A posture adjusting device capable of being quickly deployed

Abstract

The application discloses a posture adjusting device capable of being quickly unfolded, which comprises a quick unfolding device and a posture adjusting device; the quick unfolding device comprises a spring and a push rod; the posture adjusting device comprises a thigh wing, a shank wing, a horizontal adjusting device and a vertical adjusting device; one end of the spring is fixed on a machine body, and the other end is fixed on the push rod; the left and right ends of the push rod are respectively in contact with the horizontal adjusting devices on the two sides; the horizontal adjusting devices are connected with the motors fixed on the two sides of the machine body through spline connection; the vertical adjusting device is arranged at the tail end of the thigh wing; the vertical adjusting motor is arranged in the vertical adjusting device; and the vertical adjusting motor is connected with the shank wing through a crankshaft connecting rod. The application has the advantages of compact structure, quick unfolding of the wing, adjustable wing layout and lift area at any time, and easy popularization and application.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a rapidly deployable attitude adjustment device. Background Technology

[0002] Fixed-wing drone technology is now widely used in fields such as geographic surveying, agricultural monitoring, disaster relief, and emergency response. However, traditional fixed-wing drones have a fixed wing layout, a large turning radius, poor low-speed maneuverability, a large size, poor storage capacity, and are not easy to carry in large numbers. Summary of the Invention

[0003] In order to address the problems in the technical background and overcome the shortcomings of the prior art, the present invention provides a rapidly deployable attitude adjustment device.

[0004] The technical solution of this invention is:

[0005] A rapidly deployable attitude adjustment device is characterized by comprising a rapid deployment device and an attitude adjustment device; the rapid deployment device includes a spring 7 and a push rod 8; the attitude adjustment device includes a wing 2, a shank 3, a horizontal adjustment device 6, and a vertical adjustment device 11; one end of the spring 7 is fixed inside the fuselage 1, and the other end is connected to the push rod 8, which contacts the horizontal adjustment device 6. The horizontal adjustment device 6 is connected to a horizontal adjustment motor 4 fixed inside the fuselage 1 via a spline. The horizontal adjustment device 6 is fixed to one end of the wing 2. When the wing 2 rotates horizontally around the horizontal adjustment motor 4, the horizontal adjustment device 6 pushes the push rod 8 to move. When the wing 2 is fully retracted, the horizontal adjustment device 6 pushes the spring 7 to its maximum compression state. At this time, the pressure of the push rod 8 on the horizontal adjustment device 6 is within the rotational friction circle of the horizontal adjustment device 6, forming a self-locking state. To start, the horizontal adjustment motor 4 rotates one degree, the push rod 8 and the horizontal adjustment device 6 disengage from the self-locking state, the spring 7 pushes the push rod 8 to pop out, and the push rod 8 pushes the horizontal adjustment device 6 to rapidly deploy the wing 2, achieving faster wing deployment than relying solely on the motor. The fuselage 1 is equipped with two independent quick-deployment devices consisting of a right push rod 8 and a spring 7, which can deploy the front and rear wings separately. The fuselage 1 has two cavities: the upper cavity 10-1 stores the folded left front wing 2-3 and right front wing 2-1, and the lower cavity 10-2 stores the folded left rear wing 2-4 and right rear wing 2-2. The vertical adjustment device 11 is located at the other end of the wing 2. A vertical adjustment motor 5 is installed within the vertical adjustment device 11. The vertical adjustment motor 5 is connected to the shank wing 3 via a crankshaft connecting rod 9. The "C"-shaped structure of the crankshaft connecting rod 9 allows the shank wing 3 to rotate 180 degrees in the vertical plane. The upper part of the vertical adjustment device 11 is made of rigid material, while the lower part is made of flexible material to prevent collisions between the wing 2 and the vertical adjustment device 11 during movement.

[0006] After the wing 2 is deployed, the horizontal adjustment motor 4 rotates, driving the horizontal adjustment device 6 to rotate, thereby controlling the sweep angle of the wing 2 and the shank wing 3; the vertical adjustment motor 5 rotates, driving the vertical adjustment device 11 to rotate, thereby controlling the folding angle of the shank wing.

[0007] The wing 2, horizontal adjustment device 6, shank wing 3, and vertical adjustment device 11 form four wings on both sides of the fuselage 1: a right front wing 2-1 at the right front of the fuselage, a right rear wing 2-2 at the right rear, a left front wing 2-3 at the left front, and a left rear wing 2-4 at the left rear. The right front wing 2-1 and the left front wing 2-3 are identical and symmetrically arranged on the left and right sides of the fuselage 1, with an angle of attack range of 0 to 5 degrees. The right rear wing 2-2 and the left rear wing 2-4 are identical and symmetrically arranged on the left and right sides of the fuselage 1. The angle of attack is 15 degrees; the average chord length of the right rear wing 2-2 and left rear wing 2-4 is 30% of the average chord length of the right front wing 2-1 and left front wing 2-3; the trailing edge position of the right front wing 2-1 and left front wing 2-3 is 1.5% higher than the average chord length of the right rear wing 2-2 and left rear wing 2-4; when the trailing edges of the right front wing 2-1 and left front wing 2-3 are parallel to the leading edges of the right rear wing 2-2 and left rear wing 2-4, the distance between them is one-thirtieth of the average chord length of the right front wing 2-1 and left front wing 2-3. This configuration facilitates horizontal rotation of the wing 2, while improving the lift-to-drag ratio and reducing the wing area. The wing angle of attack design allows it to generate lift even when tilted forward.

[0008] The trailing edge of the shank wing 3 is arc-shaped; both the shank wing 2 and the shank wing 3 are non-biconvex airfoils. The outer contour of the cross-section of the vertical adjustment device 11 is the same as that of the outer contour of the cross-section of the shank wing 2. Attached Figure Description

[0009] Figure 1 This is a top view of a rapidly deployable attitude adjustment device.

[0010] Figure 2 This is a left view of a posture adjustment device that can be quickly deployed.

[0011] Figure 3 This is a cross-sectional view of an attitude adjustment device that can be quickly deployed.

[0012] Figure 4 This is a BB cross-sectional view of a rapidly deployable attitude adjustment device.

[0013] Figure 5 This is a cross-sectional view of the two sets of forward-folding wings of a rapidly deployable attitude adjustment device.

[0014] Figure 6This is a BB cross-section showing the folding of two sets of wings behind a rapidly deployable attitude adjustment device.

[0015] Figure 7 This is a diagram of a vertical adjustment device for a rapidly deployable attitude adjustment mechanism.

[0016] Figure 8 This is a diagram showing the rotation of the wings of a rapidly deployable attitude adjustment device.

[0017] Figure 9 This is a diagram showing the rotation of the shank of a rapidly deployable attitude adjustment device.

[0018] In the diagram: 1. Airframe; 2. Wings; 2-1. Right front wing; 2-2. Right rear wing; 2-3. Left front wing; 2-4. Left rear wing; 3. Shingle wing; 4. Horizontal adjustment motor; 5. Vertical adjustment motor; 6. Horizontal adjustment device; 7. Spring; 8. Push rod; 9. Crankshaft connecting rod; 10-1. Upper cavity; 10-2. Lower cavity; 11. Vertical adjustment device. Detailed Implementation

[0019] To more clearly illustrate the innovative concept of this application, the design and implementation details will be further explained below in conjunction with the accompanying drawings.

[0020] In the description of this invention, it should be noted that the terms "front," "rear," "left," "right," "inner side," "top," "left side," "bottom," "both sides," "one end," "the other end," and "middle," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0021] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "setting," "connection," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0022] During retraction, the wing 2 is manually rotated. When the wing 2 rotates, it drives the horizontal adjustment device 6 to rotate, which pushes the push rod 8 to compress the spring 7, folding it into the airframe cavity. When the wing 2 retracts, the spring 7, the push rod 8 and the horizontal adjustment device 6 reach a self-locking state, completing the wing recovery.

[0023] When wing deployment is required, the horizontal adjustment motor 4 rotates one degree, breaking the self-locking state between the spring 7, push rod 8, and horizontal adjustment device 6. The spring 7 pushes the push rod 8 out, which in turn pushes the horizontal adjustment device 6 to rapidly deploy the wings 2. The deployment of the first two sets of wings and the last two sets of wings can be controlled simultaneously or independently, depending on the actual situation. Flight then commences.

[0024] During flight, the wing sweep angle and wing force area can be controlled by adjusting the rotation angle of the four vertical adjustment motors 5 and the four horizontal adjustment motors 4 according to different flight states and environments, thereby realizing the flight attitude adjustment of the UAV.

[0025] After landing, the wing 2 can be used as the thigh of the legged robot, and the shank wing 3 can be used as the lower leg of the legged robot. By adjusting the rotation angle of the four vertical adjustment motors 5 and the four horizontal adjustment motors 4, it can crawl on the ground.

Claims

1. A rapidly deployable attitude adjustment device, comprising a rapid deployment device and an attitude adjustment device; the rapid deployment device comprises a spring (7) and a push rod (8); the attitude adjustment device comprises a wing (2), a shank wing (3), a horizontal adjustment device (6), and a vertical adjustment device (11); one end of the spring (7) is fixed in the body (1), and the other end is fixed on the push rod (8); the push rod (8) is in contact with the horizontal adjustment device (6); the horizontal adjustment device (6) is connected to a horizontal adjustment motor (4) fixed on both sides of the body (1) via a spline; the horizontal adjustment device (6) is fixed at one end of the wing (2); the vertical adjustment device (11) is disposed at the other end of the wing (2), and a vertical adjustment motor (5) is disposed inside the vertical adjustment device (11), the vertical adjustment motor (5) being connected to the shank wing (3) via a crankshaft connecting rod (9); Its features are: The wing (2), horizontal adjustment device (6), shank wing (3), and vertical adjustment device (11) together form four wings on both sides of the fuselage (1): a right front wing (2-1) on the right front of the fuselage, a right rear wing (2-2) on the right rear, a left front wing (2-3) on the left front, and a left rear wing (2-4) on the left rear. The right front wing (2-1) and the left front wing (2-3) are identical and symmetrically arranged on the left and right sides of the fuselage (1), with an angle of attack range of 0 to 5 degrees. The right rear wing (2-2) and the left rear wing (2-4) are identical and symmetrically arranged on the left and right sides of the fuselage (1), with an angle of attack range of 0 to 5 degrees. The angle is 15 degrees; the average chord length of the right rear wing (2-2) and the left rear wing (2-4) is 30% of the average chord length of the right front wing (2-1) and the left front wing (2-3); the trailing edge position of the right front wing (2-1) and the left front wing (2-3) is 1.5% higher than the average chord length of the right front wing (2-2) and the left rear wing (2-4) than the average chord length of the right front wing (2-1) and the left front wing (2-3); when the trailing edge of the right front wing (2-1) and the left front wing (2-3) is parallel to the leading edge of the right rear wing (2-2) and the left rear wing (2-4), the distance is one-thirtieth of the average chord length of the right front wing (2-1) and the left front wing (2-3).

2. The rapidly deployable attitude adjustment device according to claim 1, characterized in that: The wing (2) can rotate around the horizontal adjustment motor (4) in the horizontal plane; the horizontal adjustment device (6) is used to push the push rod (8) to compress the spring (7) when the wing is folded, and lock the spring (7) when the wing (2) is retracted; when the horizontal adjustment motor (4) rotates one degree, the spring (7) begins to pop out, and after the push rod (8) pushes the wing (2) to rotate 90 degrees, the spring (7) reaches the maximum tension state; the body is independently equipped with a rapid deployment device composed of two sets of right push rods (8) and springs (7); the shank (3) can rotate 180 degrees in the vertical plane with the vertical adjustment device (11).

3. The rapidly deployable attitude adjustment device according to claim 1, characterized in that: The trailing edge of the shin wing (3) is arc-shaped; both the wing (2) and the shin wing (3) are non-biconvex wing types.

4. The rapidly deployable attitude adjustment device according to claim 1, characterized in that: The outer contour of the cross section of the vertical adjustment device (11) is the same as that of the outer contour of the cross section of the wing (2); the upper part of the vertical adjustment device (11) is made of rigid material and the lower part is made of flexible material. A vertical adjustment motor (5) is installed inside, and the motor shaft is along the chord direction of the wing (2); the crankshaft connecting rod (9) is in the shape of "C", one end is fixed on the shaft of the vertical adjustment motor (5) and the other end is fixed on the shank (3), and can rotate with the vertical adjustment motor (5).

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