Structural scheme for actively changing torsion shape of wing

Abstract

The invention discloses a structural scheme for actively changing the torsion shape of a wing, and belongs to the technical field of morphing aircraft structural design, and the structural scheme is specifically as follows: when a driving device drives gear screws to rotate, the gear screws of upper and lower edge strips generate axial forces in opposite directions to form a couple, and a spar of a torsion deformation section is driven to deflect around a hinge point; front and rear spars of the wing respectively deflect upwards and downwards around hinge points, and skins on the upper and lower surfaces of the wing limit the distance between edge strips of the front and rear spars to be unchanged, so that the wing generates torsional deformation. The torsional deformation angle is measured through a pull rope displacement sensor to obtain the moving distance of a gear screw rod on a deformed wing spar relative to a nut, the deflection angle of a front beam and a rear beam is calculated according to the height of a wing spar web, and the torsional shape of the wing is obtained by combining the chordwise distance between the front beam and the rear beam. According to the structure capable of actively changing the torsion shape of the wing, the rolling maneuvering efficiency of an aircraft is effectively improved, the distribution of aerodynamic loads is improved, and the loads at the root of the wing are reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of variant aircraft structure design, and in particular relates to a structural solution for actively changing the torsion shape of a wing. Background Art

[0002] During flight, the morphing aircraft actively changes its aerodynamic shape according to the surrounding environment, so that the aircraft can maintain optimal flight performance under different flight conditions. At present, the research direction of morphing aircraft mainly focuses on changing the wing area, wingspan, wing chord length, wing sweep angle, and wing leading and trailing edge curvature. In order to effectively improve the efficiency of wing roll maneuvers and improve the static aeroelastic effect, researchers have conducted in-depth research on wing torsion deformation technology.

[0003] Adjusting the torsional shape of the wing can improve the efficiency of the aircraft's rolling maneuvers, and can also effectively improve the aileron reaction effect and static aeroelastic effect; by changing the distribution of the wing leading edge torsion angle, the wing aerodynamic load distribution can be improved and the wing root load can be reduced, thereby effectively increasing the service life of the structure; in addition, the active torsional deformation of the wing combined with the leading and trailing edge deflection increases the deformation combination of the wing.

[0004] The present invention proposes a structural scheme for actively changing the torsional shape of the wing. The structural scheme can realize active torsional deformation of the wing through differential deformation of the front and rear beams, effectively improve the rolling maneuver efficiency of the aircraft, improve the distribution of aerodynamic loads, reduce the load at the root of the wing, optimize the aerodynamic characteristics of the wing, and increase the service life of the aircraft structure. Summary of the invention

[0005] The present invention realizes active torsional deformation of the wing structure through differential deformation of the front and rear beams, effectively improves the rolling maneuver efficiency of the aircraft, improves the distribution of aerodynamic loads, reduces the load on the root of the wing, and effectively increases the service life of the aircraft structure.

[0006] The present invention is achieved in this way

[0007] A structural scheme for actively changing the torsion shape of a wing, characterized in that the structural scheme includes a gear screw, a nut, a block, a support block, a pull rope displacement sensor, and a drive device; the scheme is as follows: a hinge point is set at a certain spanwise position of the front and rear beams of the wing, a section from the wing root to the hinge point is a fixed section, and a section from the hinge point to the wing tip is a torsion deformation section, the webs of the fixed section and the torsion deformation section are hinged by single and double ears, and the upper and lower edge strips on the left and right sides of the web are respectively connected by four gear screws, and the thread direction of the upper edge strip gear screw is opposite to the thread direction of the lower edge strip gear screw;

[0008] When the driving device drives the gear screw to rotate, the gear screws of the upper and lower edge strips will generate axial forces in opposite directions, forming a force couple, driving the spar of the torsional deformation section to deflect around the hinge point; the front and rear wing spars of the wing deflect upward and downward around the hinge point respectively, and the skin on the upper and lower surfaces of the wing restricts the distance between the front and rear beam edge strips to remain unchanged, causing the wing to torsion deformation; the torsional deformation angle of the wing is measured by the pull rope displacement sensor arranged on the front and rear beams to obtain the moving distance of the gear screw on the wing beam relative to the nut after deformation, and the deflection angle of the front and rear beams is calculated according to the height of the wing beam web, and the torsional shape of the wing is obtained by combining the chord distance between the front and rear beams;

[0009] The bottom surface of the pull-rope displacement sensor is fixed to the web of the torsion deformation section spar, and the side surface is fixed to the lower edge strip of the torsion deformation section spar. The measuring pull head of the sensor is fixed to the side surface of the lower edge strip of the fixed section spar. When the wing is horizontal and has no deflection, the measuring rope of the pull-rope displacement sensor is straightened horizontally, and the sensor value is l at this time. i0 ; When the wing is twisted, the output value of the pull rope displacement sensor is l i , the movement value of the gear screw Δl i = l i -l i0 (i=1 represents the data of the front spar; i=2 represents the data of the rear spar); The calculation can obtain the front and rear wing beam deflection angle (i=1 represents the data of the front spar; i=2 represents the data of the rear spar), and then the torsion angle at the span m of the torsional deformation section can be calculated. Among them, h is the height of the web of the beam, m is the span of the spar in the torsional deformation section, and f is the chord-wise distance between the front and rear spars.

[0010] Furthermore, when the drive device is used to drive the gear screw to rotate, the gear screws of the upper and lower edge strips are acted upon by the driving torque, generating axial forces of opposite directions in the thread pair, and the force couple formed by the axial forces of opposite directions drives the torsional deformation section of the wing beam to deflect around the hinge point, and the front and rear wing beams of the wing deflect upward and downward around the hinge point respectively, causing the wing to torsion deformation; wherein, the gear screw is used to replace the disconnected upper and lower edge strips, thereby ensuring the transmission of positive stress between the fixed section and the torsional deformation section; the fixed section of the wing beam and the web of the torsional deformation section are hinged by single and double ears, thereby ensuring the transmission of shear force;

[0011] When the front and rear beams deflect upward and downward around the hinge points respectively, due to the internal force of the skin, the chord-wise distance at the corresponding positions of the front and rear wing beams remains unchanged, causing the wing torsional deformation; at the same time, due to the action of the wing ribs, the cross-sectional shape of the wing after deflection can still remain unchanged, maintaining the aerodynamic shape required by the wing cross-section.

[0012] Furthermore, the nut is fixed to the edge strip of the torsional deformation section wing beam, and the bottom surface of the nut is flush with the beam cross section; the support block is fixed to the edge strip of the fixed section wing beam, and the bottom surface of the support block is flush with the beam cross section; the gear screw passes through the circular through hole of the support block, the circular boss contacts the bottom surface of the support block, and the threaded section is adapted to the nut; the stop block is fixed to the edge strip of the fixed section wing beam, so that the smooth end of the gear screw can extend into the circular depression of the stop block; wherein the nut, the circular through hole on the support block, the gear screw and the circular depression on the stop block are coaxial; when the gear screw rotates, the support block prevents the gear screw from axial displacement, and the stop block prevents the gear screw from axial displacement and radial swing.

[0013] Furthermore, the bottom surface of the pull rope displacement sensor is adhered to the web of the torsional deformation section wing beam, and the side surface is fixed to the lower edge strip of the torsional deformation section wing beam. The measuring pull head is fixed to the lower edge strip of the fixed section wing beam, and is used to measure the movement distance of the gear screws on the front and rear beams relative to the nut; the driving device includes a motor, a primary transmission shaft, a secondary transmission shaft and a tertiary transmission shaft; the motor and each level of transmission shaft are installed on the fixed section wing beam; after the motor is started, the four gear screws are synchronously subjected to the same driving torque through the transmission shaft.

[0014] Furthermore, the gear screw is divided into six sections; the first section is a threaded section that matches the nut; the second section is a cylindrical section; the third section is a circular boss, the top surface of the circular boss contacts the bottom surface of the support block; the fourth section is a cylindrical section; the fifth section is a gear, which is used to cooperate with the driving device to transmit the force; the sixth section is a cylindrical section, the end of which extends into the circular depression of the stop block.

[0015] Furthermore, the outer contour of the nut is a quadrangular prism, the side surface one of the nut is fixedly connected to the web of the torsional deformation section wing beam, the adjacent side surface of the side surface one of the nut is fixedly connected to the upper (lower) edge strip, the nut is adapted to the threaded section of the gear screw, and the thread directions of the nut at the upper and lower edge strips are opposite; the distance between the center of the threaded through hole and the adjacent side surface of the side surface one of the nut is x, and the distance from the side surface one of the nut is y.

[0016] Furthermore, the outer contour of the support block is a quadrangular prism, the side surface one of the support block is fixedly connected to the web of the fixed section wing beam, and the adjacent side surface of the side surface one of the support block is fixedly connected to the upper (lower) edge strip; a circular through hole is arranged on the bottom surface of the support block, the center of which is located on the bottom surface, the distance from the adjacent side surface of the side surface one of the support block is x, the distance from the side surface one of the support block is y, and the diameter is adapted to the cylindrical section of the gear screw; the gear screw passes through the circular through hole so that the circular boss of the gear screw contacts the bottom surface of the support block.

[0017] Furthermore, the outer contour of the block is the same as that of the support block, the side surface one of the block is fixedly connected to the web of the fixed section wing beam, the adjacent side surface of the side surface one of the block is fixedly connected to the upper (lower) edge strip, and a circular depression is arranged on one of its bottom surfaces, the distance between the center of the circle and the adjacent side surface of the side surface one of the block is x, and the distance between the center of the circle and the side surface one of the block is y, and the diameter is adapted to the cylindrical section of the gear screw, so that the smooth end of the gear screw can extend into the depression, thereby preventing the screw from axial displacement and radial swinging.

[0018] Furthermore, the front and rear wing beams are respectively equipped with a set of driving devices, each of which is composed of a motor, a primary transmission shaft, a secondary transmission shaft and two tertiary transmission shafts; after the motor is started, the driving torque is transmitted to the primary transmission shaft, and then transmitted to the secondary transmission shaft through the meshing of the primary gear and the secondary input end gear, and the driving torque on the secondary transmission is transmitted to the two tertiary transmission shafts through the meshing of the secondary output end gear and the two tertiary input end gears, and the two tertiary transmission shafts transmit the driving torque to the gear screws through the meshing of the gears on the tertiary output end gear and the gear screws, and the four gear screws are synchronously subjected to the same driving torque; the front and rear beams are driven in coordination, and when the driving device drives the front and rear wing beams to deflect upward and downward around the hinge point respectively, the skin on the upper and lower surfaces of the wing limits the distance between the front and rear beam edge strips to remain unchanged, so that the wing produces torsional deformation. The skin is connected to the front and rear beams through ribs.

[0019] The beneficial effects of the present invention compared with the prior art are:

[0020] The present invention realizes active torsional deformation of the wing structure through differential deformation of the front and rear beams, effectively improves the rolling maneuver efficiency of the aircraft, improves the distribution of aerodynamic loads, reduces the load on the root of the wing, and effectively increases the service life of the aircraft structure.

[0021] The structure for actively changing the torsion shape of the wing proposed in the present invention effectively improves the rolling maneuver efficiency of the aircraft, improves the distribution of aerodynamic loads, and reduces the load on the root of the wing. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 A schematic diagram of the torsional deformation of a wing in a structural solution of actively changing the torsional shape of a wing according to the present invention;

[0023] Figure 2 A schematic diagram of the differential deflection of the front and rear beams in a structural solution for actively changing the torsion shape of a wing according to the present invention;

[0024] Figure 3 It is a schematic diagram of the connection between the fixed section and the torsion deformation section wing beam in a structural solution of actively changing the torsion shape of the wing of the present invention;

[0025] Figure 4A schematic diagram of a gear screw in a structural solution for actively changing the torsion shape of a wing of the present invention;

[0026] Figure 5 This is a schematic diagram of the installation of a support block in a structural solution of actively changing the torsion shape of a wing of the present invention;

[0027] Figure 6 A schematic diagram of a support block in a structural solution for actively changing the torsion shape of a wing according to the present invention;

[0028] Figure 7 This is a schematic diagram of sensor measurement in a structural solution for actively changing the torsional shape of a wing of the present invention. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical solution and effect of the present invention clearer and more specific, the present invention is further described in detail by enumerating examples below. It should be noted that the specific implementation described here is only used to explain the present invention and is not used to limit the present invention.

[0030] The present invention proposes a structural scheme for actively changing the torsional shape of the wing. The scheme is suitable for double-beam wings. A hinge point is set at a certain spanwise position of the front and rear beams of the wing. The section from the wing root to the hinge point is a fixed section, and the section from the hinge point to the wing tip is a torsional deformation section. The webs of the fixed section and the torsional deformation section are hinged by single and double ears. The upper and lower edges on the left and right sides of the web are respectively connected by four gear screws. The thread direction of the upper edge gear screw is opposite to that of the lower edge gear screw. When the driving device drives the gear screw to rotate, the gear screws of the upper and lower edges will generate axial forces in opposite directions to form a force couple, driving the wing beam of the torsional deformation section to deflect around the hinge point; and the front and rear spars of the wing deflect upward and downward respectively around the hinge point. The skin on the upper and lower surfaces of the wing limits the distance between the front and rear beam edges to remain unchanged, so that the wing produces torsional deformation, such as Figure 2 This solution allows the wing to flexibly adjust the twist angle according to demand during flight, thereby optimizing the maneuverability of the aircraft.

[0031] The structure of the present invention is mainly composed of a gear screw, a nut, a stopper, a support block, a pull rope displacement sensor and a driving device. Figure 3As shown. The nut is fixed on the edge strip of the torsional deformation section wing beam, and the bottom surface of the nut is flush with the beam section; the support block is fixed on the edge strip of the fixed section wing beam, and the bottom surface of the support block is flush with the beam section; the gear screw passes through the circular through hole of the support block, the circular boss contacts the bottom surface of the support block, and the threaded section fits the nut; the stopper is fixed on the edge strip of the fixed section wing beam, so that the smooth end of the gear screw can extend into the circular depression of the stopper. Among them, the nut, the circular through hole on the support block, the gear screw and the circular depression on the stopper are coaxial. When the gear screw rotates, the support block prevents the gear screw from axial displacement, and the stopper prevents the gear screw from axial displacement and radial swing. The pull rope displacement sensor consists of a pull rope displacement sensor and a pull rope displacement sensor. The bottom surface of the pull rope displacement sensor is attached to the web of the torsion deformation section spar, and the side surface is fixed to the lower edge strip of the torsion deformation section spar. The measuring pull head is fixed to the lower edge strip of the fixed section spar, which is used to measure the moving distance of the gear screw on the front and rear beams relative to the nut. The drive device consists of a motor, a primary transmission shaft, a secondary transmission shaft, and a tertiary transmission shaft. The motor and the transmission shafts of each level are installed on the fixed section spar. After the motor is started, the four gear screws are synchronously subjected to the same driving torque through the transmission shaft.

[0032] Gear screw Figure 4 As shown, it is divided into six sections. The first section is a threaded section that fits the nut; the second section is a cylindrical section; the third section is a circular boss, the top surface of which contacts the bottom surface of the support block; the fourth section is a cylindrical section; the fifth section is a gear, which is used to cooperate with the driving device to transmit the force; the sixth section is a cylindrical section, the end of which extends into the circular depression of the stopper.

[0033] The outer contour of the nut is a quadrangular prism. The side surface of the nut is fixedly connected to the web of the torsional deformation section spar. The adjacent side surface of the side surface of the nut is fixedly connected to the upper (lower) edge strip. The nut is adapted to the threaded section of the gear screw, and the thread directions of the nut at the upper and lower edge strips are opposite. The distance between the center of the threaded through hole and the adjacent side surface of the side surface of the nut is x, and the distance from the side surface of the nut is y. Figure 6 shown.

[0034] The outer contour of the support block is a quadrangular prism, the side surface of the support block is fixedly connected to the web of the fixed section spar, and the adjacent side surface of the side surface of the support block is fixedly connected to the upper (lower) edge strip; Figure 5 As shown. A circular through hole is set on the bottom surface of the support block, the center of which is located on the bottom surface, the distance from the adjacent side surface of the support block side one is x, the distance from the side surface of the support block side one is y, and the diameter is adapted to the cylindrical section of the gear screw. The gear screw passes through the circular through hole so that the circular boss of the gear screw contacts the bottom surface of the support block, as shown. Figure 6 shown.

[0035] The outer contour of the stopper is the same as that of the support block. The side surface of the stopper is fixedly connected to the web of the fixed section spar. The adjacent side surface of the side surface of the stopper is fixedly connected to the upper (lower) edge strip. A circular depression is arranged on one bottom surface. The distance between the center of the circle and the adjacent side surface of the side surface of the stopper is x, and the distance between the center of the circle and the side surface is y. The diameter is adapted to the cylindrical section of the gear screw, so that the smooth end of the gear screw can extend into the depression, which prevents the screw from axial displacement and radial swing. Figure 6 shown.

[0036] The front and rear wing beams are respectively equipped with a set of drive devices, each of which consists of a motor, a primary transmission shaft, a secondary transmission shaft and two tertiary transmission shafts. After the motor is started, the driving torque is transmitted to the primary transmission shaft, and then transmitted to the secondary transmission shaft through the meshing of the primary gear and the secondary input end gear, while the driving torque on the secondary transmission is transmitted to the two tertiary transmission shafts through the meshing of the secondary output end gear and the two tertiary input end gears. The two tertiary transmission shafts transmit the driving torque to the gear screws through the meshing of the gears on the tertiary output end gear and the gear screws, and the four gear screws are synchronously subjected to the same driving torque. The front and rear beams are driven in coordination. When the drive device drives the front and rear wing beams to deflect upward and downward around the hinge point respectively, the skin on the upper and lower surfaces of the wing limits the distance between the front and rear beam edges to remain unchanged, causing the wing to produce torsional deformation. The skin is connected to the front and rear beams through ribs.

[0037] The torsional deformation angle of the wing is measured by the pull-wire displacement sensor arranged on the front and rear beams. The moving distance of the gear screw on the spar relative to the nut after deformation is obtained. The deflection angle of the front and rear beams is calculated according to the height of the spar web. The torsional shape of the wing is obtained by combining the chord distance between the front and rear beams. The bottom surface of the pull-wire displacement sensor is fixed to the web of the torsional deformation section spar, and the side surface is fixed to the lower edge strip of the torsional deformation section spar. The measuring pull head of the sensor is fixed to the side of the lower edge strip of the fixed section spar. Figure 7 As shown in the figure, when the wing is horizontal and without deflection, the measuring rope of the pull rope displacement sensor is stretched horizontally, and the sensor value is l i0 ; When the wing is twisted, the output value of the pull rope displacement sensor is l i , the movement value of the gear screw Δl i = l i -l i0 (i=1 represents the data of the front spar; i=2 represents the data of the rear spar). The calculation can obtain the front and rear wing beam deflection angle (i=1 represents the data of the front spar; i=2 represents the data of the rear spar), and then the torsion angle at the span m of the torsional deformation section can be calculated. Among them, h is the height of the web of the beam, m is the span of the spar in the torsional deformation section, and f is the chord-wise distance between the front and rear spars.

[0038] The main working principle is: when the drive device is used to drive the gear screw to rotate, the gear screws of the upper and lower edge strips are acted upon by the driving torque, generating axial forces in opposite directions in the thread pair. The force couple formed by the axial forces in opposite directions drives the torsional deformation section of the wing beam to deflect around the hinge point, and the front and rear wing beams of the wing deflect upward and downward around the hinge point respectively, causing the wing to torsion deformation, such as Figure 1 As shown. Among them, the gear screw is used to replace the disconnected upper and lower edge strips to ensure the transmission of positive stress between the fixed section and the torsion deformation section; the web of the fixed section and the torsion deformation section of the wing beam is hinged by a single and double ear to ensure the transmission of shear force. In addition, when the front and rear beams are deflected upward and downward around the hinge point respectively, the chord distance at the corresponding position of the wing beam before and after the deflection remains unchanged due to the in-plane force of the skin, causing the wing to torsion deformation; at the same time, due to the action of the ribs, the cross-sectional shape of the wing after deflection can still remain unchanged, maintaining the aerodynamic shape required by the wing cross-section.

[0039] The following is a detailed description of the present invention using specific data examples.

[0040] In this embodiment, a double-beam wing of airfoil NACA0012 is selected, the relative thickness of the airfoil is 12%, the chord length is 1500mm, the span length is 5000mm, the front beam is arranged at 25% of the chord length of the airfoil, the rear beam is arranged at 65% of the chord length of the airfoil, and a hinge point is set at 3000mm from the wing root in the span direction, so that the wing section 2000mm long outside the hinge point can achieve torsional deformation. The front and rear wing spars are I-beams, the flange thickness is 5mm, the flange width is 84mm, the web thickness is 4mm, and the web height h=120mm.

[0041] Assuming that when the wing is twisted, the maximum bending moment at the hinge of the wing beam is 10000N·m, the bending moment borne by the front beam is 6000N·m, and the bending moment borne by the rear beam is 4000N·m; assuming that both the gear screw and the nut are made of alloy steel with a strength of about 800MPa, a thread lead angle of 2.5°, and an equivalent friction angle of 7°; the outer contour of the nut is a quadrangular prism of 20×36×24mm, 24mm is the length in the direction of the web height, 36mm is the length in the direction of the flange width, 20mm is the length in the direction of the gear screw, the inner hole diameter is 12mm, the distance from the center of the inner hole to the side one is x=12mm, and the distance to the side 2 is y=20mm, a trapezoidal tooth profile with a height of 1.5mm, a pitch of 2mm, and 10 thread turns. The diameter of the gear screw is 12mm, the length of the thread section is 50mm, the height is 1.5mm trapezoidal tooth profile, the pitch is 2mm, the number of thread turns is 20, and the distance between the gear screw and the thread section is 50mm. There is a boss with a diameter of 20mm and a thickness of 10mm. 20mm away from the boss is a standard spur gear with a pitch circle diameter of 20mm, a tooth thickness of 10mm, a number of teeth of 20, a module of 1, a length of the rear rod of the gear is 20mm, and the total length of the gear screw is 150mm; the block and support block are both 20×36×24mm four-piece Prism, 24mm is the length in the web height direction, 36mm is the length in the edge strip width direction, 20mm is the length in the gear screw direction, side 1 is fixed to the edge strip, side 2 is fixed to the web, on the bottom surface, with the point at a distance of x=12mm from side 1 and y=20mm from side 2 as the center of the circle, there is a depression with a diameter of 12mm and a depth of 5mm along the axis of the block, and there is a circular through hole with a diameter of 12mm along the axis of the support block; the nut at the upper edge strip of the front and rear beams is provided with positive thread, and the nut at the lower edge strip is provided with reverse thread. Among them, the distance between the nut and the support block is 50mm, that is, the distance between the upper and lower edge strips is 50mm. The fixed section wing beam and the torsional deformation section wing beam are hinged by single and double ears. The web of the fixed section wing beam is a single ear, and the web of the torsional deformation section wing beam is provided with double ears to ensure the transmission of shear force. According to the value of the allowable shear stress, the diameter of the pin at the hinge is determined to be 12mm, and the length is 16mm. The distance between the center of the pin hole on the single ear beam and the end face of the fixed section wing beam is 25mm.

[0042] The bottom of the pull-wire displacement sensor is fixed to the web of the torsion deformation section spar, and the side is fixed to the lower edge of the torsion deformation section spar. The axial distance between the outlet on the side and the nut is 100mm; the sensor's measuring pull head is fixed to the side of the lower edge of the fixed section spar, and the axial distance from the support block is 0. When the wing is horizontal and has no deflection, the value of the pull-wire displacement sensor is l i0 =150mm (i=1 represents the data of the front spar; i=2 represents the data of the rear spar), and the upward deflection of the spar is the positive direction.

[0043] In the pull-wire displacement sensor, the torsion angle is set, and the formula is used to calculate the value that the sensor should output after torsional deformation. In the current state, the output values ​​of the sensors on the front and rear wing beams are read to determine the driving state of the drive device on the wing (positive drive, negative drive, or maintaining the current flight state). If the aircraft needs to change the flight state, the front and rear beams are coordinated and driven, and the drive device drives the motors on the front and rear beams to start the front, and the drive torque is transmitted to the gear screw through the first, second, and third-level transmission shafts. The four gear screws are synchronously subjected to the same driving torque. The front and rear wing beams deflect upward and downward around the hinge point respectively, and at the same time, the pull-wire displacement sensor measures the moving distance of the gear screw relative to the nut. When the output values ​​of the pull-wire displacement sensors on the front and rear wing beams are equal to the set output displacement, the wing completes torsional deformation.

[0044] In order to increase the fixed area, the support block, stopper and nut are all in a quadrangular prism structure. At the same time, the disconnected upper and lower edges are replaced by gear screws to ensure the transmission of normal stress, and the webs of the fixed section and the torsional deformation section are hinged by single and double ears to ensure the transmission of shear force.

[0045] The skin is connected to the front and rear beams through the ribs, and after the front and rear beams are deflected, the chord length at the corresponding position of the spar will not change. At the same time, constrained by the ribs, the cross-sectional shape of the wing remains unchanged after deflection, ensuring the required aerodynamic shape of the wing cross-section.

[0046] This structural solution allows the wing to flexibly adjust the torsion angle as needed during flight, so as to optimize the maneuverability of the aircraft.

[0047] The above description is only a preferred embodiment of the present invention. It should be pointed out that a person skilled in the art can make several improvements without departing from the principle of the present invention, and these improvements should also be regarded as within the protection scope of the present invention.

Claims

1. A structural solution for actively changing the torsion shape of a wing, characterized in that: The structural scheme includes a gear screw, a nut, a stopper, a support block, a pull rope displacement sensor, and a drive device; the scheme is as follows: a hinge point is set at a certain spanwise position of the front and rear beams of the wing, a section from the wing root to the hinge point is a fixed section, and a section from the hinge point to the wing tip is a torsion deformation section, the webs of the fixed section and the torsion deformation section are hinged by single and double ears, and the upper and lower edge strips on the left and right sides of the web are respectively connected by four gear screws, and the thread direction of the upper edge strip gear screw is opposite to the thread direction of the lower edge strip gear screw; When the drive device drives the gear screw to rotate, the gear screws of the upper and lower slats will generate axial forces in opposite directions, forming a force couple, which drives the spar in the torsional deformation section to deflect around the hinge point; the front and rear wing spars of the wing deflect upward and downward around the hinge point respectively, and the skin on the upper and lower surfaces of the wing restricts the distance between the front and rear slats to remain unchanged, causing the wing to torsion deformation; The torsional deformation angle of the wing is measured by the pull-rod displacement sensor arranged on the front and rear beams to obtain the moving distance of the gear screw on the wing beam relative to the nut after deformation. The deflection angle of the front and rear beams is calculated according to the height of the wing beam web, and the torsional shape of the wing is obtained by combining the chord distance between the front and rear beams. The bottom surface of the pull rope displacement sensor is fixed to the web of the torsion deformation section spar, the side surface is fixed to the lower edge strip of the torsion deformation section spar, and the measuring pull head of the sensor is fixed to the side surface of the lower edge strip of the fixed section spar; When the wing is horizontal and without deflection, the measuring rope of the pull rope displacement sensor is stretched horizontally, and the sensor value is l i0 ; When the wing is twisted, the output value of the pull rope displacement sensor is l i , the movement value of the gear screw Δl i = l i -l i0 (i=1 represents the data of the front spar; i=2 represents the data of the rear spar); Depend on The calculation can obtain the front and rear wing beam deflection angle (i=1 represents the data of the front spar; i=2 represents the data of the rear spar), and then the torsion angle at the span m of the torsional deformation section can be calculated. Among them, h is the height of the web of the beam, m is the span of the spar in the torsional deformation section, and f is the chord-wise distance between the front and rear spars.

2. A structural solution for actively changing the torsion shape of a wing according to claim 1, characterized in that: When the drive device is used to drive the gear screw to rotate, the gear screws of the upper and lower edge strips are acted upon by the driving torque, generating axial forces of opposite directions in the thread pair. The force couple formed by the axial forces of opposite directions drives the torsional deformation section of the wing beam to deflect around the hinge point, and the front and rear wing beams of the wing deflect upward and downward around the hinge point respectively, causing the wing to torsion deformation; wherein, the gear screw is used to replace the disconnected upper and lower edge strips, thereby ensuring the transmission of positive stress between the fixed section and the torsional deformation section; the web of the fixed section of the wing beam and the torsional deformation section is hinged by single and double ears, thereby ensuring the transmission of shear force; When the front and rear beams deflect upward and downward around the hinge points respectively, due to the internal force of the skin, the chord-wise distance at the corresponding positions of the front and rear wing beams remains unchanged, causing the wing torsional deformation; at the same time, due to the action of the wing ribs, the cross-sectional shape of the wing after deflection can still remain unchanged, maintaining the aerodynamic shape required by the wing cross-section.

3. The structural solution for actively changing the torsion shape of a wing according to claim 1, characterized in that: The nut is fixed on the edge strip of the torsional deformation section wing beam, and the bottom surface of the nut is flush with the beam cross section; the support block is fixed on the edge strip of the fixed section wing beam, and the bottom surface of the support block is flush with the beam cross section; the gear screw passes through the circular through hole of the support block, the circular boss contacts the bottom surface of the support block, and the threaded section is adapted to the nut; the stop block is fixed on the edge strip of the fixed section wing beam, so that the smooth end of the gear screw can extend into the circular depression of the stop block; wherein the nut, the circular through hole on the support block, the gear screw and the circular depression on the stop block are coaxial; when the gear screw rotates, the support block prevents the gear screw from axial displacement, and the stop block prevents the gear screw from axial displacement and radial swing.

4. The structural solution for actively changing the torsion shape of a wing according to claim 1, characterized in that: The bottom surface of the pull rope displacement sensor is adhered to the web of the torsional deformation section wing beam, and the side surface is fixed to the lower edge strip of the torsional deformation section wing beam. The measuring pull head is fixed to the lower edge strip of the fixed section wing beam, and is used to measure the movement distance of the gear screws on the front and rear beams relative to the nut; the driving device includes a motor, a primary transmission shaft, a secondary transmission shaft and a tertiary transmission shaft; the motor and each level of transmission shaft are installed on the fixed section wing beam; after the motor is started, the four gear screws are synchronously subjected to the same driving torque through the transmission shaft.

5. The structural solution for actively changing the torsion shape of a wing according to claim 1, characterized in that: The gear screw is divided into six sections; the first section is a threaded section adapted to the nut; the second section is a cylindrical section; The third section is a circular boss, the top surface of which contacts the bottom surface of the support block; the fourth section is a cylindrical section; the fifth section is a gear, which is used to cooperate with the driving device to transmit the force; the sixth section is a cylindrical section, the end of which extends into the circular depression of the stopper.

6. The structural solution for actively changing the torsion shape of a wing according to claim 1, characterized in that: The outer contour of the nut is a quadrangular prism, the side surface one of the nut is fixedly connected to the web of the torsional deformation section wing beam, the adjacent side surface of the side surface one of the nut is fixedly connected to the upper (lower) edge strip, the nut is adapted to the threaded section of the gear screw, and the thread directions of the nut at the upper and lower edge strips are opposite; the distance between the center of the threaded through hole and the adjacent side surface of the side surface one of the nut is x, and the distance from the side surface one of the nut is y.

7. The structural solution for actively changing the torsion shape of a wing according to claim 1, characterized in that: The outer contour of the support block is a quadrangular prism, and the side surface of the support block is fixedly connected to the web of the fixed section wing beam, and the adjacent side surface of the side surface of the support block is fixedly connected to the upper (lower) edge strip; a circular through hole is arranged on the bottom surface of the support block, and the center of the circle is located on the bottom surface, and the distance from the adjacent side surface of the side surface of the support block is x, and the distance from the side surface of the support block is y, and the diameter is adapted to the cylindrical section of the gear screw; the gear screw passes through the circular through hole so that the circular boss of the gear screw contacts the bottom surface of the support block.

8. The structural solution for actively changing the torsion shape of a wing according to claim 1, characterized in that: The outer contour of the block is the same as that of the support block. The side surface of the block is fixedly connected to the web of the fixed section wing beam, and the adjacent side surface of the side surface of the block is fixedly connected to the upper (lower) edge strip. A circular depression is arranged on one of its bottom surfaces. The distance between the center of the circle and the adjacent side surface of the side surface of the block is x, and the distance between the center of the circle and the side surface of the block is y. The diameter is adapted to the cylindrical section of the gear screw, so that the smooth end of the gear screw can extend into the depression, thereby preventing the screw from axial displacement and radial swing.

9. The structural solution for actively changing the torsion shape of a wing according to claim 1, characterized in that: The front and rear wing beams are respectively equipped with a set of driving devices, each of which is composed of a motor, a primary transmission shaft, a secondary transmission shaft and two tertiary transmission shafts; after the motor is started, the driving torque is transmitted to the primary transmission shaft, and then transmitted to the secondary transmission shaft through the meshing of the primary gear and the secondary input end gear, and the driving torque on the secondary transmission is transmitted to the two tertiary transmission shafts through the meshing of the secondary output end gear and the two tertiary input end gears, and the two tertiary transmission shafts transmit the driving torque to the gear screws through the meshing of the gears on the tertiary output end gear and the gear screws, and the four gear screws are synchronously subjected to the same driving torque; the front and rear beams are driven in coordination, and when the driving device drives the front and rear wing beams to deflect upward and downward around the hinge point respectively, the skin on the upper and lower surfaces of the wing limits the distance between the front and rear beam edges to remain unchanged, so that the wing produces torsional deformation. The skin is connected to the front and rear beams through ribs.

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