Variable wing type structure of vertical fixed wing
The variable wing configuration in VTOL drones addresses inefficiencies by enabling rapid and stable transitions between flight modes, improving operational flexibility through integrated folding and rotating components.
Patent Information
- Application Number
- CN202421893300.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-06
- Publication Date
- 2025-07-15
- Estimated Expiration
- 2034-08-06
AI Technical Summary
The hanging fixed-wing drone cannot switch quickly back and forth in the fixed-wing and multi-rotor structure, resulting in slow response, convenient and complexity, and insufficient application flexibility.
The variable airfoil structure of the hanging fixed wing is adopted, including the fuselage, the fixed wing assembly, the folding assembly and the rotor assembly. The folding assembly realizes the fast and stable switching of the fixed wing assembly and the rotor assembly. Combined with the design of the hinge and the universal joint, the smooth transition of the drone between different flight modes is achieved.
It realizes fast and convenient switching between fixed wing and multi-rotor modes of drones, improves the application flexibility of drones, and combines high-speed flight and fixed-point hovering.
Smart Images
Figure CN223101040U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of unmanned aerial vehicles, and more specifically, to a vertical take-off fixed-wing variable airfoil structure. Background Art
[0002] At present, there are various types of unmanned aerial vehicles, including fixed-wing, multi-rotor, and vertical take-off fixed-wing. Among them, fixed-wing unmanned aerial vehicles fly stably and at high speeds, but they cannot hover in place, which is an application defect of fixed-wing unmanned aerial vehicles; multi-rotor unmanned aerial vehicles can overcome the hovering defect of fixed-wing unmanned aerial vehicles, but they cannot reach the flight speed of fixed-wing unmanned aerial vehicles; vertical take-off fixed-wing unmanned aerial vehicles combine the advantages of the former two, and can not only meet the hovering need, but also maintain high-speed flight and stable flight.
[0003] In the prior art, vertical take-off fixed-wing unmanned aerial vehicles are directly added with a multi-rotor structure on the fixed wing, and two power systems are used to control the multi-rotor structure and the fixed wing respectively, and switch back and forth between the two power control systems. In actual application, not only is the structure complex, but also the efficiency is low, and the effects of fast response and convenient operation cannot be achieved, making the application flexibility of vertical take-off fixed-wing unmanned aerial vehicles insufficient.
[0004] How to solve the problem that vertical take-off fixed-wing unmanned aerial vehicles cannot quickly switch back and forth between the fixed wing and the multi-rotor structure, resulting in slow response and complex operation of the unmanned aerial vehicle, and insufficient application flexibility of vertical take-off fixed-wing unmanned aerial vehicles has become an urgent problem to be solved in this field. Summary of the Utility Model
[0005] The utility model aims to overcome at least one defect (shortcoming) of the above prior art, and provides a vertical take-off fixed-wing variable airfoil structure for solving the problem that vertical take-off fixed-wing unmanned aerial vehicles cannot quickly switch back and forth between the fixed wing and the multi-rotor structure, resulting in slow response and complex operation of the unmanned aerial vehicle, and insufficient application flexibility of vertical take-off fixed-wing unmanned aerial vehicles.
[0006] The technical solution adopted by the utility model is a vertical take-off fixed-wing variable airfoil structure, which includes a fuselage, a fixed-wing assembly, a folding assembly, and a rotor assembly. The fuselage includes a main body and a balance plate located at the head of the main body. The rotor assemblies are evenly distributed on the fixed-wing assembly. The fixed-wing assembly includes two fixed-wing plates. The fixed-wing assembly presents a folded state or an unfolded state through the folding or unfolding of the folding assembly. In the folded state, the rotation plane generated by the rotation of the rotor assembly is perpendicular to the upper part of the fixed-wing assembly, and is used to propel the fuselage to move in the up and down direction. In the unfolded state, the rotation plane generated by the rotation of the rotor assembly is perpendicular to the front of the fixed-wing assembly, and is used to propel the fuselage to move in the front and back direction.
[0007] It is beneficial to achieve the effects of high-speed flight and stable flight of the unmanned aerial vehicle (UAV) through the fixed-wing component; to achieve the effect of the UAV hovering at a fixed point through the rotor component; to achieve the switching back and forth between the folded state and the unfolded state of the fixed-wing component, and the switching back and forth between providing power in the vertical direction and the horizontal direction of the rotor component through the folding component, so as to achieve the rapid and simple switching of the variable airfoil of the UAV, shorten the response time of the variable airfoil of the UAV, and make the application scenarios of the UAV more flexible.
[0008] Further, the fixed-wing plate includes a recess, and the balance plate includes symmetrically arranged protrusions. When the fixed-wing plate is in the unfolded state, the recess and the protrusions are horizontally fitted with each other. When the fixed-wing plate is in the folded state, the recess and the protrusions are perpendicular to each other.
[0009] It is beneficial to overcome the jitter during the flight of the UAV through the balance plate, and make the transformation between the fully folded state and the fully unfolded state of the fixed-wing plate stable by restricting the movement range of the slider, so that it is not easy to shake and affect the flight stability of the UAV; it is beneficial to make it easier for the push rod to exert force when pushing the fixed-wing plate to fold through the recess on the fixed-wing plate; the surface of the fixed-wing plate is smooth when it is in the fully unfolded state through the horizontal fitting of the recess and the protrusions, so as to avoid affecting the flight stability; the four rotor components are evenly distributed on the same plane above the fuselage through the perpendicularity of the recess and the protrusions, so that the UAV can achieve a stable hovering effect at a fixed point.
[0010] Further, the folding component includes two push rods, and a motor, a lead screw, a slider and a slide rail arranged between the balance plate and the tail of the fuselage. A universal joint is provided at the connection between the fixed-wing plate and the push rod. A first universal joint is provided on the fixed-wing plate, and a second universal joint is provided at the end of the push rod. The first universal joint and the second universal joint are movably connected; one ends of the two push rods are simultaneously connected to the slider, and the other ends are respectively connected to the first universal joints on the two fixed-wing plates through the second universal joints. The slider is arranged between the upper and lower parallel slide rails and the lead screw. The motor drives the lead screw to rotate, and the lead screw drives the slider to move on the slide rail; when the slider moves between the tail of the fuselage and the balance plate, the push rod is subjected to a force inclined downward or upward to disengage or horizontally fit the recess and the protrusions.
[0011] It is beneficial to achieve the effect of quickly and stably folding two fixed-wing plates by moving one slider through the connection of the slider to two push rods; it is beneficial to achieve the precise movement of the slider and ensure the stability of the pulling force or pushing force transmitted to the push rod through the cooperation of the motor, the lead screw, the slide rail and the slider, so as to achieve a smooth transition during the process of changing the airfoil; through the connection of the two universal joints, when the push rod transmits the pulling force or pushing force to the fixed-wing plate, it can change the direction with the change of the airfoil, so that the fixed-wing plate is always under the action of the push rod force until it reaches the fully folded state or the fully unfolded state.
[0012] Further, the two fixed wing plates are respectively connected to both sides of the balance plate through hinge members. The hinge members include a first hinge member and a second hinge member. Both the first hinge member and the second hinge member include a mounting portion and a torsion portion. The mounting portions of the first and second hinge members are respectively connected to the convex portion and the concave position. A rotational connection of two contact surfaces is provided between the torsion portions of the first and second hinge members.
[0013] It is beneficial to realize the folding or unfolding of the fixed wing plates through the hinge members. By connecting the mounting portions of the first hinge member and the second hinge member to the balance plate and the fixed wing plates respectively, and through the torsional cooperation of the contact surfaces between the torsion portions of the first hinge member and the second hinge member, the inclination angle of the fixed wing plates is changed in the roll angle direction and the pitch angle direction, thereby realizing the airfoil transformation of the unmanned aerial vehicle.
[0014] Further, when the fixed wing plates are in the unfolded state, the included angle between the mounting portions of the first hinge member and the second hinge member is 180°, and the two contact surfaces between the torsion portions of the first hinge member and the second hinge member are parallel and in contact; when the fixed wing plates are in the folded state, the included angle between the mounting portions of the first hinge member and the second hinge member is 90°, and the relative torsional included angle between the two contact surfaces between the torsion portions of the first hinge member and the second hinge member is 90°.
[0015] It is beneficial to realize the accuracy of the full unfolding or full folding of the fixed wing plates through the change of the included angle between the mounting portions of the two hinge members; and to realize the inclination of the fixed wing plates in the pitch angle direction and the roll angle direction through the torsion of the contact surfaces between the torsion portions of the two hinge members, thereby realizing the rapid execution of the airfoil transformation.
[0016] Further, the included angle formed between the mounting portion and the torsion portion of the first hinge member is A1, and the included angle formed between the mounting portion and the torsion portion of the second hinge member is A2. The angular range of A1 is 110° - 135°, the angular range of A2 is 45° - 75°, and A1 + A2 = 180°.
[0017] It is beneficial to realize the effect of mutual fitting or mutual perpendicularity between the convex portion of the balance plate and the concave position of the fixed wing plate through the specific angle between the mounting portion and the torsion portion of the first hinge member and the specific angle between the mounting portion and the torsion portion of the second hinge member.
[0018] Further, the aspect ratio range of the length and width of the connection part from the inner edge of the fixed wing plate is 1 - 1.5. The ratio range of the width of the fixed wing plate to the width of the connection part is 4 - 6, and the ratio range of the length of the fixed wing plate to the length of the connection part is 20 - 25.
[0019] It is beneficial to achieve the effect of saving the acting force of the push rod on the fixed wing plate by connecting to a specific position on the fixed wing plate and a specific proportional value between the connection and the fixed wing plate, so that the force-bearing position of the fixed wing plate is always located at the lower part on the inner side.
[0020] Furthermore, the change range of the top view angle B1 between the two push rods during the change from the unfolded state to the folded state is 10° - 60°, and the change range of the inclination angle of the push rod relative to the side of the fuselage is 10° - 30°.
[0021] It is beneficial to limit the folded or unfolded state of the fixed wing plate at a specific position through a specific included angle range of the push rod and a specific moving range of the slider, so that the rotor assembly can operate stably during the mode switching process, avoiding affecting the stable and rapid back-and-forth switching of the fixed wing plate.
[0022] Furthermore, the ratio range of the distance between adjacent two rotor assemblies to the length of the fixed wing plate is 0.3 - 0.5.
[0023] It is beneficial to avoid the mutual interference of each rotor assembly and ensure the stable flight effect of the drone in the folded state of the fixed wing plate through the specific distance between the rotor assemblies.
[0024] Furthermore, the moving distance range of the slider on the slide rail is 200 - 300 mm.
[0025] It is beneficial to quickly and stably switch the folded or unfolded state of the fixed wing plate through a specific moving distance.
[0026] Compared with the prior art, the beneficial effects of the present utility model are as follows: the rapid back-and-forth switching of the state of the fixed wing plate is realized through the variable airfoil structure, enabling it to have the effects of high-speed flight, stable flight of the fixed-wing drone and hovering in place of the rotor drone; the convenient, rapid and stable switching of the drone between different states of the fixed wing plate is realized through the folding assembly, shortening the response time of the flight mode switching and making the application scenarios of the drone more flexible. BRIEF DESCRIPTION OF THE DRAWINGS
[0027] Figure 1 It is the exploded view of the structure of the present utility model.
[0028] Figure 2 It is the three-dimensional view of the unfolded state of the fixed wing plate of the present utility model.
[0029] Figure 3 It is the three-dimensional view of the folded state of the fixed wing plate of the present utility model
[0030] Figure 4 It is the top view of the fully unfolded fixed wing plate of the present utility model.
[0031] Figure 5This is the top view of the fixed wing plate of the present utility model in a fully folded state.
[0032] Explanation of the attached drawing reference numerals: fuselage 1, fixed wing plate 2, first hinge 3, external thread bearing of the hinge 4, second hinge 5, first fuselage pipe clamp 6, screw pipe clamp 7, screw 8, screw bearing seat 9, screw nut seat 10, first slider 11, slide rail 12, slider conversion seat 13, first universal joint 14, external thread bearing of the slider 15, second universal joint 16, push rod sleeve 17, push rod 18, bearing end push rod sleeve 19, motor 20, second fuselage pipe clamp 21, coupling 22, rotor assembly 23, second slider 24. Detailed implementation manners
[0033] The attached drawings of the present utility model are only for illustrative purposes and should not be construed as a limitation to the present utility model. To better illustrate the following embodiments, some components in the attached drawings may be omitted, enlarged or reduced, which do not represent the dimensions of the actual product; for those skilled in the art, it is understandable that some well-known structures and their descriptions in the attached drawings may be omitted.
[0034] Embodiment
[0035] As Figures 1-5 shown, this embodiment provides a vertical take-off fixed wing variable airfoil structure, which includes a fuselage, a fixed wing assembly, a folding assembly and a rotor assembly. The fuselage includes a main body and a balance plate located at the head of the main body. The rotor assemblies are evenly distributed on the fixed wing assembly. The fixed wing assembly includes two fixed wing plates. The fixed wing assembly presents a folded state or an unfolded state through the folding or unfolding of the folding assembly. In the folded state, the rotation plane generated by the rotation of the rotor assembly 23 is perpendicular to the upper part of the fixed wing assembly, and is used to propel the fuselage to move in the up and down direction; in the unfolded state, the rotation plane generated by the rotation of the rotor assembly 23 is perpendicular to the front of the fixed wing assembly, and is used to propel the fuselage to move in the front and back directions.
[0036] In this embodiment, when the unmanned aerial vehicle takes off, the fixed wing plate 2 is in a folded state. At this time, the rotor assembly 23 is located above the unmanned aerial vehicle, and the rotation of the rotor assembly 23 drives the unmanned aerial vehicle to take off vertically; when the unmanned aerial vehicle is ready to cruise, the fixed wing plate 2 quickly unfolds. At this time, the rotor assembly 23 is located in front of the unmanned aerial vehicle, and the rotation of the rotor assembly 23 drives the unmanned aerial vehicle to fly stably at high speed.
[0037] In this embodiment, the fuselage 1 is made of ABS material and is in the shape of a long strip tube. The head of the fuselage 1 is provided with a trapezoidal surface for reducing air resistance. Above the fuselage 1, there is a fixed-wing assembly, which includes two fixed-wing plates 2 symmetrically arranged with respect to the fuselage 1. The fixed-wing plates 2 are made of ABS material, and the front side of the fixed-wing plates 2 includes an arc-shaped edge for reducing air resistance. The rotor assembly 23 is vertically arranged on the front side of the fixed-wing plate 2. When the fixed-wing plate 2 is fully deployed, the rotor assembly 23 is located in front of the fuselage 1 to provide forward flight power for the unmanned aerial vehicle. When the fixed-wing plate 2 is fully folded, the rotor assembly 23 is located above the fuselage 1 to provide vertical takeoff power for the unmanned aerial vehicle. The folding assembly is arranged on the fuselage 1. When the folding assembly moves, it drives the fixed-wing plate 2 to fold or unfold to both sides of the fuselage 1.
[0038] In this embodiment, there are four rotor assemblies 23, and two are provided on each fixed-wing plate 2. When the unmanned aerial vehicle is in the state where the fixed-wing plates are deployed, the rotor assemblies 23 are located directly in front of the head of the unmanned aerial vehicle, and the rotor assemblies 23 are used for the forward cruise power system of the unmanned aerial vehicle. When the unmanned aerial vehicle is in the state where the fixed-wing plates are folded, the rotor assemblies 23 are located directly above the unmanned aerial vehicle, and the rotor assemblies 23 are used for the vertical takeoff power system of the unmanned aerial vehicle. When the fixed-wing plate 2 is tilted, the rotor assembly 23 fixedly connected to the front side of the fixed-wing plate 2 follows the tilt, restricting the rotor assembly 23 to change accordingly in the pitch angle and roll angle directions, avoiding the steering out of control of the rotor assembly 23 resulting in flight instability when the unmanned aerial vehicle switches modes.
[0039] The fixed-wing plate 2 includes a recessed position, and the balance plate includes symmetrically arranged protruding portions. When the fixed-wing plate 2 is in the deployed state, the recessed position and the protruding portions are horizontally fitted with each other. When the fixed-wing plate 2 is in the folded state, the recessed position and the protruding portions are perpendicular to each other.
[0040] In this embodiment, the balance plate is in the shape of a cross and is close to the head of the fuselage 1. The tail of the fuselage is in a V shape and is located at the tail of the fuselage 1. Both the balance plate and the tail of the fuselage are used to control the balance of the fuselage 1 during flight. The slider moves between the balance plate and the tail of the fuselage, making the moving distance of the push rod 18 driving the fixed-wing plate 2 controllable.
[0041] In this embodiment, the inner side of the fixed-wing plate 2 is provided with a recessed position, which is in the shape of a chamfered rectangular strip. The central part of the balance plate is in the shape of a rectangular block, and the protruding portions of the balance plate are in the shape of chamfered rectangular strips, which are perfectly matched and fitted with the shape of the recessed position. When the fixed-wing plate 2 is folded, the recessed position and the protruding portions are disengaged from the fitting, and the end surface of the protruding portion is perpendicular to the upper surface of the fixed-wing plate 2.
[0042] The folding assembly includes two push rods 18, and a motor 20, a lead screw 8, a slider, and a slide rail 12 disposed between the balance plate and the tail of the fuselage. A universal joint is provided at the connection between the fixed wing plate 2 and the push rod 18. A first universal joint 14 is provided on the fixed wing plate 2. A second universal joint 16 is provided at the end of the push rod 18. The first universal joint 14 is movably connected to the second universal joint 16. One ends of the two push rods 18 are simultaneously connected to the slider, and the other ends are respectively connected to the first universal joints 14 on the two fixed wing plates 2 through the second universal joints 16. The slider is disposed between the slide rail 12 and the lead screw 8 that are parallel up and down. The motor 20 drives the lead screw 8 to rotate, and the lead screw 8 drives the slider to move on the slide rail 12. When the slider moves between the tail of the fuselage and the balance plate, the push rod 18 is subjected to a force that is inclined downward or upward, and the recessed portion is disengaged from or horizontally engaged with the protruding portion.
[0043] In this embodiment, the motor 20 is connected to the second fuselage pipe clamp 21 through a coupling 22. The lead screw 8 is connected to the second fuselage pipe clamp 21 through a lead screw bearing seat 9. The slide rail 12 is connected to the second fuselage pipe clamp 21. The lead screw pipe clamp 7 and the second fuselage pipe clamp 21 are respectively sleeved on the upper and lower sides of the long pipe of the fuselage 1. The materials of the lead screw pipe clamp 7, the first fuselage pipe clamp 6, and the second fuselage pipe clamp 21 are all aluminum alloy 6063.
[0044] In this embodiment, the slider includes a first slider 11 and a second slider 24. The material of the slider is aluminum alloy 6063. The push rod 18 is an 8-mm carbon tube made of carbon fiber material. One ends of two push rods 18 are connected to the second universal joint 16 through bearing end push rod tube sleeves 17. The second universal joint 16 is connected to the first universal joint 14. The first universal joint 14 is connected to the first slider 11 through a slider external thread bearing 15. The lead screw bearing seats 9 are connected to both ends of the lead screw 8. The lead screw bearing seat 9 on the lead screw 8 for connecting one end of the slider is connected to the first slider 11 through a lead screw nut seat 10. The first slider 11 is connected to the second slider 24 through a slider conversion seat 13. The second slider 24 moves on a slide rail 12. The slide rail 12 is located below the lead screw 8 and above the long tube of the fuselage 1. The materials of the bearing end push rod tube sleeve 17, the slider conversion seat 13, the first universal joint 14, and the second universal joint 16 are all aluminum alloy 6063. The lead screw 8 is connected to the lead screw clamp 7 through the lead screw bearing seat 9. The lead screw clamp 7 and the first fuselage clamp 6 are respectively sleeved on the upper and lower parts of the long tube of the fuselage 1. The materials of the lead screw clamp 7, the first fuselage clamp 6, and the second fuselage clamp 21 are all aluminum alloy 6063. The other end of the push rod 18 is connected to the second universal joint 16 through a push rod tube sleeve 17. The second universal joint 16 is connected to the first universal joint 14. The first universal joint 14 is connected to the upper surface of the fixed wing plate 2 through a slider external thread bearing 15.
[0045] In this embodiment, when the slider moves from the tail to the head of the fuselage 1, a thrust is applied to the connection between the fixed wing plate 2 and the push rod 18. The upper surface of the fixed wing plate 2 folds towards the side of the fuselage 1, so that the fixed wing plate 2 is converted from a fully unfolded state to a fully folded state, thus completing the switching. When the slider moves from the head to the tail of the fuselage 1, a pulling force is applied to the connection between the fixed wing plate 2 and the push rod 18. The upper surface of the fixed wing plate 2 unfolds towards the side of the fuselage 1, so that the fixed wing plate 2 is converted from a fully folded state to a fully unfolded state, thus completing the switching.
[0046] Two fixed wing plates 2 are respectively connected to both sides of the balance plate through hinge members. The hinge members include a first hinge member 3 and a second hinge member 5. Both the first hinge member 3 and the second hinge member 5 include a mounting portion and a torsion portion. The mounting portions of the first hinge member 3 and the second hinge member 5 are respectively connected to the raised portion and the recessed position. Between the torsion portions of the first hinge member 3 and the second hinge member 5 is a rotational connection of two contact surfaces.
[0047] In this embodiment, the hinge member includes a first hinge member 3 and a second hinge member 5. The materials of the first hinge member 3 and the second hinge member 5 are both aluminum alloy 6063. The mounting portion of the first hinge member 3 is provided with three mounting holes, which match the three mounting holes on the convex portion of the balance plate. The torsion portion of the first hinge member 3 is connected to the torsion portion of the second hinge member 5 through a hinge external thread bearing 4. The mounting portion of the second hinge member 5 is provided with three mounting holes, which match the three mounting holes on the upper surface of the fixed wing plate 2.
[0048] When the fixed wing plate 2 is in the unfolded state, the included angle between the mounting portion of the first hinge member 3 and the mounting portion of the second hinge member 5 is 180°, and the two contact surfaces between the torsion portion of the first hinge member 3 and the torsion portion of the second hinge member 5 are parallel and in contact; when the fixed wing plate 2 is in the folded state, the included angle between the mounting portion of the first hinge member 3 and the mounting portion of the second hinge member 5 is 90°, and the relative torsion angle between the two contact surfaces between the torsion portion of the first hinge member 3 and the torsion portion of the second hinge member 5 is 90°.
[0049] In this embodiment, when the fixed wing plate 2 is in the unfolded state, the first hinge member 3 and the second hinge member 5 are connected back to back and movably connected through the intermediate axis between the two torsion portions, so that two contacting and parallel surfaces are formed between the two torsion portions. At this time, the included angle between the mounting portion of the first hinge member 3 and the mounting portion of the second hinge member 5 is 180°; when the wing profile of the drone changes and the fixed wing plate 2 is in the folded state, the relative rotation of the contact surfaces occurs between the torsion portion of the first hinge member 3 and the torsion portion of the second hinge member 5 around the intermediate axis until the relative rotation between the two contact surfaces of the two torsion portions is 90°. At this time, the included angle between the mounting portion of the first hinge member 3 and the mounting portion of the second hinge member 5 is 90°.
[0050] The included angle formed between the mounting portion and the torsion portion of the first hinge member 3 is A1, and the included angle formed between the mounting portion and the torsion portion of the second hinge member 5 is A2. The angular range of A1 is 110° - 135°, the angular range of A2 is 45° - 75°, and A1 + A2 = 180°.
[0051] In this embodiment, the included angle A1 between the mounting portion and the torsion portion of the first hinge member 3 is 120°, and the included angle A2 between the mounting portion and the torsion portion of the second hinge member 5 is 60°.
[0052] The ratio of the length to the width of the connection portion from the inner edge of the fixed wing plate ranges from 1 to 1.5. The ratio of the width of the fixed wing plate to the width of the connection portion ranges from 4 to 6. The ratio of the length of the fixed wing plate to the length of the connection portion ranges from 20 to 25.
[0053] In this embodiment, the length of the connection part from the inner edge of the fixed wing plate is 30 mm, the width is 40 mm, the width of the fixed wing plate is 200 mm, and the length of the fixed wing plate is 700 mm.
[0054] During the process of the two push rods 18 changing from the unfolded state to the folded state, the change range of the top view angle B1 is between 10° and 60°, and the change range of the inclination angle of the push rod 18 relative to the side surface of the fuselage 1 is between 10° and 30°.
[0055] In this embodiment, when the fixed wing plate 2 is fully unfolded, the angle B1 between the two push rods 18 is 16.7°, and when the fixed wing plate 2 is fully folded, the angle B1 between the two push rods 18 is 47.5°. The moving distance range of the slider on the slide rail 12 is within 270 mm.
[0056] The ratio range of the distance between adjacent two rotor assemblies 23 to the length of the fixed wing plate 2 is 0.3 - 0.5.
[0057] In this embodiment, the distance between adjacent two rotor assemblies 23 is 300 mm, the length of the fixed wing plate 2 is 700 mm, the distance from the rotor assembly 23 near the head of the fuselage 1 to the inner end face of the fixed wing plate 2 is 150 mm, and the distance from the rotor assembly 23 near the tail of the fuselage 1 to the outer end face of the fixed wing plate 2 is 250 mm.
[0058] The moving distance range of the slider on the slide rail is within 200 - 300 mm.
[0059] In this embodiment, the moving distance of the slider on the slide rail is 250 mm.
[0060] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the technical solutions of the present invention, rather than limitations on the specific implementation manners of the present invention. Any modifications, equivalent replacements, and improvements made within the spirit and principle of the claims of the present invention shall be included within the protection scope of the claims of the present invention.
Claims
1. A vertical takeoff fixed-wing variable airfoil structure, characterized in that, It includes a fuselage, a fixed-wing assembly, a folding assembly and a rotor assembly. The fuselage includes a main body and a balance plate located at the head of the main body. The rotor assemblies are evenly distributed on the fixed-wing assembly. The fixed-wing assembly includes two fixed-wing plates. The fixed-wing assembly is presented in a folded state or an unfolded state through the folding or unfolding of the folding assembly. In the folded state, the rotation plane generated by the rotation of the rotor assembly is perpendicular to the upper part of the fixed-wing assembly, and is used to propel the fuselage to move in the up and down direction. In the unfolded state, the rotation plane generated by the rotation of the rotor assembly is perpendicular to the front of the fixed-wing assembly, and is used to propel the fuselage to move in the front and back direction. The balance plate is cross-shaped. There is a recess on the inner side of the fixed-wing plate, and the recess is in the shape of a chamfered rectangular strip. The protruding part of the balance plate is in the shape of a chamfered rectangular strip, which is exactly matched and fitted with the shape of the recess. The folding assembly includes two push rods and a motor, a lead screw, a slider and a slide rail arranged between the balance plate and the tail of the fuselage. A universal joint is provided at the connection between the fixed-wing plate and the push rod. A first universal joint is provided on the fixed-wing plate, and a second universal joint is provided at the end of the push rod. The first universal joint is movably connected to the second universal joint. One ends of the two push rods are simultaneously connected to the slider, and the other ends are respectively connected to the first universal joints on the two fixed-wing plates through the second universal joints. The slider is arranged between the upper and lower parallel slide rails and the lead screw. The motor drives the lead screw to rotate, and the lead screw drives the slider to move on the slide rail. When the slider moves between the tail of the fuselage and the balance plate, the push rod is subjected to a force inclined downward or upward to disengage or horizontally engage the recess and the protruding part. The two fixed-wing plates are respectively connected to both sides of the balance plate through hinge joints. The hinge joints include a first hinge joint and a second hinge joint. The first hinge joint and the second hinge joint both include a mounting part and a torsion part. The mounting parts of the first and second hinge joints are respectively connected to the protruding part and the recess. The torsion parts of the first and second hinge joints are rotatably connected between two contact surfaces. The change range of the top view angle B1 of the two push rods during the change process from the unfolded state to the folded state is between 10° and 60°, and the change range of the inclination angle of the push rod relative to the side of the fuselage is between 10° and 30°.
2. The variable airfoil structure of a vertical takeoff fixed-wing according to claim 1, characterized in that The fixed-wing plate includes a recess, and the balance plate includes symmetrically arranged protruding parts. When the fixed-wing plate is in the unfolded state, the recess and the protruding part are horizontally fitted with each other. When the fixed-wing plate is in the folded state, the recess and the protruding part are perpendicular to each other.
3. A vertical takeoff fixed-wing variable airfoil structure according to claim 1, characterized in that When the fixed-wing plate is in the unfolded state, the angle between the mounting parts of the first hinge joint and the second hinge joint is 180°, and the two contact surfaces between the torsion parts of the first hinge joint and the second hinge joint are parallel and fitted. When the fixed-wing plate is in the folded state, the angle between the mounting parts of the first hinge joint and the second hinge joint is 90°, and the relative torsion angle between the two contact surfaces between the torsion parts of the first hinge joint and the second hinge joint is 90°.
4. A vertical takeoff fixed-wing variable airfoil structure according to claim 1, characterized in that, An angle A1 is formed between the mounting portion and the torsion portion of the first hinge member, and an angle A2 is formed between the mounting portion and the torsion portion of the second hinge member. The angular range of A1 is 110° - 135°, the angular range of A2 is 45° - 75°, and A1 + A2 = 180°.
5. A vertical takeoff fixed-wing variable airfoil structure according to claim 1, characterized in that, The aspect ratio range of the distance from the connection point to the inner edge of the fixed wing plate is 1 - 1.
5. The ratio range of the width of the fixed wing plate to the width of the connection point is 4 - 6, and the ratio range of the length of the fixed wing plate to the length of the connection point is 20 - 25.
6. A vertical takeoff fixed-wing variable airfoil structure according to any one of claims 1-5, characterized in that, The ratio range of the spacing between adjacent two rotor assemblies to the length of the fixed wing plate is 0.3 - 0.
5.
7. A vertical take-off fixed-wing variable airfoil structure according to any one of claims 1-5, characterized in that, The moving distance range of the slider on the slide rail is 200 - 300 mm.