An electric servo motor

Abstract

This invention provides an electric servo motor, comprising: a servo mechanism 100, a servo blade rotation mechanism 200, a servo blade retraction and deployment mechanism 300, and a structural housing 400. The structural housing 400 includes a servo motor housing 5 and an angular position sensor bracket 6; the angular position sensor bracket 6 is mounted on the top of the servo motor housing 5, and a high-speed brushed DC motor 3 of the transmission system is mounted on the bottom of the servo motor housing 5. The servo mechanism 100, the servo blade rotation mechanism 200, and the servo blade retraction and deployment mechanism 300 are installed inside the servo motor housing 5. This invention's technical solution, employing an integrated electric servo mechanism connected to a worm gear, can solve space limitations such as the servo blade output shaft and servo motor installation space constraints, as well as the small diameter of the servo motor, thereby improving the power-to-weight ratio of the servo motor structure, increasing the utilization rate of the internal space, and improving the power-to-weight ratio.

Description

Technical Field

[0001] This invention belongs to the field of servo motor structure technology, and specifically relates to an electric servo motor. Background Technology

[0002] A servo motor is an actuator that uses a position or angle servo drive to manipulate the control surfaces of an aircraft or rotate those surfaces. It is suitable for control systems that require continuous angle changes and the ability to maintain them. Pitch, yaw, and roll movements, which change the attitude of an aircraft, are all accomplished by the coordinated operation of servos. As aircraft become increasingly miniaturized, there is a growing demand for controlling four control surfaces within a very small space. Electric servos, with their lightweight, stable performance, and ease of maintenance, are gradually becoming a new direction in servo motor development.

[0003] The actuator of an electric servo motor typically consists of a motor, a transmission mechanism, and a servo mechanism. The transmission mechanism, as the core of the actuator, is usually a reduction gear to obtain a large torque output. For a servo motor, the mechanical zero position of the servo motor needs to coincide with its electrical zero position (sensor zero position). Current solutions involve fixing the servo motor's rudder blades to the front end of the servo motor's output shaft and coaxially fixing the angular position sensor to the rear end of the servo motor's output shaft, thus controlling the servo motor's output shaft at the sensor's zero position. Traditional electric servo mechanisms typically assemble the servo motor, transmission mechanism, output mechanism, and sensor into a separate servo motor, then arrange them circumferentially and install them into a servo mechanism housing to achieve assembly and fixation of the entire mechanism. This approach suffers from drawbacks such as numerous transmission links, large clearances, low rigidity, low efficiency, a high probability of jamming, and low utilization of internal space. Furthermore, each component has its own separate housing structure, resulting in a large size and mass, and a low power-to-weight ratio.

[0004] Currently, the new servo housing has a small diameter, requiring four servo blades that can be retracted into the housing. Furthermore, the confined space necessitates that each servo blade have an independent rotary transmission mechanism and a separate angular position sensor for each blade's output shaft, making it unsuitable for installation in traditional servo structures. Summary of the Invention

[0005] This invention provides an electric servo motor that can solve space limitations such as the space constraints of the servo output shaft and servo motor installation, as well as the small diameter of the servo motor, thereby improving the power-to-weight ratio of the servo motor structure, increasing the utilization rate of the cabin space, and improving the power-to-weight ratio.

[0006] In this embodiment of the invention, an electric servo motor is provided, comprising: a servo mechanism 100, a servo blade rotation mechanism 200, a servo blade retraction and extension mechanism 300, and a structural housing 400.

[0007] The servo mechanism 100 includes: a control circuit board 4 and an angular position sensor 21;

[0008] The servo rotation mechanism 200 includes: a planetary reducer 13, a transmission worm gear 15, a transmission turbine 16, a servo output shaft 17, a copper-based self-lubricating bearing 18 supporting the outer side of the output shaft, and a deep groove ball bearing 20 supporting the inner side of the output shaft; the transmission turbine 16 and the servo output shaft 17 are coaxially connected, the output shaft of the planetary reducer 13 and the transmission worm gear 15 are coaxially connected, the two ends of the transmission worm gear 15 are supported by the deep groove ball bearing 20 supporting the inner side of the output shaft, and the front end of the transmission worm gear 15 is coaxially and fixedly connected to the output shaft of the planetary reducer 13.

[0009] The servo plate deployment and retraction mechanism 300 includes: a servo output shaft 17, a servo plate 10, a servo plate rotation shaft 11, a servo plate deployment spring 8, a servo plate deployment ball 9, a servo plate concealment groove 5.1, and a servo plate deployment spring storage groove 17.1. The servo output shaft 17 fixes the servo plate 10 and is connected to it via the servo plate rotation shaft 11. The servo plate deployment ball 9 is located in the central circular hole of the servo output shaft 17 and is used to push out the servo plate 10. The servo plate 10 is rotatably connected to the servo output shaft 17 via the servo plate rotation shaft 11.

[0010] The structural housing 400 includes a servo housing 5 and an angular position sensor bracket 6; the angular position sensor bracket 6 is installed on the top of the servo housing 5, and the high-speed brushed DC motor 3 of the transmission system is installed on the bottom of the servo housing 5. The servo mechanism 100, the servo blade rotation mechanism 200, and the servo blade retraction mechanism 300 are installed inside the servo housing 5.

[0011] Furthermore, in the rudder rotation mechanism 200, the high-speed brushed DC motor 3 drives the planetary reducer 13, the output shaft of the planetary reducer 13 drives the coaxially mounted transmission worm gear 15 to rotate, the transmission worm gear 15 drives the transmission turbine 16 to rotate, and drives the rudder output shaft 17 coaxially mounted with the transmission turbine 16 to rotate. The angular position sensor 21 receives the data and transmits it to the circuit board 4.

[0012] Furthermore, the rotating shaft of the angular position sensor 21 is coaxial with the servo output shaft 17, and the connection method adopts the form of milling flattening of a round shaft. The housing of the angular position sensor 21 is fixed on the angular position sensor bracket 6.

[0013] Furthermore, there are four angular position sensors 21. After the four angular position sensors 21 and the angular position sensor bracket 6 are assembled into a whole, they are installed in the middle groove on the top side of the servo housing 5.

[0014] Furthermore, the transmission worm gear 16 and the servo output shaft 17 are coaxially connected, and the output shaft of the planetary reducer 13 and the transmission worm gear 15 are coaxially connected, including:

[0015] The transmission turbine 16 and the servo output shaft 17 are connected by a square shaft, while the output shaft of the planetary reducer 13 and the transmission worm 15 are connected by a flattened round shaft.

[0016] Furthermore, the servo blade concealment groove 5.1 is integrally formed into the servo housing 5.

[0017] Furthermore, both the servo housing 5 and the servo blade 10 are made of high-strength aluminum alloy 7075.

[0018] Furthermore, the outer side of the servo output shaft 17 is provided with a limiting step in the inner hole of the copper-based self-lubricating bearing to restrict the axial movement of the servo output shaft. The limiting step has a fan-shaped groove for limiting the rotation of the servo blade. The outer circular surface of the copper-based self-lubricating bearing has arc-shaped fixing holes for limiting screws on both sides. The lower side of the copper-based self-lubricating bearing has a slot for the servo blade to be retracted and hidden.

[0019] Furthermore, the outer diameter of the servo housing 5 is the same as the outer diameter of the aircraft, forming part of the aircraft, and is fixedly connected to other parts of the aircraft in the axial direction via flange connections.

[0020] The beneficial effects of this invention are as follows:

[0021] As can be seen from the above scheme, the embodiments of the present invention provide an electric servo motor, including: a servo mechanism 100, a servo blade rotation mechanism 200, a servo blade retraction and deployment mechanism 300, and a structural housing 400. The structural housing 400 includes a servo motor housing 5 and an angular position sensor bracket 6; the angular position sensor bracket 6 is installed on the top of the servo motor housing 5, and a high-speed brushed DC motor 3 of the transmission system is installed on the bottom of the servo motor housing 5. The servo mechanism 100, the servo blade rotation mechanism 200, and the servo blade retraction and deployment mechanism 300 are installed inside the servo motor housing 5. The technical solution of the present invention, by adopting an integrated electric servo mechanism and a worm gear connection method, can solve the space limitations of the servo blade output shaft and servo motor installation, as well as the space limitations of the small diameter of the servo motor, thereby improving the power-to-weight ratio of the servo motor structure, increasing the utilization rate of the internal space, and improving the power-to-weight ratio. Attached Figure Description

[0022] Figure 1 This is a schematic diagram illustrating the structure of an electric servo motor according to an embodiment of the present invention;

[0023] Figure 2 This is a schematic diagram showing the overall structure of an electric servo motor according to an embodiment of the present invention;

[0024] Figure 3 A cross-sectional schematic diagram of a rudder retraction and deployment mechanism for an electric servo motor according to an embodiment of the present invention;

[0025] Figure 4A schematic cross-sectional view showing the output shaft axis of an electric servo motor according to an embodiment of the present invention is perpendicular to the axis of the servo motor.

[0026] Figure 5 A schematic diagram illustrating the transmission process from the motor output shaft to the rudder output shaft of an electric servo motor according to an embodiment of the present invention;

[0027] In the diagram, 100 is the servo mechanism, 200 is the rudder rotation mechanism, 300 is the rudder deployment and retraction mechanism, 400 is the structural housing, 1 is the control board fixing screw, 2 is the control board support copper column, 3 is the high-speed brushed DC motor, 4 is the control board, 5 is the servo housing, 5.1 is the servo rudder rudder hidden slot, 6 is the angular position sensor bracket, 7 is the bearing lock nut, 8 is the rudder rudder deployment spring, 9 is the rudder rudder deployment steel ball, 10 is the servo rudder rudder, 11 is the servo rudder rudder rotation shaft, 12 is the rudder rudder rotation limit screw, 13 is the planetary reducer, 14 is the angular position sensor clamping plate, 15 is the transmission worm gear, 16 is the transmission turbine, 17 is the servo output shaft, 17.1 is the rudder rudder deployment spring storage slot, 18 is the output shaft outer support copper-based self-lubricating bearing, 19 is the copper-based self-lubricating bearing fastening screw, 20 is the output shaft inner support deep groove ball bearing, and 21 is the angular position sensor. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of the embodiments of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this invention.

[0029] In this embodiment of the invention, by sharing the servo housing with the servo bay housing, the space allocated to the aircraft is fully utilized, resulting in a compact small servo design. A high-speed brushed DC motor, servo mechanism, transmission mechanism, and structural housing are integrated into a single unit. The drive motor is fixed to the lower surface of the servo housing and arranged along the axial direction of the servo housing. The output end of the drive motor is screwed into the servo housing, and a worm gear assembly is arranged inside the servo housing.

[0030] like Figures 1 to 5 As shown, Figure 1 This is a schematic diagram illustrating the structure of an electric servo motor according to an embodiment of the present invention; Figure 2 This is a schematic diagram showing the overall structure of an electric servo motor according to an embodiment of the present invention; Figure 3 A cross-sectional schematic diagram of a rudder retraction and deployment mechanism for an electric servo motor according to an embodiment of the present invention; Figure 4A schematic cross-sectional view showing the output shaft axis of an electric servo motor according to an embodiment of the present invention is perpendicular to the axis of the servo motor. Figure 5 This is a schematic diagram illustrating the transmission process from the motor output shaft to the rudder output shaft of an electric servo motor according to an embodiment of the present invention.

[0031] The figure shows an electric servo motor, including: a servo mechanism 100, a servo blade rotation mechanism 200, a servo blade retraction and extension mechanism 300, and a structural housing 400.

[0032] The servo mechanism 100 includes: a control circuit board 4 and an angular position sensor 21.

[0033] In this embodiment of the invention, the position sensor 21 is a Hall effect sensor, which is compact and highly accurate. It is fixed to the servo housing 5 by the angular position sensor bracket 6. The angular position sensor 21 and the servo housing 5 are limited by the angular position sensor clamping plate 14. The rotating shaft of the angular position sensor 21 is coaxial with the servo output shaft 17 (the connection method is a round shaft milling flattening), which improves the measurement accuracy and anti-interference capability of the angular position sensor 21 and realizes the application of digital position sensors in servos. When the servo output shaft 17 rotates, the angular position sensor 21 collects the rotation data of the servo output shaft 17 and feeds it back to the control circuit board 4. The control circuit board 4 controls the movement state of the high-speed brushed DC motor 3 according to the collected data, thereby adjusting the speed of the worm gear 15 and controlling the counterclockwise or clockwise rotation speed of the turbine 16.

[0034] The servo rotation mechanism 200 includes: a planetary reducer 13, a transmission worm gear 15, a transmission turbine 16, a servo output shaft 17, a copper-based self-lubricating bearing 18 supporting the outer side of the output shaft, and a deep groove ball bearing 20 supporting the inner side of the output shaft; the transmission turbine 16 and the servo output shaft 17 are coaxially connected, the output shaft of the planetary reducer 13 and the transmission worm gear 15 are coaxially connected, the two ends of the transmission worm gear 15 are supported by the deep groove ball bearing 20 supporting the inner side of the output shaft, and the front end of the transmission worm gear 15 is coaxially and fixedly connected to the output shaft of the planetary reducer 13.

[0035] In this embodiment of the invention, a high-speed brushed DC motor 3 drives a planetary reducer 13. The output shaft of the planetary reducer 13 drives a coaxially mounted transmission worm gear 15 to rotate. The transmission worm gear 15 drives a transmission turbine 16 to rotate, which in turn drives a servo output shaft 17 coaxially mounted with the transmission turbine 16 to rotate. An angular position sensor 21 receives data and transmits it to a circuit board 4. Specifically, the rotating shaft of the angular position sensor 21 is coaxial with the servo output shaft 17, and the connection is made by milling a round shaft. The housing of the angular position sensor 21 is fixed to an angular position sensor bracket 6. The transmission turbine 16 and the servo output shaft 17 are connected by a square shaft, and the output shaft of the planetary reducer 13 and the transmission worm gear 15 are milled from a round shaft.

[0036] In this embodiment of the invention, there are four angular position sensors 21. After the four angular position sensors 21 and the angular position sensor bracket 6 are assembled into a whole, they are installed in the middle groove on the top side of the servo housing 5.

[0037] The servo plate deployment and retraction mechanism 300 includes: a servo output shaft 17, a servo plate 10, a servo plate rotation shaft 11, a servo plate deployment spring 8, a servo plate deployment ball 9, a servo plate concealment groove 5.1, and a servo plate deployment spring storage groove 17.1. The servo output shaft 17 fixes the servo plate 10 and is connected to it via the servo plate rotation shaft 11. The servo plate deployment ball 9 is located in the central circular hole of the servo output shaft 17 and is used to push out the servo plate 10. The servo plate 10 is rotatably connected to the servo output shaft 17 via the servo plate rotation shaft 11.

[0038] In this embodiment of the invention, the servo steerer blade hiding groove 5.1 is integrally formed into the servo steerer housing 5, resulting in better fit and higher processing efficiency. The servo steerer output shaft 17 is used to fix the servo steerer blade 10, and the connection strength is ensured by the servo steerer blade rotation shaft 11. The servo steerer blade unfolding ball 9 is in the middle circular hole of the servo steerer output shaft 17 and can roll axially within the servo steerer blade unfolding spring receiving groove 17.1 in the middle of the servo steerer output shaft 17. The servo steerer blade unfolding ball 9 is used to push out the servo steerer blade 10. The servo steerer blade 10 has a step on one side of the servo steerer blade unfolding ball 9 to improve the fixing effect of the servo steerer blade 10 after unfolding. The servo steerer blade 10 is rotatably connected to the servo steerer output shaft 17 by the servo steerer blade rotation shaft 11, and the connection strength is ensured by the servo steerer blade rotation shaft 11. The servo steerer housing 5 and the servo steerer blade 10 are both made of high-strength aluminum alloy 7075. The use of lightweight materials ensures the smooth unfolding of the servo steerer blade 10.

[0039] When the servo housing 5 is launched along with the entire aircraft, the servo blade 10 loses its external constraint. At this time, the servo blade deployment spring 8 located in the servo blade deployment spring storage groove 17.1 inside the servo output shaft 17 pushes out the servo blade deployment steel ball 9. The servo blade deployment steel ball 9 pushes the servo blade 10, so that the servo blade 10 can be deployed. After the servo blade deployment steel ball 9 is pushed out to the limit position, it presses against the step of the servo blade 10, thereby ensuring the deployment effect of the servo blade 10.

[0040] The structural housing 400 includes a servo housing 5 and an angular position sensor bracket 6; the angular position sensor bracket 6 is installed on the top of the servo housing 5, and the high-speed brushed DC motor 3 of the transmission system is installed on the bottom of the servo housing 5. The servo mechanism 100, the servo blade rotation mechanism 200, and the servo blade retraction mechanism 300 are installed inside the servo housing 5.

[0041] In this embodiment of the invention, the outer diameter of the structural shell is the same as the diameter of the aircraft and is part of the aircraft. It is connected to other parts of the aircraft by flanges in the axial direction. The main component of the structural shell is the servo housing 5. The top of the servo housing 5 is equipped with an angular position sensor bracket 6, and the bottom of the servo housing 5 is equipped with a high-speed brushed DC motor 3 of the transmission system. Other parts of the servo, such as the servo mechanism, the transmission mechanism, and the servo blade retraction mechanism, are all installed inside the servo housing 5.

[0042] The working process of this embodiment includes: the control circuit board 4 controls the high-speed brushed DC motor 3 to start moving, and drives the coaxially mounted transmission worm 15 to rotate synchronously through the output shaft of the planetary reducer 13. The transmission worm 15 drives the transmission turbine 16 meshing with it to rotate. The transmission turbine 16 and the servo output shaft 17 are coaxially fixedly connected (the connection method adopts the square shaft connection form). The two ends of the transmission worm 15 are supported by deep groove ball bearings 20, and the front end is coaxially fixedly connected to the output shaft of the planetary reducer 13 (the connection method adopts the round shaft milling flat form). The servo output shaft 17 drives the servo blade 10 to rotate. When the servo output shaft 17 rotates, the angular position sensor 21 collects the rotation data of the servo output shaft 17 and feeds it back to the control circuit board 4. The control circuit board 4 controls the movement state of the high-speed brushed DC motor 3 according to the collected data, thereby adjusting the speed of the transmission worm 15, controlling the counterclockwise or clockwise rotation speed of the transmission turbine 16, and finally controlling the rotation of the servo blade 10.

[0043] When the servo housing 5 is launched along with the entire aircraft, the servo blade 10 loses its external constraint. At this time, the servo blade deployment spring 8 located in the servo blade deployment spring storage groove 17.1 inside the servo output shaft 17 pushes out the servo blade deployment steel ball 9. The servo blade deployment steel ball 9 pushes the servo blade 10 to rotate along the servo blade rotation axis 11, so that the servo blade 10 can be deployed. After the servo blade deployment steel ball 9 reaches the limit position, it hits the step of the servo blade 10, thus ensuring that the servo blade 10 is firmly deployed.

[0044] Furthermore, the outer side of the servo output shaft 17 is provided with a limiting step in the inner hole of the copper-based self-lubricating bearing to restrict the axial movement of the servo output shaft. The limiting step has a fan-shaped groove for limiting the rotation of the servo blade. The outer circular surface of the copper-based self-lubricating bearing has arc-shaped fixing holes for limiting screws on both sides. The lower side of the copper-based self-lubricating bearing has a slot for the servo blade to be retracted and hidden.

[0045] Furthermore, the outer diameter of the servo housing 5 is the same as the outer diameter of the aircraft, forming part of the aircraft, and is fixedly connected to other parts of the aircraft in the axial direction via flange connections.

[0046] To accommodate the limited installation space of servo motors, this invention integrates the servo motor housing and the servo motor bay housing into a single unit. The servo motor shaft is driven by a motor shaft, which in turn drives a transmission worm and a transmission turbine to rotate the servo blade shaft. To address the issue of the copper-based self-lubricating bearing on the outer side of the servo motor output shaft rotating with it, set screws are used on both sides of the copper sleeve of the output shaft to limit axial movement and circumferential rotation of the servo blade output shaft, thus restricting the rotation angle range of the servo motor output shaft.

[0047] An angular position sensor bracket is fixed between the output shaft end of the servo and the servo housing to solve the problem of fixing the angular position sensor at the output shaft end of the servo, preventing it from rotating with the servo output shaft. The integrated electric servo mechanism adopts a high-speed brushed DC motor, servo mechanism, transmission mechanism, servo retraction and deployment mechanism, and structural housing integrated into a single design. By integrating the high-speed brushed DC motor, transmission worm gear, transmission turbine, angular position sensor, and servo mechanism structure into a single unit, and following the design concept of hollow structure and integrated internal worm gear, as well as the design philosophy of improving the power-to-weight ratio of the servo mechanism, negative mass is reduced, and the space utilization rate of the servo housing is improved.

[0048] The present invention provides an electric servo motor that uses an integrated electric servo mechanism connected to a worm gear, which can solve the space limitations of the servo output shaft and servo motor installation; at the same time, it solves the space limitations such as the small diameter of the servo motor, and has the advantages of small size and light weight.

[0049] The above are preferred embodiments of the present invention. It should be noted that, for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. An electric servo motor, characterized in that, The electric servo motor includes: a servo mechanism (100), a servo blade rotation mechanism (200), a servo blade retraction and extension mechanism (300), and a structural housing (400). The servo mechanism (100) includes: a control circuit board (4) and an angular position sensor (21); The rudder rotation mechanism (200) includes: a planetary reducer (13), a transmission worm (15), a transmission worm wheel (16), a rudder output shaft (17), a copper-based self-lubricating bearing (18) supporting the outer side of the output shaft, and a deep groove ball bearing (20) supporting the inner side of the output shaft; the transmission worm wheel (16) and the rudder output shaft (17) are coaxially connected, the output shaft of the planetary reducer (13) and the transmission worm (15) are coaxially connected, the two ends of the transmission worm (15) are supported by the deep groove ball bearing (20) supporting the inner side of the output shaft, and the front end of the transmission worm (15) is coaxially fixedly connected to the output shaft of the planetary reducer (13); The servo plate deployment and retraction mechanism (300) includes a servo output shaft (17), a servo plate (10), a servo plate rotation shaft (11), a servo plate deployment spring (8), a servo plate deployment ball (9), a servo plate hiding groove (5.1), and a servo plate deployment spring storage groove (17.1). The servo output shaft (17) fixes the servo plate (10) and is connected through the servo plate rotation shaft (11). The servo plate deployment ball (9) is in the middle circular hole of the servo output shaft (17) and is used to push out the servo plate (10). The servo plate (10) is rotatably connected to the servo output shaft (17) through the servo plate rotation shaft (11). The structural housing (400) includes a servo housing (5) and an angular position sensor bracket (6); the angular position sensor bracket (6) is installed on the top of the servo housing (5), and a high-speed brushed DC motor (3) of the transmission system is installed on the bottom of the servo housing (5); the servo mechanism (100), the servo blade rotation mechanism (200), and the servo blade retraction mechanism (300) are installed inside the servo housing (5); In the rudder rotation mechanism (200), the high-speed brushed DC motor (3) drives the planetary reducer (13), the output shaft of the planetary reducer (13) drives the coaxially mounted transmission worm (15) to rotate, the transmission worm (15) drives the transmission worm wheel (16) to rotate, and drives the rudder output shaft (17) coaxially mounted with the transmission worm wheel (16) to rotate. The angular position sensor (21) receives data and transmits it to the circuit board (4).

2. The electric servo motor according to claim 1, characterized in that, The rotating shaft of the angular position sensor (21) is coaxial with the output shaft (17) of the servo motor, and the connection method is a flattened round shaft. The outer shell of the angular position sensor (21) is fixed on the angular position sensor bracket (6).

3. An electric servo motor according to claim 1, characterized in that, The number of the angular position sensors (21) is four. After the four angular position sensors (21) and the angular position sensor bracket (6) are assembled into a whole, they are installed in the middle groove on the top side of the servo housing (5).

4. An electric servo motor according to claim 1, characterized in that, The transmission worm gear (16) and the servo output shaft (17) are coaxially connected, and the output shaft of the planetary reducer (13) and the transmission worm (15) are coaxially connected, including: The transmission worm gear (16) and the servo motor output shaft (17) are connected by a square shaft, and the output shaft of the planetary reducer (13) and the transmission worm (15) are connected by a flattened round shaft.

5. An electric servo motor according to claim 1, characterized in that, The servo blade hiding groove (5.1) is integrally formed on the servo housing (5).

6. An electric servo motor according to claim 1, characterized in that, The servo housing (5) and servo blade (10) are both made of high-strength aluminum alloy 7075.

7. An electric servo motor according to claim 1, characterized in that, The inner hole of the copper-based self-lubricating bearing supporting the outer side of the output shaft is provided with a limiting step to restrict the axial movement of the servo motor output. The limiting step has a fan-shaped groove for limiting the rotation of the servo motor blade. The outer circular surface of the copper-based self-lubricating bearing supporting the outer side of the output shaft is provided with arc-shaped fixing holes for limiting screws. The lower side of the copper-based self-lubricating bearing supporting the outer side of the output shaft is provided with a slot for the servo motor blade to be retracted and hidden.

8. An electric servo motor according to claim 1, characterized in that, The outer diameter of the servo housing (5) is the same as that of the aircraft, forming part of the aircraft. It is fixedly connected to other parts of the aircraft in the axial direction by flange connection.

Images