A front and rear wing coordinated control unmanned aerial vehicle structure

Abstract

The utility model relates to a kind of unmanned aerial vehicle structure of front and rear wing coordinated control, including bearing shaft, bearing shaft is equipped with installation slot, installation slot is equipped with installation shell, installation shell is fixed with mounting plate, full-actuated steering gear is installed on mounting plate, installation shell is fixedly connected with baffle, baffle is equipped with wing movable link key, wing movable link key is externally rotatably equipped with rudder connecting piece, rudder connecting piece is fixedly connected with extension plate, extension plate is rotatably connected with eccentric wheel connecting rod, and pull rod is arranged between full-actuated steering gear and eccentric wheel connecting rod;By starting full-actuated steering gear, drive pull rod relative movement, to indirectly drive rudder connecting piece rotation, to realize the deflection of different angles of front and rear wing surface, realize the adjustment wing surface aerodynamic distribution of unmanned aerial vehicle, so that unmanned aerial vehicle can respond in time when low-altitude flight, hovering or big maneuvering attitude adjustment, improve the maneuverability and control performance of unmanned aerial vehicle.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a UAV structure with coordinated control of the front and rear wings. Background Technology

[0002] Traditional fixed-wing UAVs mostly adopt a forward-swept or backward-swept monoplane structure and rely on the tail or aileron for attitude control. Although they have high flight efficiency, they have problems such as response lag and control coupling in low-speed flight, hovering or large-maneuver attitude adjustment.

[0003] While some hybrid aircraft combining rotor and fixed wings have improved some maneuverability, they are also complex in structure, have redundant control systems, consume a lot of power, and have limited stability. To address these issues, we propose a UAV structure with coordinated control of the front and rear wings. Utility Model Content

[0004] The purpose of this invention is to provide a UAV structure with coordinated control of the fore and aft wings, in order to solve the problems existing in the prior art.

[0005] To achieve the above-mentioned technical objectives, the technical solution adopted by this utility model is as follows:

[0006] A drone structure with coordinated fore-and-aft wing control, comprising:

[0007] A load-bearing shaft, wherein a mounting groove is provided in the middle of the load-bearing shaft;

[0008] Mounting housing, the mounting housing is installed inside the mounting groove, and a mounting plate is fixed on the mounting housing;

[0009] A fully movable servo motor, which is mounted on the mounting plate;

[0010] The mounting housing is symmetrically equipped with adjustment components on both sides;

[0011] The adjustment component includes:

[0012] Two partitions, both of which are fixedly connected to the mounting shell and fit against both sides of the load-bearing shaft;

[0013] A wing movable link key is located at the ends of the two partitions;

[0014] A control surface connector, which is rotatably disposed on the outside of the wing movable link key and located between the two partitions;

[0015] An extension plate, which is fixedly connected to the rudder surface connector;

[0016] An eccentric wheel connecting rod is rotatably connected to the extension plate;

[0017] A pull rod, one end of which is connected to the all-moving servo motor, and the other end of which is connected to the eccentric wheel connecting rod.

[0018] Furthermore, the two levers are rotationally symmetrical about the center of the fully movable servo.

[0019] Furthermore, a slot is provided on the side of the rudder surface connector away from the bulkhead.

[0020] Further specified, a differential gear is provided between the two partitions on the same side, and the differential gear meshes with the arc surface of the rudder surface connector.

[0021] Further specifying, a dual-axis digital servo is installed inside the mounting housing, and an extension rod is fixed to one end of the output shaft of the dual-axis digital servo that passes through the mounting housing, with a metal servo arm at the end of the extension rod.

[0022] The beneficial effects of this utility model are:

[0023] 1. By symmetrically setting adjustment components on both sides of the mounting shell, the components such as the partition, wing movable link key, control surface connector, extension plate, eccentric wheel link and tie rod in the adjustment components work together to achieve coordinated control of the front and rear wing surfaces under the drive of the all-moving servo motor. This allows for precise adjustment of the aerodynamic distribution of the aircraft wing surfaces, enabling the UAV to fly more stably in complex flight attitudes and improving maneuverability and attitude control accuracy.

[0024] 2. By setting a differential gear between two partitions on the same side, and having the differential gear mesh with the arc surface of the control surface connector, differential control of the rotation speed or angle of the control surface connector on both sides can be achieved, so that the front and rear wing surfaces can deflect at different rates or angles, accurately adjust the aerodynamic layout of the UAV, and meet the control requirements of complex flight attitudes.

[0025] 3. By installing a dual-axis digital servo inside the mounting housing, with an extension rod fixed to one end of its output shaft passing through the housing and a metal rudder arm at the end of the extension rod, an independent wing angle adjustment system is formed. Compared with the complex structure and high power consumption of compound aircraft, this design can precisely control the movement of the extension rod and the metal rudder arm, realizing independent adjustment of the UAV wing angle, meeting the flight requirements such as rapid turning and attitude fine adjustment, while simplifying the structure, reducing power consumption and weight, and improving stability. Attached Figure Description

[0026] This utility model can be further illustrated by the non-limiting embodiments given in the accompanying drawings.

[0027] Figure 1 This is a schematic diagram of the structure of an unmanned aerial vehicle (UAV) with coordinated control of the fore and aft wings according to this utility model. Figure 1 ;

[0028] Figure 2 This is a schematic diagram of the structure of an unmanned aerial vehicle (UAV) with coordinated control of the fore and aft wings according to this utility model. Figure 2 .

[0029] The symbols for the main components are explained below:

[0030] Bearing shaft 100, mounting housing 101, mounting plate 102, all-moving servo motor 103.

[0031] 200, bulkhead 201, wing movable link key 202, control surface connector 202, extension plate 203, eccentric wheel connecting rod 204, tie rod 205.

[0032] Card slot 300, differential gear 301, dual-axis digital servo motor 302, extension rod 303, metal servo arm 304. Detailed Implementation

[0033] To enable those skilled in the art to better understand this utility model, the technical solution of this utility model will be further described below in conjunction with the accompanying drawings and embodiments.

[0034] like Figures 1-2 As shown, a UAV structure with coordinated control of the fore and aft wings includes:

[0035] The load-bearing shaft 100 has an installation groove in the middle.

[0036] Mounting housing 101 is installed inside the mounting groove, and mounting plate 102 is fixed on mounting housing 101.

[0037] Full-motion servo motor 103 is mounted on mounting plate 102;

[0038] Adjustment components are symmetrically provided on both sides of the mounting housing 101;

[0039] The adjustment components include:

[0040] Two partitions 200 are fixedly connected to the mounting shell 101 and are in contact with both sides of the load-bearing shaft 100.

[0041] Wing movable link key 201, the wing movable link key 201 is located at the end of the two partitions 200;

[0042] The control surface connector 202 is rotatably located on the outside of the wing movable link key 201 and between the two partitions 200.

[0043] Extension plate 203 is fixedly connected to the rudder surface connector 202;

[0044] Eccentric wheel connecting rod 204 is rotatably connected to extension plate 203;

[0045] Pull rod 205, one end of which is connected to the all-movement servo motor 103. The other end is connected to the eccentric wheel connecting rod 204.

[0046] The load-bearing shaft 100, as the core support of the UAV structure, is installed in the center of the UAV's interior. It provides stable support for the entire coordinated control structure, ensures the installation position and relative relationship of each component, and ensures the stability and reliability of the entire system.

[0047] Mounting housing 101 is installed in the mounting slot of bearing shaft 100, serving to fix and protect internal mounting plate 102 and all-moving servo motor 103 and other components. At the same time, it provides a supporting foundation for the installation of adjustment components, ensuring that adjustment components can be accurately installed on both sides of bearing shaft 100 to achieve coordinated control of the front and rear wing surfaces.

[0048] Mounting plate 102 is fixed on mounting shell 101, providing a mounting surface for all-motion servo motor 103, ensuring that all-motion servo motor 103 can be installed stably, and ensuring that all-motion servo motor 103 will not be displaced during operation, so as to perform its power output function normally.

[0049] The all-motion servo motor 103, as a power source, is mounted on the mounting plate 102 to provide power output. It is connected to the eccentric wheel connecting rod 204 through the pull rod 205 to drive the adjustment component to work, thereby controlling the deflection angle of the front and rear wing surfaces, thereby adjusting the aerodynamic distribution of the aircraft's wing surfaces, so that the UAV can respond in a timely manner when flying at low altitude, hovering, or making large maneuvering attitude adjustments.

[0050] The bulkhead 200 serves to support and position the wing movable link key 201, while also providing guidance and restriction for the rotation of the control surface connector 202, ensuring that the control surface connector 202 can rotate within a specified range, thereby achieving accurate control of the fore and aft wing surfaces.

[0051] Among them, the bulkhead 200 can effectively isolate the airflow interference between the front and rear wing surfaces, reduce fuselage vibration during the transition phase, and ensure equipment safety.

[0052] The wing movable link key 201 is used to install the control surface connector 202, enabling the control surface connector 202 to rotate around it, realizing the movable connection of the control surface connector 202, and providing a rotation fulcrum for the deflection of the front and rear wing surfaces.

[0053] The control surface connector 202 is used to connect the front and rear wings of the UAV. By rotating itself, it drives the deflection of the front and rear wings, thereby controlling the deflection angle of the front and rear wings and adjusting the aerodynamic distribution of the aircraft's wings.

[0054] The extension plate 203 is used to connect the rudder surface connector 202 and the eccentric wheel connecting rod 204, and transmits the motion of the eccentric wheel connecting rod 204 to the rudder surface connector 202 to realize the transmission of power, so that the rudder surface connector 202 can rotate with the motion of the eccentric wheel connecting rod 204.

[0055] The eccentric wheel connecting rod 204 transmits the power of the all-moving servo motor 103 to the extension plate 203, which drives the extension plate 203 and the rudder surface connector 202 to move, thereby controlling the rotation angle of the rudder surface connector 202 and thus achieving the deflection of the front and rear wing surfaces.

[0056] The lever 205 is used to transmit the power of the all-moving servo motor 103, converting the rotation of the all-moving servo motor 103 into the linear motion of the lever 205, thereby driving the eccentric wheel connecting rod 204 to move and realize the transmission of power.

[0057] The two levers 205 are rotated symmetrically with the all-moving servo 103 located at the center.

[0058] The two levers 205 are symmetrically distributed around the all-moving servo motor 103, forming a symmetrical power transmission system.

[0059] When the all-moving servo motor 103 is working, the rotation of its output shaft is synchronously transmitted to the eccentric wheel connecting rods 204 on both sides through the symmetrical tie rods 205, so that the eccentric wheel connecting rods 204 on both sides produce symmetrical and opposite movements; this symmetrical power transmission method can ensure that the control surface connecting parts 202 on both sides remain coordinated when rotating, and realize the opposite deflection of the front and rear wing surfaces.

[0060] This symmetrical design allows for precise adjustment of the aerodynamic distribution on both sides of the aircraft's wings, generating the required roll moment, yaw moment, or pitch moment. This enables the UAV to respond quickly and stably to control commands during low-altitude flight, hovering, or large-maneuver attitude adjustments, improving the UAV's maneuverability and attitude control accuracy, and avoiding flight attitude deviations caused by asymmetrical power transmission.

[0061] A slot 300 is provided on the side of the rudder surface connector 202 away from the bulkhead 200.

[0062] The slot 300 is used to form a locking structure with the connecting parts on the front and rear wing surfaces, providing a detachable mechanical connection method, which facilitates the installation and removal of the front and rear wing surfaces, while ensuring the stability of the connection and ensuring that the rudder surface connector 202 can reliably drive the front and rear wing surfaces to move synchronously when it rotates.

[0063] A differential gear 301 is provided between the two partitions 200 on the same side, and the differential gear 301 meshes with the arc surface of the rudder surface connector 202.

[0064] The differential gear 301, through meshing with the arc surface of the control surface connector 202, enables differentiated control of the rotation speed or angle of the two control surface connectors 202, allowing the front and rear wing surfaces to deflect at different rates or angles, thereby precisely adjusting the aerodynamic layout of the UAV and meeting the control requirements of complex flight attitudes.

[0065] During the turning process of the front and rear wing surfaces, the differential gear 301 can automatically adjust its movement range to avoid overload of a single component, ensure smooth and continuous movement, and reduce flight attitude fluctuations.

[0066] A dual-axis digital servo motor 302 is installed inside the mounting housing 101. An extension rod 303 is fixed to one end of the output shaft of the dual-axis digital servo motor 302 that passes through the mounting housing 101. A metal servo arm 304 is provided at the end of the extension rod 303.

[0067] The dual-axis digital servo motor 302 can output rotational power in both directions to precisely control the movement of the extension rod 303 and the metal servo arm 304, thereby enabling independent adjustment of the UAV wing angle and meeting flight requirements such as rapid turning and attitude fine-tuning; its digital control characteristics can achieve high-precision and high-response angle control.

[0068] The extension rod 303 is used to extend the power transmission distance of the dual-axis digital servo motor 302, so that the metal servo arm 304 can be extended to the connection position of the UAV wing to realize the adjustment of the wing angle; at the same time, the extension rod 303 can enhance the stability of power transmission and avoid transmission failure due to excessive distance.

[0069] The metal control arm 304 is used to connect to the wings of the UAV and drives the change of wing angle through its own rotation; the metal material provides sufficient structural strength and rigidity to withstand the aerodynamic loads on the wings during flight, ensuring the reliability and stability of wing adjustment.

[0070] When a drone needs to change the angle of its wing surfaces:

[0071] When the all-moving servo motor 103 is activated, the all-moving servo motor 103 drives the pull rod 205 to move relative to each other. The two pull rods 205 drive the eccentric wheel connecting rod 204 to rotate. Since the eccentric wheel connecting rod 204 is connected to the control surface connector 202, the control surface connector 202 will also rotate relative to the wing movable link key 201.

[0072] The control surface connector 202 has a slot 300 that can be connected to the front and rear wings of the UAV. When the control surface connector 202 rotates, the front and rear wings of the UAV will also rotate, thereby changing the angle of the UAV wings and controlling the flight direction of the UAV.

[0073] When the control surface connector 202 rotates, the differential gear 301 can also rotate. The operator can precisely control the deflection angle difference between the front and rear wing surfaces through the gear ratio and structural design of the differential gear 301 to meet complex maneuver requirements.

[0074] When a drone needs to change its wing angle:

[0075] Start the dual-axis digital servo motor 302. The output shaft of the dual-axis digital servo motor 302 rotates, which drives the extension rod 303 to rotate synchronously. The extension rod 303 transmits power from the inside of the mounting housing 101 to the external metal servo arm 304.

[0076] Among them, the metal rudder arm 304 is connected to the wing by bolts or other connecting parts, and when it rotates, it drives the wing to change the angle around the fixed hinge point.

[0077] Among them, the dual-axis digital servo 302 can independently control two output axes, enabling the wing to adjust its angle in two dimensions and optimize its aerodynamic performance under different flight conditions.

[0078] In this embodiment, by activating the all-moving servo, the pull rod is moved relative to the servo, thereby indirectly driving the control surface connector 202 to rotate, thus achieving deflection at different angles on the front and rear wing surfaces. This allows for adjustment of the aerodynamic distribution of the UAV's wing surfaces, enabling the UAV to respond promptly during low-altitude flight, hovering, or large-maneuver attitude adjustments, thereby improving the UAV's maneuverability and control performance. Simultaneously, by setting up a dual-axis digital servo, extension rod, and metal control arm inside the mounting housing to form an independent wing angle adjustment system, the wing is rotated, achieving precise control of the wing angle.

[0079] The above embodiments are merely illustrative of the principles and effects of this utility model and are not intended to limit the scope of this utility model. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of this utility model. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in this utility model should still be covered by the claims of this utility model.

Claims

1. A front and rear wing coordinated control unmanned aerial vehicle structure, characterized in that, include: A load-bearing shaft (100) has an installation groove in the middle. Mounting housing (101), which is installed inside the mounting groove, and mounting plate (102) is fixed on the mounting housing (101). A fully movable servo motor (103) is mounted on the mounting plate (102); Adjustment components are symmetrically provided on both sides of the mounting shell (101); The adjustment component includes: Two partitions (200) are fixedly connected to the mounting shell (101) and are attached to both sides of the load-bearing shaft (100); A wing movable link key (201) is provided at the ends of the two partitions (200); The control surface connector (202) is rotatably disposed outside the wing movable link key (201) and located between the two partitions (200); An extension plate (203) is fixedly connected to the rudder surface connector (202); An eccentric wheel connecting rod (204) is rotatably connected to the extension plate (203); A pull rod (205) is connected at one end to the all-moving servo motor (103) and at the other end to the eccentric wheel connecting rod (204).

2. The UAV structure with coordinated control of fore and aft wings according to claim 1, characterized in that: The two levers (205) are rotationally symmetrical about the all-moving servo (103) at the center.

3. The UAV structure with coordinated control of fore and aft wings according to claim 1, characterized in that: The rudder surface connector (202) has a slot (300) on the side away from the partition (200).

4. The UAV structure with coordinated control of fore and aft wings according to claim 1, characterized in that: A differential gear (301) is provided between the two partitions (200) on the same side, and the differential gear (301) meshes with the arc surface of the rudder surface connector (202).

5. The UAV structure with coordinated control of fore and aft wings according to claim 1, characterized in that: The mounting housing (101) houses a dual-axis digital servo motor (302). The output shaft of the dual-axis digital servo motor (302) passes through the mounting housing (101) and is fixed with an extension rod (303). The end of the extension rod (303) is provided with a metal servo arm (304).

Images