Attitude adjusting device capable of being quickly unfolded

Abstract

The invention discloses a posture adjusting device capable of being rapidly unfolded. The posture adjusting device comprises a rapid unfolding device and a posture adjusting device body. The quick unfolding device comprises a spring and a push rod; the posture adjusting device comprises a thigh wing, a shin wing, a horizontal adjusting device and a vertical adjusting device; the left end and the right end of the push rod make contact with the horizontal adjusting devices on the two sides respectively, and the horizontal adjusting devices are connected with the motors fixed to the two sides of the machine body through splines. A vertical adjusting device is arranged at the tail end of the thigh wing, a vertical adjusting motor is arranged in the vertical adjusting device, and the vertical adjusting motor is connected with the thigh wing through a crankshaft connecting rod. The structure is compact, the wings can be rapidly unfolded, the wing layout and the lift force area can be adjusted at any time, and application and popularization are easy.

Description

Technical Field

[0001] The present application relates to the technical field of unmanned aerial vehicles, and in particular to a posture adjustment device that can be rapidly deployed. Background Art

[0002] Nowadays, fixed-wing UAV technology has been widely used in geographic surveying and mapping, agricultural monitoring, disaster rescue and emergency response. However, traditional fixed-wing UAVs have fixed wing layout, large turning radius, poor low-speed maneuverability, large size, poor storage, and are not easy to carry in large quantities. Summary of the invention

[0003] In order to solve the problems in the technical background and overcome the shortcomings of the prior art, the present invention provides a posture adjustment device that can be quickly deployed.

[0004] The technical solution of the present invention is:

[0005] A fast deployable attitude adjustment device, characterized in that: it comprises a fast deploying device and an attitude adjustment device; the fast deploying device comprises a spring 7 and a push rod 8; the attitude adjustment device comprises a thigh 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 connected to the push rod 8, the push rod 8 contacts the horizontal adjustment device 6, the horizontal adjustment device 6 is connected to the horizontal adjustment motor 4 fixed in the body 1 through a spline, the horizontal adjustment device 6 is fixed at one end of the thigh wing 2, when the thigh wing 2 rotates horizontally around the horizontal adjustment motor 4, the horizontal adjustment device 6 will push the push rod 8 to move, when the thigh wing 2 is fully retracted, the horizontal adjustment device 6 pushes the spring 7 to the maximum compression state, at this time, the pressure of the push rod 8 on the horizontal adjustment device 6 is in the rotation friction circle of the horizontal adjustment device 6, forming a self-locking state, when starting, the horizontal adjustment motor 4 rotates once, the push rod 8 and the horizontal adjustment device 6 are out of 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 make the thigh wing 2 quickly deploy, thereby achieving a wing deployment faster than relying on the motor alone. Two independent quick deployment devices composed of right push rod 8 and spring 7 are arranged in the body 1, and the front wing and the rear wing can be deployed separately. Two cavities are arranged in the body 1, the upper cavity 10-1 is used to store the folded left front wing 2-3 and right front wing 2-1, and the lower cavity 10-2 is used to store the folded left rear wing 2-4 and right rear wing 2-2. The vertical adjustment device 11 is arranged at the other end of the thigh wing 2, and the vertical adjustment motor 5 is arranged in the vertical adjustment device 11. The vertical adjustment motor 5 is connected with the shank wing 3 through the crankshaft connecting rod 9. The "C"-shaped structure of the crankshaft connecting rod 9 enables the shank wing 3 to rotate the vertical adjustment motor 5 180 degrees in the vertical plane. The upper half of the vertical adjustment device 11 is made of rigid material, and the lower half is made of flexible material to avoid collision between the thigh wing 2 and the vertical adjustment device 11 when the thigh wing 2 moves.

[0006] After the thigh wing 2 is unfolded, the horizontal adjustment motor 4 rotates, driving the horizontal adjustment device 6 to rotate, thereby controlling the sweep angle of the thigh 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 thigh wing 2, the horizontal adjustment device 6, the shank wing 3 and the vertical adjustment device 11 form four wings on both sides of the fuselage 1, which are a right front wing 2-1 formed on the right front of the fuselage, a right rear wing 2-2 formed on the right rear, a left front wing 2-3 formed on the left front, and a left rear wing 2-4 formed on the left rear; the right front wing 2-1 and the left front wing 2-3 are exactly the same, and are symmetrically arranged on the left and right sides of the fuselage 1, with an angle of attack ranging from 0 degrees to 5 degrees; the right rear wing 2-2 and the left rear wing 2-4 are exactly the same, and are 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 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 2-1 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 spacing is one thirtieth of the average chord length of the right front wing 2-1 and the left front wing 2-3. Such a setting helps the wing 2 to rotate horizontally, and at the same time can improve the lift-to-drag ratio and reduce the wing area. The design of the wing angle of attack enables it to have lift even when it is tilted forward.

[0008] The rear edge of the shank wing 3 is arc-shaped; the thigh wing 2 and the shank wing 3 are both non-biconvex airfoil-shaped. The cross-sectional outer contour of the vertical adjustment device 11 is the same as the cross-sectional outer contour of the thigh wing 2. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 The figure is a top view of a posture adjustment device that can be quickly deployed.

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

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

[0012] Figure 4 It is a BB cross-sectional view of a posture adjustment device that can be quickly deployed.

[0013] Figure 5 A diagram of the folded front two sets of wings in the AA section of a rapidly deployable attitude adjustment device.

[0014] Figure 6A diagram showing the two sets of wings folded at the rear of the BB section of a rapidly deployable attitude adjustment device.

[0015] Figure 7 A diagram of a vertical adjustment device of a posture adjustment device that can be quickly deployed.

[0016] Figure 8 A diagram of the rotation of the wing of a rapidly deployable attitude adjustment device.

[0017] Fig. 9 A diagram of the rotation of the shin wing of a rapidly deployable attitude adjustment device.

[0018] In the figure: 1 fuselage, 2 wings, 2-1 right front wing, 2-2 right rear wing, 2-3 left front wing, 2-4 left rear wing, 3 wings, 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 DESCRIPTION

[0019] In order to more clearly illustrate the innovative concept of the present application, the design and implementation details will be further described in detail below in conjunction with the drawings in the specification.

[0020] In the description of the present invention, it should be noted that the terms "front", "rear", "left", "right", "inside", "top", "left side", "bottom", "both sides", "one end", "the other end", "middle", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0021] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "setting", "connection", etc. should be understood in a broad sense. 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 it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0022] When retracting, the wing 2 is manually rotated, and the rotation of the wing 2 drives the horizontal adjustment device 6 to rotate, pushing the push rod 8 to compress the spring 7, and folding it into the cavity of the fuselage. When the wing 2 is retracted, the spring 7, the push rod 8 and the horizontal adjustment device 6 reach a self-locking state, completing the wing retraction.

[0023] When the wings need to be unfolded, the horizontal adjustment motor 4 rotates once to break the self-locking state between the spring 7, the push rod 8 and the horizontal adjustment device 6. The spring 7 pushes the push rod 8 to pop out, pushing the horizontal adjustment device 6 to drive the wings 2 to unfold quickly. The front two sets of wings and the rear two sets of wings can be controlled to unfold simultaneously or independently according to actual conditions. Then the flight process begins.

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

[0025] After landing, the femoral wing 2 can be used as the thigh of the foot-type robot, and the shin wing 3 can be used as the calf of the foot-type robot. By adjusting the rotation angles of the four vertical adjustment motors 5 and the four horizontal adjustment motors 4, the robot can crawl on the ground.

Claims

1. A rapidly deployable posture adjustment device, characterized in that: The invention comprises a quick deployment device and a posture adjustment device; the quick deployment device comprises a spring (7) and a push rod (8); the posture adjustment device comprises a thigh 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 machine 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 machine body (1) through a spline; the horizontal adjustment device (6) is fixed at one end of the thigh wing (2); the vertical adjustment device (11) is arranged at the other end of the thigh wing (2), a vertical adjustment motor (5) is arranged in the vertical adjustment device (11), and the vertical adjustment motor (5) is connected to the shank wing (3) through a crankshaft connecting rod (9).

2. A rapidly deployable posture adjustment device according to claim 1, characterized in that: The thigh wing (2), the horizontal adjustment device (6), the shank wing (3) and the vertical adjustment device (11) form four wings on both sides of the fuselage (1), which are a right front wing (2-1) formed on the right front of the fuselage, a right rear wing (2-2) formed on the right rear, a left front wing (2-3) formed on the left front, and a left rear wing (2-4) formed on the left rear; the right front wing (2-1) and the left front wing (2-3) are completely identical and symmetrically arranged on the left and right sides of the fuselage (1), with an angle of attack ranging from 0 degrees to 5 degrees; the right rear wing (2-2) and the left rear wing (2-4) are completely identical and symmetrically arranged on the left and right sides of the fuselage (1), with an angle of attack ranging from 0 degrees 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 (2-1) and the left rear wing (2-3); when the trailing edges of the right front wing (2-1) and the left front wing (2-3) are parallel to the leading edges of the right rear wing (2-2) and the left rear wing (2-4), the spacing is one thirtieth of the average chord length of the right front wing (2-1) and the left front wing (2-3).

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

4. The rapidly deployable posture adjustment device according to claim 1, characterized in that: The rear edge of the tibia wing (3) is arc-shaped; the femoral wing (2) and the tibia wing (3) are both non-biconvex airfoil shapes.

5. The rapidly deployable posture adjustment device according to claim 1, characterized in that: The cross-sectional outer contour of the vertical adjustment device (11) is the same as the cross-sectional outer contour of the thigh 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, and a vertical adjustment motor (5) is arranged inside, and the motor shaft is along the chord direction of the thigh wing (2); the crankshaft connecting rod (9) is in a "C" shape, one end of which is fixed on the shaft of the vertical adjustment motor (5), and the other end is fixed on the shank wing (3), and can rotate with the vertical adjustment motor (5).

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