Electric steering engine control surface folding and unfolding locking mechanism

Abstract

The utility model relates to the technical field of steering engines, in particular to an electric steering engine control surface folding and unfolding locking mechanism which comprises a rudder shaft, one end of the rudder shaft is rotationally connected with a rudder sheet, the end face of one side of the rudder sheet is provided with an arc-shaped end face, and the end, facing the rudder sheet, of the rudder shaft is provided with a plug arranged in the rudder shaft in a sliding mode. The plug is used for locking the rudder sheet in the unfolded state, the rudder sheet and the rudder shaft are both connected with torsional springs used for assisting in unfolding of the rudder sheet, a limiting block used for preventing the rudder sheet from swinging in a reciprocating mode is arranged at one end of the rudder sheet, and when the rudder sheet is in the unfolded state, the limiting block is attached to a platform located at the bottom end of the rudder shaft. When the rudder sheet is in a horizontal state, the pressure spring exerts force on the plug, so that the plug abuts against the rudder sheet and the limiting block abuts against the platform, the purpose of locking the rudder sheet is achieved through the arrangement of the plug and the limiting block, and the situation that the stability of an aircraft is reduced due to unnecessary movement of the rudder sheet when the aircraft is in a flying state is avoided; and the problems that the flight attitude of the aircraft is changed and the maneuverability is reduced due to reciprocating swing of the rudder sheet are solved.

Description

Technical Field

[0001] The utility model relates to the technical field of steering gears, in particular to a folding, unfolding and locking mechanism for a steering surface of an electric steering gear. Background Art

[0002] In the technical field of intelligent ammunition and aircraft such as drones, small-caliber servos are often used to control the aircraft's elevator tail, directional tail and other devices to achieve stable flight and attitude control of the aircraft.

[0003] Existing small-caliber servos may not have a rudder blade locking mechanism, which may cause the rudder blades to move unnecessarily due to external factors when the aircraft does not need to adjust its attitude, causing the aircraft's attitude to change, thereby affecting its stability. During flight, the autopilot system needs to adjust the aircraft's attitude by controlling the servo. If there is no rudder blade locking mechanism in the servo, the rudder blades may move without a control signal, causing the autopilot system to be unable to accurately control the aircraft's attitude, thereby reducing controllability.

[0004] Therefore, it is necessary to invent a folding and unfolding locking mechanism for the rudder surface of an electric steering gear to solve the above problems. Utility Model Content

[0005] In order to address the deficiencies in the prior art, the purpose of the utility model is to provide an electric servo rudder surface folding and unfolding locking mechanism, which solves the problem that existing small-caliber servos may often not have a rudder blade locking mechanism during actual use, which may cause the aircraft's attitude to change when the aircraft does not need to adjust its attitude, thereby affecting its stability. During flight, if there is no rudder blade locking mechanism in the servo, the rudder blade may move without a control signal, causing the autopilot system to be unable to accurately control the aircraft's attitude, thereby reducing the problem of maneuverability.

[0006] In order to achieve the above objectives, the utility model adopts the following technical solutions:

[0007] A folding and unfolding locking mechanism for a rudder surface of an electric steering gear comprises a rudder shaft, one end of the rudder shaft is rotatably connected to a rudder blade, one side end face of the rudder blade is provided with an arc-shaped end face, the end of the rudder shaft facing the rudder blade is provided with a plug slidably arranged inside the plug, the plug is used to lock the rudder blade in the unfolded state, the rudder blade and the rudder shaft are both connected to a torsion spring for assisting the rudder blade in unfolding, one end of the rudder blade is provided with a limit block for preventing the rudder blade from swinging back and forth, and when the rudder blade is in the unfolded state, the limit block fits with a platform located at the bottom end of the rudder shaft.

[0008] As a preferred solution of the utility model, a circular groove is provided at one end of the rudder shaft, the position of the circular groove is adapted to the arc-shaped end face in the unfolded state, a compression spring is provided inside the circular groove, one end of the compression spring is fitted with the plug, and the other end of the compression spring is fitted with the inner wall of the circular groove.

[0009] As a preferred solution of the utility model, an end of the plug facing the rudder blade is provided with an oblique angle, and the arc-shaped end surface can shrink the rudder blade by squeezing the oblique angle.

[0010] As a preferred solution of the utility model, a rectangular groove is provided at the top end of the rudder shaft on one side of the circular groove, and the size of the rectangular groove is matched with the size of the head end of the rudder blade.

[0011] As a preferred solution of the utility model, the rudder shaft is provided with a mounting hole 1 below the circular groove, the head end of the rudder plate is provided with a mounting hole 2, a rotating shaft is passed through the mounting hole 1 and the mounting hole 2, the rotating shaft extends to both sides of the rudder shaft, and the torsion spring is sleeved on the outer wall of the rotating shaft.

[0012] As a preferred solution of the utility model, a plug hole is provided on the side wall of the rudder shaft, one end of the torsion spring is inserted into the plug hole, and a rocker arm at the other end of the torsion spring is arranged on the upper surface of the rudder blade.

[0013] In the above technical solution, the technical effects and advantages provided by the utility model are:

[0014] The utility model discloses that when the rudder blade needs to be unfolded, the rudder blade can be unfolded from a vertical state to a horizontal state under the action of a torsion spring. When the rudder blade is in the horizontal state, the compression spring applies force to the plug, so that the plug abuts against the rudder blade, and the limit block abuts against the platform. The purpose of locking the rudder blade is achieved by setting the plug and the limit block, thereby avoiding the problem that the stability of the aircraft is reduced due to unnecessary movement of the rudder blade in the flight state, and the flight attitude of the aircraft is changed and the maneuverability is reduced due to the reciprocating swing of the rudder blade. When the rudder blade needs to be retracted, the rudder blade is rotated, and the arc-shaped end face on one side of the rudder blade is squeezed against the oblique angle of the plug, and the plug slides toward the inside of the rudder shaft, and the rudder blade is rotated to the rectangular groove. After the rudder blade is stored, the aircraft is released to achieve automatic unfolding of the rudder blade. The utility model is applicable to the scene with limited launch space. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0016] Figure 2 It is a schematic diagram of the overall top view structure of the utility model;

[0017] Figure 3 This is a schematic diagram of the cross-sectional structure of the rudder shaft of the utility model;

[0018] Figure 4 This is a schematic diagram of the main structure of the rudder blade of the utility model.

[0019] Explanation of the reference numerals in the accompanying drawings: 1. rudder shaft; 2. rotating shaft; 3. torsion spring; 4. rudder blade; 5. circular groove; 6. platform; 7. limit block; 8. arc-shaped end face; 9. compression spring; 10. plug; 11. socket; 12. rectangular groove; 13. mounting hole one; 14. mounting hole two. DETAILED DESCRIPTION

[0020] The utility model is further described below in conjunction with the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the utility model, and cannot be used to limit the protection scope of the utility model.

[0021] The utility model provides Figure 1-4 The rudder surface folding and unfolding locking mechanism of an electric servo shown in the figure comprises a rudder shaft 1, one end of the rudder shaft 1 is rotatably connected with a rudder blade 4, one side end face of the rudder blade 4 is provided with an arc-shaped end face 8, the end of the rudder shaft 1 facing the rudder blade 4 is provided with a plug 10 slidably arranged inside the rudder shaft 1, the plug 10 is used to lock the rudder blade 4 in the unfolded state, the rudder blade 4 and the rudder shaft 1 are both connected with a torsion spring 3 for assisting the unfolding of the rudder blade 4, one end of the rudder blade 4 is provided with a limit block 7 for preventing the rudder blade 4 from reciprocatingly swinging, when the rudder blade 4 is in the unfolded state, the limit block 7 is fitted with a platform 6 located at the bottom end of the rudder shaft 1, the setting of the limit block 7 can prevent the rudder blade 4 from being over-expanded, and prevent the rudder blade 4 from having a flipping angle that is too large, thereby resulting in a decrease in the control accuracy, the outer surface of the limit block 7 can be specially treated, such as surface hardening, etc., to prevent the limit block 7 from being worn after the rudder blade 4 is repeatedly moved, resulting in an error in the unfolding angle of the rudder blade 4, thereby reducing the flight accuracy of the aircraft.

[0022] A circular groove 5 is provided at one end of the rudder shaft 1, and the position of the circular groove 5 is adapted to the arc-shaped end face 8 in the unfolded state. A compression spring 9 is provided inside the circular groove 5, and one end of the compression spring 9 is fitted with a plug 10, and the other end of the compression spring 9 is fitted with the inner wall of the circular groove 5. Through the arrangement of the compression spring 9 and the plug 10, the rebound of the rudder blade 4 can be effectively avoided, and the unfolding speed of the rudder blade 4 can be increased. The faster unfolding speed of the rudder blade 4 can improve the response capability of the aircraft, thereby improving the maneuverability of the aircraft.

[0023] The end of the plug 10 facing the rudder blade 4 is provided with a bevel, and the arc-shaped end surface 8 can shrink the rudder blade 4 by squeezing the bevel. The bevel set at the end of the plug 10 facing the rudder blade 4 can reduce the difficulty of restoring the rudder blade 4 to the retracted state. The bevel setting of the plug 10 can also be changed to a rounded corner, so as to avoid the problem of excessive friction and inconvenience in shrinkage when the corner contacts the rudder blade 4.

[0024] The rudder shaft 1 is provided with a rectangular groove 12 at the top end on one side of the circular groove 5. The size of the rectangular groove 12 is adapted to the size of the head end of the rudder blade 4. The rectangular groove 12 should be formed to avoid the problem of the plug 10 and the compression spring 9 flowing out and falling along the gap of the rectangular groove 12, thereby causing the function for locking the rudder blade 4 to fail, affecting the stability and maneuverability of the aircraft.

[0025] The rudder shaft 1 is provided with a mounting hole 13 below the circular groove 5, and the head end of the rudder blade 4 is provided with a mounting hole 2 14. The mounting hole 13 and the mounting hole 2 14 are jointly penetrated by a rotating shaft 2, and the rotating shaft 2 extends to both sides of the rudder shaft 1. The torsion spring 3 is sleeved on the outer wall of the rotating shaft 2. The diameters of both ends of the rotating shaft 2 are larger than the inner diameter of the rotating shaft 2, so as to intercept and prevent the torsion spring 3 from falling off, thereby affecting the deployment speed of the rudder blade 4.

[0026] The side wall of the rudder shaft 1 is provided with an insertion hole 11, and one end of the torsion spring 3 is inserted into the insertion hole 11, and the other end of the torsion spring 3 is provided with a rocker arm on the upper surface of the rudder blade 4. By arranging the rocker arm of the torsion spring 3 on the upper surface of the rudder blade 4, the force-bearing surface after deformation is on the rudder blade 4, thereby enhancing the locking effect of the rudder blade 4.

[0027] When the rudder blade 4 needs to be unfolded, the rudder blade 4 can be unfolded from a vertical state to a horizontal state under the action of the torsion spring 3. When the rudder blade 4 is in the horizontal state, the compression spring 9 applies force to the plug 10 to make the plug 10 abut against the rudder blade 4 and the limit block 7 abut against the platform 6. The purpose of locking the rudder blade 4 is achieved through the arrangement of the plug 10 and the limit block 7, so as to avoid the problem that the stability of the aircraft is reduced due to unnecessary movement of the rudder blade 4 in the flight state, and the flight attitude of the aircraft is changed and the maneuverability is reduced due to the reciprocating swing of the rudder blade 4. When the rudder blade 4 needs to be retracted, the rudder blade 4 is rotated, and the arc end face 8 on one side of the rudder blade 4 squeezes the bevel angle of the plug 10, and the plug 10 slides toward the inside of the rudder shaft 1, and the rudder blade 4 rotates to the rectangular groove 12. After the rudder blade 4 is stored, the rudder blade 4 is automatically unfolded by releasing the aircraft. This is suitable for scenes with limited launching space.

[0028] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as the protection scope of the present invention.

Claims

1. A folding and unfolding locking mechanism for the rudder surface of an electric servo. Features: The invention comprises a rudder shaft (1), one end of which is rotatably connected to a rudder blade (4), one end face of which is provided with an arc-shaped end face (8), one end of which is provided with a plug (10) which is slidably arranged inside the rudder shaft (1) and which is used to lock the rudder blade (4) in an unfolded state, the rudder blade (4) and the rudder shaft (1) are both connected with a torsion spring (3) for assisting the rudder blade (4) in unfolding, one end of which is provided with a limit block (7) for preventing the rudder blade (4) from reciprocatingly swinging, and when the rudder blade (4) is in the unfolded state, the limit block (7) is in contact with a platform (6) located at the bottom end of the rudder shaft (1).

2. The electric steering gear control surface folding and unfolding locking mechanism according to claim 1, Features: A circular groove (5) is provided at one end of the rudder shaft (1), the position of the circular groove (5) being matched with the arc-shaped end surface (8) in the unfolded state, a compression spring (9) is provided inside the circular groove (5), one end of the compression spring (9) is fitted with the plug (10), and the other end of the compression spring (9) is fitted with the inner wall of the circular groove (5).

3. The electric steering gear rudder surface folding and unfolding locking mechanism according to claim 2, Features: An end of the plug (10) facing the rudder blade (4) is provided with an oblique angle, and the arc-shaped end surface (8) can shrink the rudder blade (4) by squeezing the oblique angle.

4. The electric steering gear rudder surface folding and unfolding locking mechanism according to claim 2, Features: A rectangular groove (12) is provided at the top end of the rudder shaft (1) on one side of the circular groove (5), and the size of the rectangular groove (12) is matched with the size of the head end of the rudder blade (4).

5. The electric steering gear control surface folding and unfolding locking mechanism according to claim 1, Features: The rudder shaft (1) is provided with a mounting hole (13) below the circular groove (5), and the head end of the rudder plate (4) is provided with a mounting hole (14). A rotating shaft (2) is passed through the mounting hole (13) and the mounting hole (14). The rotating shaft (2) extends to both sides of the rudder shaft (1), and the torsion spring (3) is sleeved on the outer wall of the rotating shaft (2).

6. The electric steering gear control surface folding and unfolding locking mechanism according to claim 5, Features: The side wall of the rudder shaft (1) is provided with an insertion hole (11), one end of the torsion spring (3) is inserted into the insertion hole (11), and the other end of the torsion spring (3) is provided with a rocker arm on the upper surface of the rudder sheet (4).

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