Integrated micro steering engine

Abstract

An integrated micro steering engine comprises a shell and a rudder wing control assembly. The shell is annular, a supporting base is arranged in the shell, a plurality of through grooves are formed in the circumferential side of the shell in the circumferential direction, the length direction of the through grooves is parallel to the axis of the shell, and a connecting block is arranged in the center of the bottom of the supporting base. The rudder wing control assembly comprises a plurality of rudder wing control modules which are arranged in the shell and arranged at intervals in the circumferential direction of the shell, each rudder wing control module comprises a rotating shaft which is installed on the side wall of the connecting block and rotates around the axis of the rotating shaft, two installation blocks are arranged at the end, away from the connecting block, of each rotating shaft at an interval, and a rudder wing is rotationally connected between the installation blocks. The rotation angle of the rudder wing is 90 degrees, and the rudder wing is located in the through groove. A limiting groove is formed in the end, away from the connecting block, of the rotating shaft, an ejector rod moving in the axis direction of the limiting groove is arranged in the limiting groove, a connecting plate is arranged at one end of the rudder wing, and the ejector rod pushes the connecting plate during application. According to the device, through the folding design of the rudder wings, the steering engine is more integrated, the diameter and the size of the steering engine are reduced, and high practicability is achieved.

Description

Technical Field

[0001] This utility model relates to the field of servo motor technology, and in particular to an integrated micro servo motor. Background Technology

[0002] A servo motor is a type of servo control system that uses a motor as the drive element to rotate a control fin. It is widely used in aerospace, shipbuilding, robotics, and other fields. Especially in aircraft control, multiple servos are often configured to adjust the aircraft's attitude by changing the angle of the control fins, enabling the aircraft to maintain or change its flight trajectory to achieve the desired goal. Currently, a common configuration consists of one servo motor, one controller, one motor, and a reduction gear, all connected to the control fin. Therefore, the drive and control components of a servo motor often occupy a significant amount of space, making it difficult to use in smaller aircraft and limiting miniaturization and cost control. Utility Model Content

[0003] In view of the shortcomings of the above-mentioned prior art, this application provides an integrated micro servo motor. Through the folding design of the servo wings, it is more integrated, reducing the diameter and volume of the servo motor, and has strong practicality.

[0004] To achieve the above objectives, the present invention employs the following technology:

[0005] An integrated micro servo motor includes: a housing and a rudder control assembly.

[0006] The shell is annular, with a support base inside and multiple through slots along its circumference. The length of the through slots is parallel to the axis of the shell, and a connecting block is located at the center of the bottom of the support base. The rudder control assembly includes multiple rudder control modules located inside the shell and spaced apart along its circumference. Each rudder control module includes a rotating shaft mounted on the side wall of the connecting block and rotating around its own axis. Two spaced mounting blocks are located at the end of the rotating shaft away from the connecting block. A rudder wing is rotatably connected between the mounting blocks. The rudder wing rotates at a 90-degree angle and is located in the through slot.

[0007] Furthermore, the side wall of the connecting block has multiple through holes arranged at intervals along the circumferential direction. Bearings are installed in the through holes, and the other end of the rotating shaft is fitted into the inner wall of the bearing. The end of the rotating shaft away from the connecting block has a limiting groove with a circular cross-section. One end of the limiting groove extends to the end of the mounting block. A pad is provided at the bottom of the limiting groove. The end of the pad near the mounting block has a groove. A screw passes through the groove. The threaded part of the screw passes through the pad and the rotating shaft in sequence and is connected to the connecting ring. The end of the connecting block has a mounting hole extending to the end of the support base. The connecting ring is installed in the mounting hole.

[0008] Furthermore, a connecting plate is provided at one end of the rudder wing, the connecting plate is sleeved on the cam shaft, the cam shaft is installed between two mounting blocks, a stop block is provided between the mounting blocks, and a hook block is provided at the end of the connecting plate. When the length direction of the connecting plate is parallel to the axis of the rotating shaft, the side of the hook block abuts against the end face of the stop block.

[0009] Furthermore, a push rod is provided in the limiting groove, and a slot is provided at one end of the push rod near the center of the connecting block. A spring is provided in the slot, and at least part of the spring is located outside the slot. The spring abuts against the bottom of the slot and the screw respectively, and is always in a compressed state. The other end of the push rod is arc-shaped, and the side of the connecting plate is provided with a slope. When the length direction of the connecting plate is parallel to the axis of the rotating shaft, the arc-shaped part of the push rod contacts the slope of the connecting plate. When the length direction of the connecting plate is perpendicular to the axis of the rotating shaft, the end face of the push rod abuts against the side of the connecting plate.

[0010] Furthermore, the sidewall of the connecting ring is provided with multiple threaded holes along the circumferential direction, and a coaxial convex ring is provided on the outside of the threaded holes. The inner wall of the convex ring is provided with threads, and the screw is connected to the inner wall of the convex ring. The end of the rotating shaft near the center of the connecting block is provided with a through hole that extends to the limiting groove. The diameter of the through hole is smaller than the outer diameter of the pad. The convex ring is located in the through hole, and the pad abuts against the end face of the convex ring.

[0011] Furthermore, the outer side of the rotating shaft is connected to the rotating end of the reduction mechanism and is coaxially arranged with the rotating end of the reduction mechanism. The reduction mechanism is mounted on the support base, and its input end is connected to the output end of the motor. The motor is mounted on the support base.

[0012] The beneficial effects of this utility model are as follows: through the folding design of the rudder wing, the rudder wing can be retracted into the shell, thereby making the servo motor more integrated, reducing the diameter and volume of the servo motor, and making it easier to place it in a smaller aircraft. Attached Figure Description

[0013] The accompanying drawings described herein are merely illustrative of selected embodiments, not all possible implementations, and are not intended to limit the scope of this invention.

[0014] Figure 1 This is a schematic diagram of the overall structure of an embodiment of this application.

[0015] Figure 2 This is a schematic cross-sectional view of the overall structure of an embodiment of this application.

[0016] Figure 3 This is a three-dimensional schematic diagram of the control component according to an embodiment of this application.

[0017] Figure 4 This is a three-dimensional schematic diagram of the control component according to an embodiment of this application from another angle.

[0018] Figure 5 This is a cross-sectional structural diagram of the control component according to an embodiment of this application.

[0019] Figure 6 for Figure 5 Enlarged diagram of point A. Detailed Implementation

[0020] To make the objectives, technical solutions and advantages of the present utility model clearer, the implementation methods of the present utility model will be described in detail below with reference to the accompanying drawings. However, the embodiments described in the present utility model are only some embodiments of the present utility model, and not all embodiments.

[0021] like Figures 1-6 As shown, this example provides an integrated micro servo motor, including: a housing 100 and a servo control assembly 200.

[0022] The housing 100 is annular, and a support base 101 is provided inside the housing 100. Multiple through slots 102 are provided along the circumferential direction on the periphery of the housing 100. The length direction of the through slots 102 is parallel to the axis of the housing 100. A connecting block 103 is provided at the center of the bottom of the support base 101. The rudder control assembly 200 includes multiple rudder control modules disposed within the housing 100 and spaced apart along its circumference. Each rudder control module includes a rotating shaft 201 mounted on the side wall of the connecting block 103 and rotating about its own axis. Two [unclear - possibly referring to components or features] are provided at the end of the rotating shaft 201 away from the connecting block 103. The mounting blocks 202 are spaced apart, and the mounting blocks 202 are provided with rotatable wing 203 connected between them. The wing 203 rotates at an angle of 90 degrees and is located in the through groove 102. When the wing 203 is retracted, the length direction of the wing 203 is parallel to the axis of the housing 100. When the wing 203 is deployed, the length direction of the wing 203 is perpendicular to the axis of the housing 100. The through groove 102 can be set to T-shape to avoid interference between the wing 203 and the housing 100 when the wing 203 is deployed and the deflection angle of the wing 203 is adjusted.

[0023] Specifically, the sidewall of the connecting block 103 has multiple spaced through holes 104 along the circumferential direction. Bearings 107 are installed in the through holes 104. The other end of the rotating shaft 201 is fitted into the inner wall of the bearing 107. The end of the rotating shaft 201 away from the connecting block 103 has a circularly shaped limiting groove 204. One end of the limiting groove 204 extends to the end of the mounting block 202. A pad 205 is provided at the bottom of the limiting groove 204. A groove 206 is provided at the end of the pad 205 near the mounting block 202. A screw 207 is inserted through the middle. The threaded part of the screw 207 passes through the pad 205 and the rotating shaft 201 in sequence and is connected to the connecting ring 105. The end of the connecting block 103 is provided with a mounting hole 106 that extends through to the end of the support base 101. The connecting ring 105 is installed in the mounting hole 106, thereby installing the rotating shaft 201 in the connecting block 103. Under the action of the bearing 107, the rotating shaft 201 can be rotated around its own axis, so as to adjust the deflection angle of the rudder 203.

[0024] Specifically, one end of the rudder 203 is provided with a connecting plate 208, which is sleeved on the cam shaft 209. The cam shaft 209 is installed between two mounting blocks 202, and a stop block 210 is provided between the mounting blocks 202. The end of the connecting plate 208 is provided with a hook block 211. When the length direction of the connecting plate 208 is parallel to the axis of the rotating shaft 201, the side of the hook block 211 abuts against the end face of the stop block 210, thereby putting the rudder 203 in the deployed state.

[0025] Specifically, a push rod 212 is provided in the limiting groove 204. A slot 213 is provided at one end of the push rod 212 near the center of the connecting block 103. A spring 214 is provided in the slot 213, with at least a portion of the spring 214 located outside the slot 213. The spring 214 abuts against the bottom of the slot 213 and the screw 207, and is always in a compressed state, causing the push rod 212 to always tend to move away from the bottom of the limiting groove 204. Furthermore, the circumference of the other end of the push rod 212 is arc-shaped. The side of the connecting plate 208 is provided with a slope. When the length of the connecting plate 208... When the direction is parallel to the axis of the rotating shaft 201, the arc-shaped part of the push rod 212 contacts the inclined surface of the connecting plate 208, thereby preventing the push rod 212 from moving further. When the length direction of the connecting plate 208 is perpendicular to the axis of the rotating shaft 201, the end face of the push rod 212 abuts against the side of the connecting plate 208, making the state of the rudder 203 more stable. In actual operation, when it is necessary to deploy the rudder 203, the constraint force on the rudder 203 can be released manually or by the aircraft. At this time, under the action of the spring 214, the push rod 212 moves towards... Moving away from the bottom of the limiting groove 204, the rudder 203 will rotate around the axis of the convex shaft 209 until the hook block 211 abuts against the stop block 210. The length direction of the rudder 203 is parallel to the axis of the limiting groove 204. At the same time, the arc-shaped part of the push rod 212 contacts the inclined surface of the connecting plate 208, preventing the push rod 212 from moving further, thereby realizing the deployment of the rudder 203. When it is necessary to fold the rudder 203, a restraining force is applied to the rudder 203 manually or by the aircraft, forcing the rudder 203 to rotate around the convex shaft 209. When the axis of shaft 209 rotates, the hook block 211 and the stop block 210 disengage during the rotation of the rudder wing 203, and the push rod 212 is forced to move back. The spring 214 is also further compressed until the rudder wing 203 rotates 90 degrees and its length direction is parallel to the axis of the housing 100. At this time, the end of the push rod 212 abuts against the side of the connecting plate 208, and the folding operation of the rudder wing 203 is completed. After that, it is only necessary to continuously apply a constraint force to the rudder wing 203 through the aircraft to maintain the folded state of the rudder wing 203.

[0026] Specifically, the connecting ring 105 has multiple threaded holes 108 along its circumferential direction on its sidewall. A coaxial convex ring 109 is provided on the outside of the threaded holes 108. The inner wall of the convex ring 109 is threaded. A screw 207 is connected to the inner wall of the convex ring 109. The end of the rotating shaft 201 near the center of the connecting block 103 has a through hole 215 that extends to the limiting groove 204. The diameter of the through hole 215 is smaller than the outer diameter of the pad 205. The convex ring 109 is located in the through hole 215, and the pad 205 abuts against the end face of the convex ring 109, so that the pad 205 directly contacts the end face of the convex ring 109, reducing the contact area between the pad 205 and the bottom of the limiting groove 204. This reduces the locking force on the rotating shaft 201 when the screw 2017 locks the pad 205, ensuring that the rotating shaft 201 is installed stably while also enabling the rotation of the rotating shaft 201.

[0027] Specifically, the outer side of the rotating shaft 201 is connected to the rotating end of the reduction mechanism and is coaxially arranged with the rotating end of the reduction mechanism. The reduction mechanism is installed on the support base 101, and its input end is connected to the output end of the motor 3. The motor 3 is installed on the support base 101. The motor 3 drives the reduction mechanism to operate. Under the drive of the reduction mechanism, the rotating shaft 201 rotates, thereby causing the rudder 203 to deflect, thus realizing the adjustment of the deflection angle of the rudder 203.

[0028] Since the above are merely preferred embodiments of this utility model and are not intended to limit this utility model, it is obvious that those skilled in the art can make various modifications and variations to this utility model without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this utility model and their equivalents, this utility model also intends to include these modifications and variations.

Claims

1. An integrated micro servo motor, characterized in that, include: The housing (100) is annular, and a support base (101) is provided in the housing (100). Multiple through slots (102) are provided on the periphery along the circumferential direction. The length direction of the through slots (102) is parallel to the axis of the housing (100). A connecting block (103) is provided at the center of the bottom of the support base (101). The rudder control assembly (200) includes a plurality of rudder control modules disposed within the housing (100) and spaced apart along its circumference. Each rudder control module includes a rotating shaft (201) mounted on the side wall of the connecting block (103) and rotating about its own axis. At the end of the rotating shaft (201) away from the connecting block (103), there are two mounting blocks (202) with a distance between them. A rudder wing (203) is rotatably connected between the mounting blocks (202). The rudder wing (203) has a rotation angle of 90 degrees and is located in the through groove (102). The rotating shaft (201) has a circularly shaped limiting groove (204) at one end away from the connecting block (103). One end of the limiting groove (204) extends through to the end of the mounting block (202). A pad (205) is provided at the bottom of the limiting groove (204). A groove (206) is provided at one end of the pad (205) near the mounting block (202). A screw (207) is inserted in the groove (206). The threaded portion of the screw (207) passes through the pad (205) and the rotating shaft (201) in sequence and is connected to the connecting ring (105). The end of the connecting block (103) has a mounting hole (106) extending through to the end of the support base (101). The connecting ring (105) is installed in the mounting hole (106). One end of the rudder wing (203) is provided with a connecting plate (208), the connecting plate (208) is sleeved on the convex shaft (209), the convex shaft (209) is installed between two mounting blocks (202), a stop block (210) is provided between the mounting blocks (202), and a hook block (211) is provided at the end of the connecting plate (208). When the length direction of the connecting plate (208) is parallel to the axis of the rotating shaft (201), the side of the hook block (211) abuts against the end face of the stop block (210). The limiting groove (204) is provided with a push rod (212), and the end of the push rod (212) near the center of the connecting block (103) is provided with a slot (213). The slot (213) is provided with a spring (214), at least a part of which is located outside the slot (213). The spring (214) abuts against the bottom of the slot (213) and the screw (207) respectively, and is always in a compressed state. (212) The other end is arc-shaped, and the side of the connecting plate (208) is provided with a slope. When the length direction of the connecting plate (208) is parallel to the axis of the rotating shaft (201), the arc-shaped part of the top rod (212) contacts the slope of the connecting plate (208). When the length direction of the connecting plate (208) is perpendicular to the axis of the rotating shaft (201), the end face of the top rod (212) abuts against the side of the connecting plate (208).

2. The integrated micro servo motor according to claim 1, characterized in that, The connecting block (103) has a plurality of through holes (104) arranged at intervals along the circumferential direction on its side wall. A bearing (107) is provided in the through hole (104), and the other end of the rotating shaft (201) is fitted to the inner wall of the bearing (107).

3. The integrated micro servo motor according to claim 1, characterized in that, The connecting ring (105) has multiple threaded holes (108) along its circumferential direction on its sidewall. A coaxial convex ring (109) is provided on the outside of the threaded hole (108). The inner wall of the convex ring (109) is threaded. The screw (207) is connected to the inner wall of the convex ring (109). The rotating shaft (201) has a through hole (215) at one end near the center of the connecting block (103) that extends through to the limiting groove (204). The diameter of the through hole (215) is smaller than the outer diameter of the pad (205). The convex ring (109) is located in the through hole (215), and the pad (205) abuts against the end face of the convex ring (109).

4. The integrated micro servo motor according to claim 1, characterized in that, The outer side of the rotating shaft (201) is connected to the rotating end of the deceleration mechanism and is coaxially arranged with the rotating end of the deceleration mechanism. The deceleration mechanism is installed on the support base (101) and its input end is connected to the output end of the motor (3). The motor (3) is installed on the support base (101).

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