an inclination angle, a torsion angle and a sweepback angle; the parameters further comprise an initial position L of the leading edge, and the initial position L is a distance value between the windward leading edge of the connecting section andthe most front end of the bottom of the blade tip section; and the initial position L is set between 0 and 0.20<c> to increase the power coefficient of the blade tip winglet and the connected wind turbine blade. According to the blade tip winglet, the wind turbine blade and the blade synergy calculation method, by defining multiple parameter sizes, the induced drag is integrally reduced, so thatthe lift force is improved, and the power coefficient is increased.

The flapping-wing fling water automobile includes engine, double-blade air screw propeller, right and left hydraulic screw propellers, right and left wings, control system, safety lifesaving equipment, and four-wheel undercarriage, hanging damper and fuselage, with the wings being connected to the fuselage via mechanical and hydraulic mechanism. The present automobile is one traffic facility for land, water and air use simultaneously, and has high efficiency and maneuverability. Its wings may be folded for land running.