140results about How to "Improve aerodynamic characteristics" patented technology

The invention provides a skin of a morphing wing, which is made from fiber-reinforced composite material (1). The skin is characterized in that: a shape memory alloy driver (2) is arranged between the two layers of the fiber-reinforced composite material (1); the wave trough of the upper layer fiber-reinforced composite material is internally filled with silica-based rubber (3) for meeting the requirements of smoothness, continuity and whole gas tightness on the surface of the wing; the fiber-reinforced composite material (1) and the shape memory alloy driver (2) are jointly pressed into to a corrugated structure under room temperature; the shape memory alloy driver (2) is in the shape of a high-temperature memory straight line; and the silica-based rubber (3) can be solidified under normal temperature. The invention also provides a drive method of the skin of the morphing wing. The skin of the morphing wing has the corrugated structure, thereby having high flexibility, large morphing amount and fast morphing response speed on the morphing direction, having high carrying capability on the perpendicular morphing direction, and having simple structure, light weight and reliable performance.

The invention provides a variable camber self-adaptive wing structure, the whole wing is divided into wing leading edge section, wing trailing edge section and each spanwise fixed wing structure section therebetween, wherein the The wing structure segment connected to the edge structure segment is fixed to the fuselage through the spar, and these structural segments are connected to each other by a double-fin structure. This double-fin structure allows the force between the wing structure segments to pass through the ribs. The transmission of the contact surface avoids the influence of the hinge gap of the wing deformation mechanism on the deformation, and improves the structural weight and complexity increased to meet the structural strength requirements of the wing. Use the control system of the aircraft to control and change the camber of the wing, so that the aircraft can obtain the optimal aerodynamic efficiency at different speeds and angles of attack. This adaptive wing with variable camber can greatly improve the lift. Enhancing the maneuverability of the aircraft and improving the stall characteristics can greatly improve the endurance time of the aircraft and the stability of the aircraft itself.

The invention provides a low-Reynolds-number wing section matched with a full-wing solar unmanned aerial vehicle. The low-Reynolds-number wing section is characterized in that the relative thickness of the wing section is 11%-13%, the maximum camber of the wind section is 2%-4%, and a chordwise position with the maximum camber is 25%-30%; the wing section has a single bent outline in a 70% chordwise range from a front edge. With a full-aircraft matching design, the checking of pneumatic characteristics of a pair of wing sections is finished by checking the corresponding pneumatic characteristics of the wing sections and applying the two wing sections to the full-wing solar unmanned aerial vehicle, and the low-Reynolds-number wing section shows good pneumatic characteristics and engineering enforceability and can meet application demands on low Reynolds number, high lift force and lift-to-drag ratio and large relative thickness of the full-wing solar unmanned aerial vehicle.

A method for aerodynamic robust optimization design of thick airfoil on that inner side of wind turbine blade According to the uncertainty of Reynolds number of incoming flow in the actual operation of wind turbine blades, Taking the maximum lift coefficient of airfoil and the probability statistics of stall characteristic parameters under random Reynolds number as the characteristic parameters ofairfoil affected by Reynolds number uncertainty, the robust optimization objective function of thick airfoil is formed by using the weight coefficient method and the aerodynamic lift characteristicsof airfoil at high angle of attack. A robust optimization design method for thick airfoil is proposed based on the geometrical characteristics of airfoil and genetic algorithm. The numerical prediction and evaluation of the optimization result of the concrete case show that the robust optimization design method of the large-thickness airfoil proposed by the invention can make the new airfoil obtain a high aerodynamic lift level in the range of a large angle of attack, and further improve the robustness of the aerodynamic characteristics of the airfoil with Reynolds number change, thereby realizing the design requirements.

The invention belongs to the technical field of cross of bionics and aerodynamics, and discloses a novel feather-wing bionic ventilation flapping wing system and a multi-vortex interference mechanismanalysis method, so as to derive and describe a motion equation set and capture the vortex motion tracks. The method is characterized by analyzing the influence rules of the dynamic aerodynamic characteristics, the flow rules, the dynamic vortex structures and the vortex interference characteristics of the ventilation flapping wing system. The invention provides a multi-body model design of the novel feather wing bionic ventilation flapping wing system, and provides an aerodynamic shape and a flapping scheme, so that the design thought of the micro flapping-wing aircraft is expanded, and the aerodynamic characteristics are improved, the influence rules of the parameter changes of different fluttering frequencies, fluttering angles, fluttering inclination angles, Reynolds numbers and the like on the lift resistance characteristics, the thrust characteristics, the flow rules, the dynamic vortex structures and the like of the ventilation flapping wing layout are concluded and summarized,and the dynamic aerodynamic force between the moving winglet and the main flapping wing and a multi-vortex interference mechanism of the dynamic aerodynamic force are summarized.

The invention discloses a solar united wing unmanned aerial vehicle and a control method thereof. The united wing unmanned aerial vehicle comprises a tail supporting rod, wings and pod assemblies, thewings comprise front wings, back rings and a vertical fin, and a left front wing, a wing body and a right front wing are integrated to form the front wings; the left front wing and the right front wing are symmetrically arranged at the two sides of the wing body, the wing body is fixedly connected with the tail supporting rod, and a left back wing and a right back wing which are symmetrically arranged are integrated to form the back wings; the back wings are located above the tail supporting rod, the connecting joint of the left back wing and right back wing is connected to the tail portion of the tail supporting rod through the vertical fin, the outer side ends of the left back wing and right back wing are in overlapping connection to the middles of the left front wing and right front wing respectively through streamline vertical end plates to form united wings, and four pod assemblies are arranged and respectively located at the lower portions of the front wings and back wings. Thesolar united wing unmanned aerial vehicle can solve the problems that an existing unmanned aerial vehicle with the quite high aspect ratio is poor in structure intensity and difficult in design, is only controlled by an electromotor, and cannot cooperate with a steering engine to achieve comprehensive control.

The invention discloses a power-operated tail-sitting type mixed layout vertical take-off and landing aircraft. The power-operated tail-sitting type mixed layout vertical take-off and landing aircraft is composed of a fuselage, airfoils, motors, propellers and landing gears; the fuselage axis coincides with the OX axis of a body axial system, the projections of the fuselage axis and the OX axis in an XOY plane of the body axial system are distributed in an X shape; each airfoil on the fuselage is divided into several sections, sweepback angles and dihedral angles of all the sections are different from one another, and excellent pneumatic performance and maneuvering performance are achieved through positively-curved airfoil profiles and negatively-curved airfoil profiles; four sets of propeller-motor power systems are installed on the four airfoils correspondingly, and the distances between the positions where the propeller-motor power systems are located and the OX axis of the body axial system are the same; and four power devices take off in an X-shaped quad-rotor mode in the vertical take-off and landing processes and complete conversion operation to enter a cruising state through different tensile forces of the motors or by being matched with maneuvering surfaces, and required maneuvering is completed through tensile force changing of the motors in the whole process. The power devices of the aircraft are simple, the control mode is reliable, propeller slipstreams can be effectively utilized, and the aircraft is suitable for serving as flying platforms of a tail-sitting type vertical take-off and landing unmanned aerial vehicle.

The invention relates to a method for controlling the thermal effluents of an aircraft including an airframe (110) and at least one propulsion unit (112), wherein said at least one propulsion unit (112) includes a turbomachine (116) supplied with fuel via a fuel supply circuit (122) extending from a tank (124) provided at the airframe (110), said airframe (110) including at least one thermal effluent source (134), characterised in that it comprises scattering at least partially, at the level of at least one propulsion unit (112), the thermal effluents generated at the airframe (110) by using the fuel used for supplying the turbomachine (116) as a heat-carrier fluid.

To effectively perform lightning protection in a blade for wind power generation and to prevent the blade from being damaged when arresting lightning. The lightning protection structure of the blade for wind power generation includes a conductive lightning receptor 1 attached to a part of the blade for wind power generation, and a ceramic member 10 interposed between at least surface-layer portions of the lightning receptor 1 and the blade 5. Therefore, an electric field is likely to concentrate at an interface between the ceramic member 10 having excellent heat resistance and the lightning receptor 1, so that it is possible to effectively prevent the blade 5 from being damaged due to a concentration of the electric field at the interface of the blade 5 attached with the lightning receptor 1 when arresting the lightning.

An end configuration for a bat includes in one embodiment an end cap that has a base that is shaped to fit within the open end of the bat thereby to attach the end cap to the bat. The end cap also includes a convexly contoured end surface that is exposed when the end cap is attached to the bat. The end surface is roughened to reduce the aerodynamic drag when the bat is swung, thereby to increase the momentum of the bat for a given amount of force applied to swing the bat.

The invention discloses a rotary aircraft wing folding and unfolding mechanism and a folding method thereof, which mainly solve the problem existing in the prior art that the conventional folding mechanism occupies the internal space of the wing, the moving mechanism is not compact and the wing surface is uneven due to the single rotating hinge. The rotary aircraft wing folding and unfolding mechanism comprises an inner wing, an outer wing, a driving gear, and a folding actuator for driving the driving gear; an inner wing link mechanism and an outer wing link mechanism are respectively articulated with the opposite surfaces of the inner wing and the outer wing; a driven gear A and a driven gear B are respectively fixedly connected to the inner wing link mechanism and the outer wing link mechanism; the driving gear, the driven gear A and the driven gear B are all incomplete gears; and at different stages, the driving gear is engaged with the driven gear A or the driven gear B. Through the solution, the invention achieves the objectives of even wing surface and compact structure, having high practical value and popularization value.

The invention provides an integrated thermal protection structure for the leading edge of a hypersonic aircraft pneumatic rudder, which is integrally designed and comprises a heat protection skin, a heat pipe, a heat absorption device and a heat insulation layer, wherein the heat protection skin is arranged on the outer surface of the leading edge of the pneumatic rudder; the heat absorption device is arranged on the inner surface of the heat protection skin; the heat pipe is fixedly connected with the heat absorption device; the heat pipe is arranged on the inner surface of the heat absorption device; and the heat insulation layer is fixedly arranged on the inner surface of the heat pipe. The invention also provides a coolant circulating system and a hypersonic aircraft. According to theinvention, the deformation of the leading edge of the aircraft pneumatic rudder is small, the heat flow density is small, the aerodynamic characteristic of the aircraft with high lift-resistance ratioand the operability of the pneumatic rudder are kept, the problems of material failure caused by large heat flow of the leading edge of the aircraft pneumatic rudder and poor pneumatic load bearing capacity caused by high flying speed are solved, the extreme distribution of the temperature of the leading edge of the pneumatic rudder is avoided, and the long-time thermal insulation of the aircraftis achieved.

The invention relates to a flow guide type air barrier. An air barrier support is composed of upright columns, an upper beam and a lower beam, and forms an air barrier unit. The dip angle between the axis of each upright column of the air barrier and a plumb line ranges from 1 degrees to 45 degrees. Multiple rows of transverse air barrier bars and multiple columns of vertical air barrier bars are distributed in the air barrier support and are connected smoothly on the windward side to form a whole air barrier face. The vertical air barrier bars are arranged continuously at equal intervals between the upper beam and the lower beam, and dip angles ranging from 1 degree to 45 degrees are formed between the vertical air barrier bars and the plumb line. The upper beam and the lower beam of the air barrier can be integrated or combined. Flow guide air barrier bars are additionally arranged on the windward side of the whole air barrier face. By means of the air barrier, a part of air flow can bypass an air barrier plate, so that the flow guide type air barrier has a wind shielding function as a common air barrier and also has an air flow guide function. When the air barrier is applied to a noise barrier, wind resistance of the noise barrier can be improved. By means of the air barrier, the pneumatic characteristics o f a bridge structure can be improved, and wind resistance of the bridge structure is improved.

The application of the invention provides a wind turbine blade and a wind turbine. The wind turbine blade includes a blade body and at least one flap flexibly mounted at the trailing edge of the blade body, wherein the flap is provided with two panels and an elastic component; the two panels are oppositely fixed on the two sides of the elastic component and rotate by taking the elastic component as a shaft, so as to form a meshed clamping structure at one end of the elastic component and forms a folding dovetail structure at the other end of the elastic component. The flap is meshed with the trailing edge of the blade body through the clamping structure, the clamping structure is fastened with the trailing edge of the blade body through the thrust applied on the inner side of the dovetail structure, of the elastic component, so that the aerodynamic characteristics of the blade body can be improved and further chattering of the blade body is reduced.

A pulsating heat pipe active thermal protection structure coupled with ablative resistant materials comprises a thermal grooming device and ablative resistant materials, wherein the ablative resistantmaterials are coated on the periphery of the thermal grooming device and comprise an inner layer and an outer layer; the inner layer is a flexible foam, and the outer layer is a high thermal conductivity carbon/carbon material; the thermal grooming device comprises a cooling panel, a pulsating heat pipe group and a phase change cold storage box; the cooling panel is bonded with the ablative resistant materials; the pulsating heat pipe group is welded with the cooling panel; the phase change cold storage box is welded with the cooling panel and fixed with the end frame of the aircraft; and thepulsating heat pipe extends into the phase change cold storage box. The pulsating heat pipe active thermal protection structure coupled with ablative resistant materials combine ablation-resistant material with the thermal grooming device. By means of the active thermal protection structure of the sharp lead edge of the aircraft, ablation is reduced or no ablation occur, and the aerodynamic shapeof the aircraft is changed little, and the aerodynamic characteristic of the aircraft with high lift-to-drag ratio is maintained, and the problem of material failure caused by the local high heat ofthe aircraft is solved, and the extreme distribution of temperature is avoided, and the long-time heat insulation is realized.

The invention discloses an all-directional wideband antenna which has the same shape with an installation surface structure; the all-directional wideband antenna comprises a coaxial feed joint, a cylindrical back chamber (1), a glass fiber reinforced plastic cover (2), a metal upper cover (3), a metal lower cover (7), a sleeve (8), three groups of short circuit columns and three supporting frames; three groups of short circuit columns are arranged between the metal upper cover (3) and the metal lower cover (7); the three supporting frames are arranged on the internal wall of the sleeve (8) which is welded inside the cylindrical back chamber (1) and is positioned at the jointing of a conical bottom surface (101) and a transition section (103); the glass fiber reinforced plastic cover (2) is arranged on a flange platform (104) of the cylindrical back chamber (1); the frontal disc (35) of the metal upper cover (3) is attached to the glass fiber reinforced plastic cover (2); the frontal disc (35) of the metal upper cover (3) is attached to the glass fiber reinforced plastic cover (2), thus leading the all-directional wideband antenna to be internally embedded into the installation plane of a movable platform so as to form the structural conformality.

The invention discloses a structure for a trailing edge slat of a thin-airfoil-profile aircraft and a linkage method of the structure. The trailing edge slat comprises a main foil and two sub-foils, wherein two flap runners are symmetrically arranged at the two sides of the trailing edge slat, sub-foil rotating shaft holes are respectively formed in the two flap runners, and a sub-foil rotating shaft penetrates through the sub-foil rotating shaft holes and is rotatably connected with the front ends of the two sub-foils; main foil rotation pin slide rings are arranged in the sub-foils, and the front end of the main foil is in sliding and rotating connection with the main foil rotation pin slide rings through a main foil rotation pin; the two ends of the main foil rotation pin are in sliding connection with arc-shaped main foil sliding grooves in the flap runners; a driving lug which is located at a joint gap of the two sub-foils is arranged at the front end of the main foil and is hinged to a telescopic rod which is located on an actuating cylinder between the two sub-foils, and a cylinder body of the actuating cylinder is hinged to an airfoil. According to the structure for the trailing edge slat of the thin-airfoil aircraft and the linkage method of the structure, the linkage of the main foil and the sub-foils in the trailing edge slat is realized through one actuating cylinder, the whole mechanism can be completely hidden in the airfoil of the trailing edge slat, and the smoothness of the appearance of the whole trailing edge slat is ensured, so that the aerodynamic characteristics of the trailing edge slat are improved.