Variable sweepback wing aircraft with movable winglet
By designing movable winglets and swing devices on variable sweep wing vehicles, the problem that traditional winglets cannot be adjusted is solved, and the aircraft is efficiently adapted and aerodynamic performance optimization is achieved at different flight stages, significantly improving flight efficiency and safety.
Patent Information
- Application Number
- CN202510040821.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-10
- Publication Date
- 2025-04-08
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
When the sweep angle of the variable sweep wing vehicle changes, the traditional immovable winglet cannot be adjusted accordingly, resulting in an increase in resistance and cannot effectively solve the problems of wingtip stall and induced resistance.
A variable sweep wing aircraft with movable winglets is designed. By setting up a swing device, it is ensured that the winglets can be adjusted accurately according to the flight requirements and maintain perpendicular correspondence with the airflow direction.
By adjusting the direction of the winglets in real time, the drag during flight is significantly reduced, the flight efficiency and energy utilization are improved, the flight time and range are extended, and the stability and safety of the aircraft under complex meteorological conditions are ensured.
Smart Images
Figure CN119773955A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of aircraft, in particular to a variable-sweep wing aircraft with movable winglets. Background Art
[0002] A variable-sweep wing aircraft refers to an aircraft whose wing sweep angle can be changed during flight. Its basic design concept is to change the size of the sweep angle, thereby changing the frontal area of the aircraft wing by changing the wingspan and sweep angle of the wing, so that the aircraft can take into account the aerodynamic requirements of high-speed and low-speed flight at the same time. Specifically, when the aircraft takes off, lands or needs to fly at a low speed, the wing is turned forward to reduce the sweep angle to increase the lift of the aircraft and shorten the take-off and landing distance; when the aircraft needs to fly at a high speed, the wing is turned backward to increase the sweep angle to reduce flight resistance and improve the high-speed flight performance of the aircraft, so as to optimize the aerodynamic performance of different flight stages. However, in the process of the variable-sweep wing aircraft constantly changing and the wing gradually sweeping back, the sweep angle gradually increases, and the three-dimensional effect of the wing tip becomes more obvious. Due to the wingtip effect, the flow tube becomes thinner and the suction increases in the front section of the upper surface of the wingtip; while in the rear section of the upper surface, the flow tube becomes thicker and the suction decreases. As a result, the adverse pressure gradient between the trailing edge of the upper surface of the wingtip and the lowest pressure point increases, which enhances the tendency of the air in the boundary layer to flow back forward, easily forming airflow separation, which leads to wingtip stall. In addition, the wingtip vortex of the aircraft is larger, resulting in larger induced drag, which further leads to high energy consumption of the aircraft.
[0003] In response to the above problems, the current mainstream solution is to install winglets. Winglets can produce an end plate effect, block the flow from the lower surface of the wing to the upper surface, weaken the strength of the wingtip vortex, and thus reduce the induced drag of the aircraft. The favorable pressure gradient generated by the winglets can also be used to offset part of the wingtip adverse pressure field, so that the pressure distribution becomes smoother, the adverse pressure gradient is reduced, the airflow separation at the wingtip is delayed, and the aircraft stall angle of attack is increased. However, since the variable swept wing will continuously change the sweep angle of the aircraft, if the traditional immovable winglet is used, the change in the sweep angle will cause the original wingtip and the incoming flow direction to change from no angle to an angle, which greatly increases the resistance of the aircraft. Therefore, traditional winglets cannot be installed on variable swept wing aircraft, resulting in the inability of existing variable swept wing aircraft to install winglets to solve the above problems. Summary of the invention
[0004] The object of the present invention is to provide a variable-sweep wing aircraft with a movable winglet, so that the winglet can rotate to match the incoming flow direction, thereby changing the angle between the winglet and the 1 / 4 chord line of the wing according to the constantly changing sweep angle, so that the winglet always maintains a vertical correspondence with the incoming flow direction, so as to solve the problems in the background technology.
[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a variable-sweep wing aircraft with movable winglets, comprising an aircraft body, a mounting slot and a winglet body, the aircraft body being provided with an organic tail wing, the outer surface of the aircraft body being provided with wings near the left and right sides, the aircraft body being connected to the front ends of the wings on the left and right sides by hinges, a Hall effect sensor being fixedly mounted on the inner front end wall of the mounting slot, a swing device being arranged inside the mounting slot, the swing device comprising a hydraulic telescopic rod, a sliding rod, a first sliding block, a connecting block, a limiting block, a second sliding block, a second sliding bar, a first sliding rail, a central axis, a spherical support, a spherical column, a swing seat, a swing frame, a mounting seat and a second sliding rail, wherein there are two connecting blocks, and the adjacent ends of the two connecting blocks are fixedly connected with a second connecting block near the left side. A slide rail, the right sides of the two connecting blocks are fixedly connected to the outer surface of the slide rod, the front side of the first slide block near the right side is fixedly connected to the output end of the hydraulic telescopic rod, the limit block is fixedly connected to the outer surface of the slide rod near the rear end, the front side of the second slide block is fixedly connected to the rear end of the slide rod, the front side of the slide rod is fixedly connected to the rear end of the spherical column, the outer surface of the spherical column is movably sleeved with a spherical bearing, the front side of the hydraulic telescopic rod is fixedly connected to a swing frame, a swing seat is provided on the swing frame, the front side of the mounting seat is fixedly connected to the rear end of the second slide rail near the center, the top and bottom of the central axis are respectively fixedly connected to the inner top wall and the inner bottom wall of the mounting groove near the front end, a magnet is fixedly installed on the winglet body, and the right side of the winglet body is fixedly connected to the second slide bar.
[0006] Furthermore, a slide groove is provided on the front side of the first sliding block near the left side, and the outer surface of the sliding rod is movably sleeved with the inside of the slide groove on the first sliding block.
[0007] Furthermore, the outer surface of the second sliding block is movably sleeved with the front inner portion of the second sliding rail.
[0008] Furthermore, the right side of the second slide bar is movably sleeved inside the left side of the first slide rail.
[0009] Furthermore, the spherical support is fixedly connected to the inner front end wall of the mounting groove, and the front face of the swing seat is fixedly connected to the inner front end wall of the mounting groove.
[0010] Furthermore, the rear end of the mounting seat is fixedly connected to the inner rear end wall of the mounting groove.
[0011] Furthermore, a position of the outer surface of the winglet body close to the right side is located inside the mounting groove, a slide groove is provided at the right front end of the winglet body, and the slide groove on the winglet body is movably connected to the outer surface of the central axis.
[0012] Furthermore, there are two mounting grooves, and the internal structures of the two mounting grooves are the same, but the positions are opposite, and the two mounting grooves are respectively opened at the ends of the two wings.
[0013] Furthermore, the aircraft body is a manned aircraft body, a flight control system and a cockpit are provided in the aircraft body, a propeller is provided at the tail of the aircraft body, and an aircraft variable swept wing drive device is provided in the aircraft body, and the connecting ends of the aircraft variable swept wing drive device are respectively hinged to the rear ends of adjacent sides of the two wings.
[0014] Furthermore, there are two winglet bodies, and adjacent sides of the two winglet bodies are respectively located inside the two mounting grooves.
[0015] Compared with the prior art, the present invention provides a variable-sweep wing aircraft with movable winglets, which has the following beneficial effects:
[0016] 1. The variable swept wing aircraft with movable winglets can ensure that the wing sweep angle and the winglet can be accurately adjusted according to flight requirements by setting a swing device, thereby changing the wingspan, sweep angle and the angle between the winglet and the 1 / 4 chord line of the wing, thereby changing the frontal area of the aircraft wing and affecting the lift of the aircraft, and also meeting the specific requirements of the aircraft for the angle between the winglet and the 1 / 4 chord line of the wing in different flight stages, ensuring that the winglet corresponds to the incoming flow direction; this flexibility enables the aircraft to more effectively adapt to various flight conditions and optimize flight performance; more importantly, this setting enables the winglet to be adjusted as the aircraft flies. The aircraft adjusts its direction in real time according to the changes in the swept wings of the aircraft; when the swept wings of the aircraft change, the winglets respond quickly through a precise mechanical structure and adjust their direction to ensure that they match the direction of the airflow; this real-time adjustment mechanism significantly reduces the resistance during flight, improves flight efficiency, and enables the aircraft to use energy more efficiently; the setting of adjustable winglets in the aircraft is an important innovation; it not only optimizes the airflow distribution around the aircraft, reduces wingtip vortices and induced drag, and improves the effective aspect ratio, thereby effectively reducing energy consumption; this setting makes the aircraft more energy-efficient during flight, and extends the flight time and range.
[0017] 2. The variable-sweep-wing aircraft with movable winglets can generate an end plate effect by arranging winglets on the variable-sweep-wing aircraft, thereby reducing the increase in the adverse pressure gradient between the trailing edge of the upper surface of the wingtip and the lowest pressure point caused by the more obvious three-dimensional effect of the wingtip due to the increase in the sweep angle, thereby slowing down the tendency of air in the wingtip boundary layer to flow back forward, delaying the occurrence of wingtip stall, and ensuring the safety and reliability of the aircraft. Under complex meteorological conditions such as strong winds and turbulence, precise winglet control can help the aircraft maintain a stable flight attitude and ensure flight safety; this stability is very important for improving the safety of the aircraft Safety and reliability are crucial, especially in extreme weather conditions; through motor drive, gear transmission system and sophisticated mechanical structure, precise control and real-time adjustment of winglets are achieved, improving the reliability of the aircraft; this advanced technical support provides a solid foundation for the setting and optimization of the aircraft, ensuring that the aircraft can maintain optimal performance under various flight conditions; by setting up a swing device in the aircraft, the flight efficiency and stability of the aircraft are improved. This setting is of great significance for the setting, manufacturing and optimization of the aircraft, and provides strong support for technological progress and development in the aviation field.
[0018] 3. The variable-sweep-wing aircraft with movable winglets is provided with magnets and Hall effect sensors. Specifically, the magnets are firmly mounted on the swing block and move with the left and right swing of the swing block; the Hall effect sensors are precisely placed at corresponding positions and can sense the position changes of the magnets in real time; this arrangement constitutes an efficient and accurate monitoring system that can capture the swing angle information of the winglets in real time; the data captured by the Hall effect sensors are quickly and accurately transmitted to the flight control system; the flight control system, as the "brain" of the aircraft, can intelligently analyze these data and make fine adjustments to the angles of the winglets according to current flight conditions, speed, altitude, airflow conditions and other factors; this intelligent adjustment not only ensures that the winglets can always maintain the best position with the airflow direction, but also ensures that the winglets can always maintain the best position with the airflow direction. The intersection also greatly improves the aerodynamic performance and flight efficiency of the aircraft; more importantly, this real-time monitoring and intelligent adjustment mechanism based on magnets and Hall effect sensors enables the aircraft to maintain a high degree of stability and controllability in complex and changeable flight environments; whether in strong winds, turbulence or other extreme weather conditions, the flight control system can accurately adjust the winglets according to real-time data to ensure the safe flight of the aircraft; in summary, by setting up magnets and Hall effect sensors, we have achieved real-time monitoring of the swing angle of the winglets, providing key data support for the flight control system; and the flight control system intelligently adjusts the angle of the winglets based on these data to achieve more precise flight control; this innovative setting not only improves the performance of the aircraft, but also provides a strong guarantee for flight safety. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] Figure 1 It is a schematic diagram of the overall structure of the present invention;
[0020] Figure 2 A diagram showing the connection relationship between the wing of the present invention and the variable swept wing drive device of the aircraft;
[0021] Figure 3 It is a cross-sectional structural diagram of the interior of the installation groove of the present invention;
[0022] Figure 4 It is a top-down cross-sectional structural diagram of the interior of the installation box of the present invention.
[0023] In the figure: 1. aircraft body; 2. tail wing; 3. wing; 4. winglet body; 5. aircraft variable swept wing drive device; 6. swing device; 601. hydraulic telescopic rod; 602. slide bar; 603. first slide block; 604. connecting block; 605. limit block; 606. second slide block; 607. second slide bar; 608. first slide rail; 609. central axis; 610. spherical support; 611. spherical column; 612. swing seat; 613. swing frame; 614. mounting seat; 615. second slide rail; 7. magnet; 8. Hall effect sensor; 9. mounting groove. DETAILED DESCRIPTION
[0024] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.
[0025] See also Figure 1-4The present invention discloses a variable swept wing aircraft with a movable winglet, comprising an aircraft body 1, a mounting slot 9 and a winglet body 4, wherein an organic tail 2 is arranged on the aircraft body 1, and an organic wing 3 is arranged near the left and right sides of the outer surface of the aircraft body 1, the aircraft body 1 is connected to the front ends of the wings 3 on the left and right sides through hinges, a Hall effect sensor 8 is fixedly installed on the inner front end wall of the mounting slot 9, and a swing device 6 is arranged inside the mounting slot 9, wherein the swing device 6 comprises a hydraulic telescopic rod 601, a slide bar 602, a first slide block 603, a connecting block 604, a limit block 605, a second slide block 606, a second slide bar 607, a first slide rail 608, a central axis 609, a spherical support 610, a spherical column 611, a swing seat 612, a swing frame 613, a mounting seat 614 and a second slide rail 615, wherein there are two connecting blocks 604, and the adjacent ends of the two connecting blocks 604 are fixedly connected to the first slide rail near the left side. 608, the right sides of the two connecting blocks 604 are fixedly connected to the outer surface of the slide bar 602, the front of the first slider 603 is fixedly connected to the output end of the hydraulic telescopic rod 601 near the right side, the limit block 605 is fixedly connected to the outer surface of the slide bar 602 near the rear end, the front of the second slider 606 is fixedly connected to the rear end of the slide bar 602, the front of the slide bar 602 is fixedly connected to the rear end of the spherical column 611, the outer surface of the spherical column 611 is movably sleeved with a spherical support 610, the front of the hydraulic telescopic rod 601 is fixedly connected to a swing frame 613, and a swing seat 612 is provided on the swing frame 613. The front of the mounting seat 614 is fixedly connected to the rear end of the second slide rail 615 near the center, the top and bottom of the central axis 609 are respectively fixedly connected to the inner top wall and the inner bottom wall of the mounting groove 9 near the front end, a magnet 7 is fixedly installed on the winglet body 4, and the right side of the winglet body 4 is fixedly connected to the second slide bar 607.
[0026] Specifically, a slide groove is provided on the front side of the first sliding block 603 near the left side, and the outer surface of the sliding rod 602 is movably connected to the inside of the slide groove on the first sliding block 603 .
[0027] Specifically, the outer surface of the second sliding block 606 is movably sleeved with the front inner portion of the second sliding rail 615 .
[0028] Specifically, the right side of the second slide bar 607 is movably connected to the left side of the first slide rail 608 .
[0029] Specifically, the spherical support 610 is fixedly connected to the inner front end wall of the installation groove 9 , and the front side of the swing seat 612 is fixedly connected to the inner front end wall of the installation groove 9 .
[0030] Specifically, the rear end of the mounting seat 614 is fixedly connected to the inner rear end wall of the mounting groove 9 .
[0031] Specifically, the outer surface of the winglet body 4 near the right side is located inside the mounting groove 9 , a slide groove is opened at the right front end of the winglet body 4 , and the slide groove on the winglet body 4 is movably connected to the outer surface of the central shaft 609 .
[0032] Specifically, there are two mounting grooves 9 , and the two mounting grooves 9 have the same internal structure but are located in opposite positions. The two mounting grooves 9 are respectively opened at the ends of the two wings 3 .
[0033] Specifically, the aircraft body 1 is a manned aircraft body, a flight control system and a cockpit are provided in the aircraft body 1, a propeller is provided at the tail of the aircraft body 1, and an aircraft variable swept wing drive device 5 is provided in the aircraft body 1. The connecting ends of the aircraft variable swept wing drive device 5 are respectively hinged to the rear ends of the adjacent sides of the two wings 3.
[0034] When in use, the aircraft drives the screw to rotate through the internal self-locking motor of the variable sweep wing drive device 5, thereby driving the load-bearing rod to move, and further driving the connecting rod hinged thereon to move, thereby driving the wing 3 on the connecting end to move, thereby changing the sweep angle of the wing 3.
[0035] Specifically, there are two winglet bodies 4 , and adjacent sides of the two winglet bodies 4 are located inside the two installation grooves 9 respectively.
[0036] When in use, driving the hydraulic telescopic rod 601 becomes the starting point of the entire adjustment mechanism; the output end of the hydraulic telescopic rod 601, with its powerful driving force, accurately drives the first slider 603 to move smoothly along the slider 602 to the rear end; as the first slider 603 moves, it further drives the second slider 606 closely connected thereto, so that the second slider 606 can swing smoothly along the second slide rail 615; this swinging action then triggers a series of chain reactions, and the slide bar 602, the connecting block 604 and the first slide rail 608 are all driven to form a coordinated and consistent Swing system; when the first slide rail 608 is swung, this tight and flexible connection ensures that the winglet body 4 can rotate accurately with the central axis 609 as the center; this rotation directly drives the swing of the winglet body 4, so that it can be flexibly adjusted according to needs; in the whole process of the swing adjustment of the winglet body 4, the Hall effect sensor 8 plays a decisive role; it forms a set of precise monitoring system with the magnet 7 on the winglet body 4, and together completes the accurate monitoring of the swing angle of the winglet body 4; the Hall effect sensor The device 8 can sense the position change of the magnet 7 in real time with its high sensitivity and high precision; through this change, it can accurately calculate the swing angle of the winglet body 4; this key data is timely and accurately transmitted to the flight control system, providing crucial data support for subsequent flight control; the flight control system adjusts and optimizes the swing angle of the winglet body 4 in real time based on these data; this precise regulation ensures that the aircraft can always maintain the best aerodynamic performance and stability during the flight, whether facing a complex and changeable airflow environment or performing difficult flight maneuvers, it can cope with it with ease; this ingenious setting not only significantly reduces the resistance during the flight and improves the flight efficiency, but also enables the incoming flow direction of the winglet 4 to be flexibly adjusted with the change of the sweep angle; in this way, no matter how the flight attitude of the aircraft changes, the winglet 4 can always remain perpendicular to the incoming flow direction of the airflow, thereby minimizing the resistance and improving the flight performance; this innovative setting undoubtedly opens up new ideas for the setting and manufacturing of aircraft, and also lays a solid foundation for the future development of aviation technology.
[0037] In summary, the variable swept wing aircraft with movable winglets, by providing a swing device 6, can ensure that the wing sweep angle and the winglet 4 can be accurately adjusted according to flight requirements, thereby changing the wingspan, sweep angle of the wing 3 and the angle between the winglet 4 and the 1 / 4 chord line of the wing, thereby changing the frontal area of the aircraft wing and further affecting the lift of the aircraft, and also meeting the specific requirements of the aircraft for the angle between the position of the winglet 4 and the 1 / 4 chord line of the wing in different flight stages; this flexibility enables the aircraft to more effectively adapt to various flight conditions and optimize flight performance; more importantly, this setting enables the winglet 4 to adjust its direction in real time as the swept wing of the aircraft changes; when the swept wing of the aircraft changes The wingtip winglet 4 responds quickly through a precise mechanical structure and adjusts its direction to ensure that it matches the incoming flow direction; this real-time adjustment mechanism significantly reduces the resistance during flight, improves flight efficiency, and enables the aircraft to use energy more efficiently; the arrangement of an adjustable wingtip winglet 4 in the aircraft is an important innovation; it not only optimizes the airflow distribution around the aircraft, reduces wingtip vortices and induced drag, and improves the effective aspect ratio, thereby effectively reducing energy consumption; this arrangement enables the aircraft to be more energy-efficient during flight, prolongs flight time and range; by arranging the wingtip winglet 4 on a variable-sweep wing aircraft, an end plate effect can be generated, which reduces the trailing edge of the wingtip upper surface caused by the wingtip three-dimensional effect that becomes more obvious as the sweep angle increases The increase of the adverse pressure gradient between the highest and lowest pressure points slows down the tendency of air in the wingtip boundary layer to flow back forward, delays the occurrence of wingtip stall, and ensures the safety and reliability of the aircraft. Under complex meteorological conditions such as strong winds and turbulence, precise wingtip winglet 4 control can help the aircraft maintain a stable flight attitude and ensure flight safety. This stability is crucial to improving the safety and reliability of aircraft, especially in extreme weather conditions. Through motor drive, gear transmission system and precise mechanical structure, precise control and real-time adjustment of wingtip winglets 4 are achieved to improve the reliability of the aircraft. This advanced technical support provides a solid foundation for the setting and optimization of the aircraft, ensuring that the aircraft can maintain the best flight attitude under various flight conditions. performance; by setting a swing device 6 in the aircraft, not only the flight efficiency and stability of the aircraft are improved, but also the energy consumption and flight cost are reduced; this setting is of great significance to the setting, manufacturing and optimization of the aircraft, and provides strong support for the technological progress and development in the aviation field; by setting a magnet 7 and a Hall effect sensor 8, it moves with the swing of the winglet body 4; and the Hall effect sensor 8 is accurately placed at a corresponding position, and can sense the position change of the magnet 7 in real time; this setting constitutes an efficient and accurate monitoring system, which can capture the swing angle information of the winglet 4 in real time; the data captured by the Hall effect sensor 8 is quickly and accurately transmitted to the flight control system;As the "brain" of the aircraft, the flight control system can intelligently analyze these data and make fine adjustments to the angle of the winglet 4 according to the current flight conditions, speed, altitude, airflow conditions and other factors; this intelligent adjustment not only ensures that the winglet 4 can always maintain the best intersection with the airflow direction, but also greatly improves the aerodynamic performance and flight efficiency of the aircraft; more importantly, this real-time monitoring and intelligent adjustment mechanism based on the magnet 7 and the Hall effect sensor 8 enables the aircraft to maintain a high degree of stability and controllability in a complex and changeable flight environment; whether in strong winds, turbulence or other extreme weather conditions, the flight control system can accurately adjust the winglet 4 according to real-time data to ensure the safe flight of the aircraft; in summary, by setting the magnet 7 and the Hall effect sensor 8, we have achieved real-time monitoring of the swing angle of the winglet 4, providing key data support for the flight control system; and the flight control system intelligently adjusts the angle of the winglet 4 according to these data, achieving more precise flight control; this innovative setting not only improves the performance of the aircraft, but also provides a strong guarantee for flight safety. ;
[0038] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. A variable-sweep wing aircraft with a movable winglet, comprising an aircraft body (1), a mounting slot (9) and a winglet body (4), characterized in that: The aircraft body (1) is provided with an organic tail wing (2), and the outer surface of the aircraft body (1) is provided with organic wings (3) near the left and right sides. The aircraft body (1) is connected to the front ends of the wings (3) on the left and right sides via hinges. A Hall effect sensor (8) is fixedly installed on the inner front end wall of the installation groove (9). A swing device (6) is provided inside the installation groove (9). The swing device (6) includes a hydraulic telescopic rod (601), a sliding rod (602), a first sliding block (603), and a connecting block (60 4), a limit block (605), a second slider (606), a second slide bar (607), a first slide rail (608), a central axis (609), a spherical support (610), a spherical column (611), a swing seat (612), a swing frame (613), a mounting seat (614) and a second slide rail (615), wherein there are two connecting blocks (604), adjacent ends of the two connecting blocks (604) are fixedly connected to the first slide rail (608) at a position close to the left side, and the right sides of the two connecting blocks (604) are connected to the slide bar (608). 2), the front of the first slider (603) is fixedly connected to the output end of the hydraulic telescopic rod (601) near the right side, the limit block (605) is fixedly connected to the outer surface of the slide bar (602) near the rear end, the front of the second slider (606) is fixedly connected to the rear end of the slide bar (602), the front of the slide bar (602) is fixedly connected to the rear end of the spherical column (611), the outer surface of the spherical column (611) is movably sleeved with a spherical support (610), and the hydraulic telescopic rod The front side of (601) is fixedly connected to a swing frame (613), and a swing seat (612) is arranged on the swing frame (613). The front side of the mounting seat (614) is fixedly connected to the rear end of the second slide rail (615) near the center. The top and bottom of the central axis (609) are respectively fixedly connected to the inner top wall and the inner bottom wall of the mounting groove (9) near the front end. A magnet (7) is fixedly installed on the winglet body (4), and the right side of the winglet body (4) is fixedly connected to the second slide bar (607).
2. A variable-sweep wing aircraft with movable winglets according to claim 1, characterized in that: A sliding groove is provided on the front side of the first sliding block (603) near the left side, and the outer surface of the sliding rod (602) is movably sleeved inside the sliding groove on the first sliding block (603).
3. A variable-sweep wing aircraft with movable winglets according to claim 1, characterized in that: The outer surface of the second sliding block (606) is movably sleeved with the front inner portion of the second sliding rail (615).
4. A variable-sweep wing aircraft with movable winglets according to claim 1, characterized in that: The right side of the second slide bar (607) is movably sleeved inside the left side of the first slide rail (608).
5. The variable-sweep wing aircraft with movable winglets according to claim 1, characterized in that: The spherical support (610) is fixedly connected to the inner front end wall of the mounting groove (9), and the front face of the swing seat (612) is fixedly connected to the inner front end wall of the mounting groove (9).
6. A variable-sweep wing aircraft with movable winglets according to claim 1, characterized in that: The rear end of the mounting seat (614) is fixedly connected to the inner rear end wall of the mounting groove (9).
7. The variable-sweep wing aircraft with movable winglets according to claim 1, characterized in that: The outer surface of the winglet body (4) is located near the right side and is inside the mounting groove (9). A slide groove is provided at the front end of the right side of the winglet body (4), and the slide groove on the winglet body (4) is movably connected to the outer surface of the central shaft (609).
8. The variable-sweep wing aircraft with movable winglets according to claim 1, characterized in that: There are two mounting grooves (9), and the two mounting grooves (9) have the same internal structure but are located in opposite positions. The two mounting grooves (9) are respectively opened at the ends of the two wings (3).
9. The variable-sweep wing aircraft with movable winglets according to claim 1, characterized in that: The aircraft body (1) is a manned aircraft body, a flight control system and a cockpit are arranged in the aircraft body (1), a propeller is arranged at the tail of the aircraft body (1), and an aircraft variable swept wing drive device (5) is arranged in the aircraft body (1), and the connection ends of the aircraft variable swept wing drive device (5) are respectively hinged to the rear ends of adjacent sides of two wings (3).
10. The variable-sweep wing aircraft with movable winglets according to claim 1, characterized in that: There are two winglet bodies (4), and adjacent sides of the two winglet bodies (4) are respectively located inside the two installation grooves (9).