A compact aerospace drive mechanism with combined transmission methods and adjustable angle.

Abstract

This invention relates to a compact aerospace drive mechanism with a combined transmission method and adjustable angle. It includes a housing, a two-stage planetary gear reducer, a primary gear pair, a primary worm gear pair, a primary spline pair, and a drive motor. The drive motor sequentially drives the primary gear pair, the primary worm gear pair, and the primary spline pair through the first and second planetary gear reducers, ultimately driving the output gear. The advantages of this invention are: through the combined transmission method of planetary gear reducers, spur gear reduction, worm gear pair reduction, and spline transmission, the structure is compact and reasonable, requiring little space, and operating reliably. It can achieve forward and reverse direction adjustment of the aerospace drive mechanism within a small space. The self-locking characteristic of the primary worm gear pair enables high load-bearing capacity and locking of the final moving part's position.

Description

Technical Field

[0001] This invention relates to the field of aircraft drive mechanisms, and in particular, to a compact aircraft drive mechanism with a combined transmission method and adjustable angle. Background Technology

[0002] In the aviation field, aircraft drive mechanisms are designed to drive the movement of aircraft terminal moving parts to adapt to the aircraft's flight objectives, thereby adjusting the position of these parts. The power output components of an aircraft drive mechanism need to stop and lock at their extreme clockwise and counterclockwise rotation positions, as well as any intermediate positions. Due to space and weight constraints, the size and weight of aircraft drive mechanisms have been gradually reduced. Simultaneously, due to the requirement for low power and compact structure, relatively high transmission efficiency is required. Different aircraft moving parts exhibit varying consistency, resulting in differences in the clockwise and counterclockwise extreme positions of the installed aircraft drive mechanism. Therefore, the extreme position angles of the power output components need to be adjustable. Due to the small space required and the high load-bearing capacity, such aircraft drive mechanisms currently do not exist. Summary of the Invention

[0003] The purpose of this invention is to address the lack of such aviation drive mechanisms in the prior art, and to provide a compact aviation drive mechanism with a combined transmission method and adjustable angle.

[0004] To achieve this objective, the technical solution of the present invention is as follows: a compact aerospace drive mechanism with a combined transmission method and adjustable angle, characterized in that the aerospace drive mechanism includes,

[0005] The mechanism housing has a partition, a first protective cover and a second protective cover arranged inside it. The partition, the first protective cover and the second protective cover divide the interior of the mechanism housing into a left cavity and a right cavity. Threaded holes can be provided on the outer surface of the housing for installing and fixing the aircraft drive mechanism.

[0006] A two-stage planetary gear reducer is arranged outside the housing and placed at the output shaft end of the drive motor; the two-stage planetary gear reducer has a first row of planetary reducers, a second row of planetary reducers, and an internal gear ring; the first row of planetary reducers and the second row of planetary reducers are arranged inside the internal gear ring;

[0007] A primary gear pair is arranged in the right cavity of the housing and includes a first gear and a second gear that mesh with each other. The first gear is connected to the second row of planetary reducers.

[0008] A first-stage worm gear pair is arranged in the right cavity of the housing, including a worm wheel and a worm, the worm being connected to a second gear;

[0009] A primary spline pair is arranged in the right cavity of the housing, including a first spline shaft, which is connected to a worm gear and an output gear.

[0010] The drive motor has its main body located outside the housing of the mechanism. The drive motor is fixed to the housing of the mechanism by two screws passing through the mounting lug holes of the internal gear ring. The drive motor has a motor output shaft with a flat structure. The motor output shaft extends horizontally and enters the two-stage planetary gear reducer horizontally.

[0011] The drive motor drives the first-stage gear pair, the first-stage worm gear pair, and the first-stage spline pair to rotate in sequence through the first planetary gear reducer and the second planetary gear reducer, ultimately driving the output gear to rotate.

[0012] Furthermore, the first row of planetary reducers includes a first sun gear, a first set screw, a first open retaining ring, a retaining ring, first planet gears, and a first planetary carrier. The first sun gear is fixed to the output shaft of the drive motor by the first set screw and rotates synchronously with the output shaft of the drive motor. The first sun gear and the output shaft of the drive motor share a common axis of rotation. The first sun gear meshes with the three first planet gears simultaneously. The first planetary carrier is triangular in shape, with a raised shaft corresponding to each corner in the axial direction, and a groove is provided on each raised shaft. The three first planet gears are mounted on the three raised shafts of the first planetary carrier, and the retaining ring and the first open retaining ring are sequentially mounted on the end face of each first planet gear away from the first carrier. The first open retaining ring is engaged in the groove on the raised shaft of the first planetary carrier. Each first planet gear and the corresponding raised shaft of the first planetary carrier share a common axis of rotation. The three first planet gears of the first row of planetary reducers simultaneously mesh with the internal gear ring.

[0013] Furthermore, the retaining ring and the first open retaining ring serve to prevent the first planetary gear from falling off the first planetary support.

[0014] Furthermore, the second-row planetary reducer includes a second sun gear, second planet gears, a second planetary carrier, and a first bearing. The second sun gear is mounted on the first planetary carrier, and rotates synchronously with the first planetary carrier, sharing a common axis of rotation. The second planetary carrier is triangular in shape, with a protruding shaft at each corner corresponding to an axial direction. A shaft extends axially from the other end face of the second planetary carrier, and a groove is provided on the outer surface of the shaft end. The three second planet gears are mounted on the three protruding shafts of the second planetary carrier. The three second planet gears simultaneously mesh with the second sun gear and the internal gear ring. Each second planet gear shares a common axis of rotation with its corresponding protruding shaft on the second planetary carrier. The three second planet gears of the second-row planetary reducer simultaneously mesh with the internal gear ring. The first bearing is mounted on the extended shaft of the second planetary carrier.

[0015] Furthermore, the internal gear ring is provided with four mounting ears, and each mounting ear is provided with a mounting through hole; the first sun gear, the first planetary support, the second sun gear, the second planetary support, and the first bearing have a common axis.

[0016] Furthermore, the primary gear pair has a first flat key, a first gear, a second gear, a second flat key, and a second open retaining ring; the first gear meshes with the second gear, the first gear is mounted on the extended shaft of the second planetary carrier via the first flat key, and the first gear and the second planetary carrier have a common axis; the second open retaining ring is engaged in a groove on the extended shaft of the second planetary carrier;

[0017] Furthermore, the second open retaining ring serves to prevent the first gear from falling off the second planetary carrier; the second gear transmits torque via the second flat key.

[0018] Furthermore, the first-stage worm gear pair includes a first worm, a first worm wheel, a second bearing, and a third flat key; the first worm meshes with the first worm wheel, and the second gear is connected and fixed to the first worm via the second flat key, and the first worm and the second gear have a common axis; the first worm is supported and fixed to the mechanism housing by the second bearing, and the first worm and the second bearing have a common axis; the first worm wheel transmits torque through the third flat key.

[0019] Furthermore, the primary spline pair includes a third bearing, a first spline shaft, a first output gear, and a screw combination fastener. The first spline shaft is supported and mounted in the right cavity enclosed by the housing and the partition plate by two of the third bearings; the effective portion of the outer spline of the first spline shaft extends horizontally to the right, protruding from the housing; the effective portion of the outer spline of the first spline shaft meshes with the inner spline of the first output gear; the first worm gear is connected and fixed to the first spline shaft by the third flat key, and the first spline shaft, the first worm gear, and the first output gear share a common axis.

[0020] Furthermore, the first spline shaft has an internal threaded hole on one side of the external spline; the first output gear has an internal spline and is fixed to the first spline shaft by the screw combination fastener.

[0021] As a preferred embodiment of an aircraft drive mechanism, it also includes an angular displacement sensor disposed inside the left cavity of the housing. The angular displacement sensor has a sensor output shaft that extends horizontally. The sensor output shaft passes through the partition and enters the right cavity of the housing, where it is connected and fixed to the first splined shaft. The sensor output shaft rotates synchronously with the first splined shaft, and the sensor output shaft and the first splined shaft share a common axis.

[0022] As a preferred embodiment of an aerospace drive mechanism, the sensor output shaft has a "I"-shaped protrusion, and the left end face of the first spline shaft has a "I"-shaped groove, with the sensor output shaft protrusion inserted into the groove on the left end face of the first spline shaft.

[0023] As a preferred embodiment of an aerospace drive mechanism, the first sun gear, the first planet gear, the second sun gear, the second planet gear, the internal gear ring, the first gear, and the second gear all adopt a small module.

[0024] As a preferred option for an aircraft drive mechanism, the drive motor is an adjustable speed brushless DC motor.

[0025] As a preferred embodiment of an aerospace drive mechanism, one end of the second gear has a protruding structure, the protruding end face of the second gear is close to the shoulder end face of the first worm shaft, one end face of the second bearing is close to the non-protruding end face of the second gear, and the other end face of the second bearing is axially positioned by the second protective cover.

[0026] As a preferred embodiment of an aerospace drive mechanism, the partition is provided with a bearing chamber for housing and supporting the third bearing; the partition is positioned by a locating pin; the partition has threaded holes for mounting wire clamps, and the lead wire of the angular displacement sensor is fixed by the wire clamps.

[0027] Compared with existing technologies, the beneficial effects of this invention are at least as follows: Through a combination of transmission methods such as planetary gear reducers, spur gear reducers, worm gear reducers, and spline drives, the structure is compact and reasonable, requiring little space and operating reliably, enabling forward and reverse adjustment of the aircraft drive mechanism within a small space. The self-locking characteristic of the first-stage worm gear pair achieves the locking of the terminal moving parts' position requirements under high load. The angular displacement sensor and corresponding drive circuit enable adjustable motion angles of the aircraft drive mechanism's output shaft, thereby achieving adjustable extreme position angles and ensuring reliable aircraft flight. Attached Figure Description

[0028] Figure 1 This is an exploded view of the axial structure of the planetary gear shaft and worm gear of the present invention.

[0029] Figure 2 This is an exploded view of the worm gear and output gear shaft structure of the present invention.

[0030] Figure 3 This is a schematic cross-sectional view of the planetary gear structure of the present invention.

[0031] Figure 4 This is a cross-sectional schematic diagram of the worm gear structure of the present invention. Detailed Implementation

[0032] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments. It should be noted that these descriptions are for the purpose of aiding understanding the invention and do not constitute a limitation thereof. Furthermore, the technical features involved in the various embodiments of the invention described below can be combined with each other as long as they do not conflict with each other.

[0033] Please see Figures 1 to 4 The figure shows a compact aerospace drive mechanism with a combined transmission method and adjustable angle.

[0034] The aircraft drive mechanism consists of a drive motor 1, a two-stage planetary gear reducer 2, a single-stage gear pair 3, a single-stage worm gear pair 4, a mechanism housing 5, a spline pair 6, an angular displacement sensor 7, and other components.

[0035] The aircraft drive mechanism housing 5 is provided with a partition 52, a first protective cover 51, and a second protective cover 55. The first protective cover 51 and the second protective cover 55 divide the interior of the mechanism housing 5 into a left cavity 57 and a right cavity 56. Threaded holes can be provided on the outer surface of the mechanism housing 5 for installing and fixing the aircraft drive mechanism.

[0036] The two-stage planetary gear reducer 2 is arranged outside the housing 5 and placed at the output shaft 13 end of the drive motor 1. The two-stage planetary gear reducer 2 has a first row of planetary reducers 21, a second row of planetary reducers 22, and an internal gear ring 200. The first row of planetary reducers 21 and the second row of planetary reducers 22 are arranged inside the internal gear ring 200. The first row of planetary reducers 21 has a first sun gear 211, a first set screw 212, a first open stop 213, a retaining ring 214, first planetary gears 215, and a first planetary carrier 216. The first sun gear 211 is fixed to the output shaft 13 of the drive motor 1 by the first set screw 212 and rotates synchronously with the output shaft 13 of the drive motor 1. The first sun gear 211 and the output shaft 13 of the drive motor 1 have a common axis. The first sun gear 211 meshes with three first planetary gears 215 at the same time. The first planetary carrier 216 is triangular in shape and has a triangular shape. Each corner has a protruding shaft 217 corresponding to the axial direction, and each protruding shaft has a groove 218. The three first planetary gears 215 are mounted on the three protruding shafts 217 of the first planetary support 216, and the retaining ring 214 and the first open retaining ring 213 are sequentially installed on the end face of each first planetary gear 215 away from the first support. The first open retaining ring 213 is engaged in the groove 218 on the protruding shaft 217 of the first planetary support 216. Each first planetary gear 215 and the corresponding protruding shaft 217 of the first planetary support 216 have a common axis of rotation. The three first planetary gears 215 of the first row of planetary reducers 21 mesh with the internal gear ring 200 simultaneously.

[0037] Preferably, the retaining ring 214 and the first open retaining ring 213 serve to prevent the first planetary gear 215 from falling off the first planetary support 216.

[0038] The second-row planetary reducer 22 includes a second sun gear 221, second planet gears 222, a second planetary carrier 223, and a first bearing 225. The second sun gear 221 is mounted on the first planetary carrier 216, and rotates synchronously with the first planetary carrier 216, sharing a common axis of rotation. The second planetary carrier 223 is triangular in shape, with a protruding shaft 227 at each corner corresponding to an axial direction. A shaft 226 extends axially from the other end face of the second planetary carrier 223, and a groove 224 is provided on the outer surface of the extended shaft 226. The three second planet gears 222 are mounted on the three protruding shafts 227 of the second planetary carrier 223. The three second planet gears 222 simultaneously mesh with the second sun gear 221 and the internal gear ring 200. Each second planet gear 222 shares a common axis of rotation with its corresponding protruding shaft 227 on the second planetary carrier 223. The three second planetary gears 222 of the second-row planetary reducer 22 simultaneously mesh with the internal gear ring 200. The first bearing 225 is mounted on the extended shaft 226 of the second planetary carrier 223.

[0039] Preferably, the internal gear ring 200 is provided with four mounting ears 201, and each mounting ear 201 is provided with a mounting through hole 202; the first sun gear 211, the first planetary support 216, the second sun gear 221, the second planetary support 223 and the first bearing 225 have a common axis.

[0040] The primary gear pair 3 includes a first flat key 31, a first gear 32, a second gear 34, a second flat key 35, and a second open retaining ring 33; the first gear 32 meshes with the second gear 34, the first gear 32 is mounted on the extension shaft 226 of the second planetary support 223 via the first flat key 31, and the first gear 32 and the second planetary support 223 have a common axis of rotation; the second open retaining ring 33 is engaged in a groove 224 on the extension shaft 226 of the second planetary support 223.

[0041] Furthermore, the second open retaining ring 33 serves to prevent the first gear 32 from falling off the second planetary support 223; the second gear 34 transmits torque through the second flat key 35.

[0042] The first-stage worm gear pair 4 includes a first worm 42, a first worm wheel 44, a second bearing 41, and a third flat key 43. The first worm 42 meshes with the first worm wheel 44, and the second gear 34 is connected and fixed to the first worm 42 via the second flat key 35, with the first worm 42 and the second gear 34 sharing a common axis. The first worm 42 is supported and fixed to the mechanism housing 5 via the second bearing 41, with the first worm 42 and the second bearing 41 sharing a common axis. The first worm wheel 44 transmits torque via the third flat key 43.

[0043] The primary spline assembly 6 includes a third bearing 61, a first spline shaft 63, a first output gear 66, and a screw fastener 68. The first spline shaft 63 is supported by two of the third bearings 61 and mounted within the right cavity 56 enclosed by the housing 5 and the partition 52. The effective portion of the outer spline 64 of the first spline shaft 63 extends horizontally to the right, protruding from the housing 5. The effective portion of the outer spline 64 of the first spline shaft 63 meshes with the inner spline 67 of the first output gear 66. The first worm gear 44 is connected and fixed to the first spline shaft 63 via a third flat key 43, and the first spline shaft 63, the first worm gear 44, and the first output gear 66 share a common axis.

[0044] Furthermore, the first spline shaft 63 has an internal threaded hole 65 on one side of the external spline 64; the first output gear 66 has an internal spline 67, and the first output gear 66 is fixed to the first spline shaft 63 by the screw combination fastener 68.

[0045] The drive motor 1 has its main body located outside the drive mechanism housing 5. The drive motor 1 is fixed to the housing 5 by two screws 14 passing through the mounting lug holes 202 of the internal gear ring 200. The drive motor 1 has a motor output shaft 13 with a flat structure. The drive motor 1 output shaft 13 extends horizontally and enters the two-stage planetary gear reducer 2 horizontally. The drive motor 1 can be an adjustable speed brushless DC motor.

[0046] The angular displacement sensor 7 is arranged inside the left cavity 57 of the housing 5. The angular displacement sensor 7 has a sensor output shaft 71, which extends horizontally. The output shaft 71 passes through the partition 52 and enters the right cavity 56 of the housing 5, and is connected and fixed to the first spline shaft 63. The output shaft 71 of the sensor 7 rotates synchronously with the first spline shaft 63, and the output shaft 71 of the sensor 7 and the first spline shaft 63 have a common axis.

[0047] Preferably, the output shaft 71 of the angular displacement sensor 7 has a "I"-shaped protrusion, and the left end face of the first spline shaft 63 has a "I"-shaped groove 62, and the protrusion of the output shaft 71 of the sensor 7 is inserted into the groove 62 on the left end face of the first spline shaft 63.

[0048] Preferably, the first sun gear 211, the first planet gear 215, the second sun gear 221, the second planet gear 222, the internal gear ring 200, the first gear 32 and the second gear 34 all adopt a small module.

[0049] Preferably, one end of the second gear 34 has a protruding structure, the protruding end face of the second gear 34 is close to the shoulder end face of the first worm 42, one end face of the second bearing 41 is close to the non-protruding end face of the second gear 34, and the other end face of the second bearing 41 is axially positioned by the second protective cover 55.

[0050] Preferably, the partition 52 is provided with a bearing chamber 53, which is used to place and support the third bearing 61; the partition 52 is positioned by a positioning pin 54; the partition 52 has a threaded hole for installing a wire clamp, and the lead wire of the angular displacement sensor 7 is fixed by the wire clamp 72.

[0051] Working process: The output shaft 13 of the drive motor 1 rotates, and the output shaft 13 of the drive motor 1 drives the first sun gear 211 to rotate through the first set screw 212. The first sun gear 211 drives the first planetary support 216 and the second sun gear 221 to rotate synchronously through the first planetary gear 215 and the internal gear ring 200. Similarly, the second sun gear 221 drives the second planetary support 223 and the first gear 32 to rotate synchronously through the second planetary gear 222 and the internal gear ring 200. The first gear 32 drives the second gear 34, the first worm 42, the first worm wheel 44, the first spline shaft 63, the output shaft 71 of the angular displacement sensor 7, and the output gear 66 to rotate in sequence. Among them, the second gear 34 and the first worm 42 rotate synchronously under the action of the second flat key 35; the first worm wheel 44 and the first spline shaft 63 rotate synchronously under the action of the third flat key 43; the first spline shaft 63 and the output gear 66 rotate synchronously. During the rotation of the output gear 66, the first spline shaft 63 drives the output shaft 71 of the angular displacement sensor 7 to rotate synchronously. The high-precision signal output by the angle sensor 7 is collected by the control circuit to control the rotation angle of the output gear 66 of the drive mechanism. At the same time, the rotation angle of the output gear 66 of the drive mechanism can be adjusted by collecting different signals output by the angle sensor 7 through the control circuit, thereby meeting the requirement of adjustable angle of the output shaft of the aviation drive mechanism and ensuring reliable flight of the aircraft. In addition, the lead wire of the angle sensor 7 can be fixed on the partition 52 by the wire clamp 72.

[0052] Drive motor 1 drives the first planetary reducer, the first planetary reducer drives the second planetary reducer, the second planetary reducer drives the first gear to rotate through the second planetary support, the first gear meshes with the second gear, driving the second gear to rotate, the second gear is connected to the first worm through the second flat key, the first worm meshes with the first worm wheel, driving the first worm wheel to rotate, the first worm wheel drives the first spline shaft to rotate through the third flat key, and the first spline shaft drives the output gear to rotate through the spline.

[0053] The above description merely illustrates embodiments of the present invention and is quite specific and detailed; however, it should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the protection scope of the present invention. Therefore, the protection scope of this invention patent should be determined by the appended claims.

Claims

1. A compact aerospace drive mechanism with a combined transmission method and adjustable angle, characterized in that... The aviation drive mechanism includes: The mechanism housing has a partition, a first protective cover and a second protective cover arranged inside it, and the partition, the first protective cover and the second protective cover divide the interior of the mechanism housing into a left cavity and a right cavity. Threaded holes are provided on the outer surface of the mechanism housing for installing and fixing the aircraft drive mechanism. A two-stage planetary gear reducer is arranged outside the housing of the mechanism. The two-stage planetary gear reducer has a first row of planetary reducers, a second row of planetary reducers, and an internal gear ring. The first row of planetary reducers and the second row of planetary reducers are arranged inside the internal gear ring. A primary gear pair is arranged in the right cavity of the housing and includes a first gear and a second gear that mesh with each other. The first gear is connected to the second row of planetary reducers. A primary worm gear pair is arranged in the right cavity of the housing. The primary worm gear pair includes a first worm, a first worm wheel, a second bearing, and a third flat key. The first worm meshes with the first worm wheel. The first worm is connected and fixed to the second gear via the second flat key, and the first worm and the second gear have a common axis. The first worm is supported and fixed to the housing by the second bearing, and the first worm and the second bearing have a common axis. The first worm wheel transmits torque via the third flat key. A primary spline pair is arranged in the right cavity of the housing. The primary spline pair has a third bearing, a first spline shaft, a first output gear, and a screw combination fastener. The first spline shaft is supported and installed in the right cavity of the housing formed by the mechanism housing and the partition plate by two of the third bearings. The effective portion of the outer spline of the first spline shaft extends horizontally to the right and protrudes from the mechanism housing. The effective portion of the external spline of the first spline shaft meshes with the internal spline of the first output gear; the first worm gear is fixed to the first spline shaft via the third flat key, and the first spline shaft, the first worm gear, and the first output gear have a common axis. The drive motor, the main body of which is located outside the housing of the mechanism, is fixed to the housing of the mechanism by two screws passing through the mounting lug holes of the internal gear ring. The drive motor has a drive motor output shaft. The two-stage planetary gear reducer is placed at the end of the drive motor output shaft. The drive motor output shaft has a flat structure and extends horizontally. The drive motor output shaft enters the two-stage planetary gear reducer horizontally. The drive motor drives the first-stage gear pair, the first-stage worm gear pair, and the first-stage spline pair to rotate in sequence through the first-row planetary reducer and the second-row planetary reducer, and finally drives the first output gear to rotate. The first splined shaft has an internal threaded hole on one side of the external splined shaft end; the first output gear has an internal splined and is fixed to the first splined shaft by the screw combination fastener; The aircraft drive mechanism has an angular displacement sensor, which is arranged inside the left cavity of the housing. The angular displacement sensor has a sensor output shaft that extends horizontally. The sensor output shaft passes through the partition and enters the right cavity of the housing, where it is connected and fixed to the first splined shaft. The sensor output shaft rotates synchronously with the first splined shaft and shares a common axis with the first splined shaft.

2. The aerospace drive mechanism as described in claim 1, characterized in that, The first-row planetary reducer includes a first sun gear, a first set screw, a first open retaining ring, a retaining ring, first planet gears, and a first planetary carrier. The first sun gear is fixed to the output shaft of the drive motor by the first set screw and rotates synchronously with the output shaft of the drive motor. The first sun gear and the output shaft of the drive motor share a common axis of rotation. The first sun gear meshes with three first planet gears simultaneously. The first planetary carrier is triangular in shape, with a raised shaft corresponding to each corner in the axial direction. A groove is provided on each raised shaft. The three first planet gears are mounted on the three raised shafts of the first planetary carrier. The retaining ring and the first open retaining ring are sequentially mounted on the end face of each first planet gear away from the first planetary carrier. The first open retaining ring is engaged in the groove on the raised shaft of the first planetary carrier. Each first planet gear and the corresponding raised shaft of the first planetary carrier share a common axis of rotation. The first row of planetary reducers has three first planetary gears that simultaneously mesh with the internal gear ring; the second row of planetary reducers has a second sun gear, a second planetary gear, a second planetary carrier, and a first bearing; the second sun gear is mounted on the first planetary carrier, and the second sun gear rotates synchronously with the first planetary carrier and has a common axis of rotation with the first planetary carrier; The second planetary carrier is triangular in shape, with a protruding shaft at each corner corresponding to the axial direction. An extended shaft extends along the axial direction at the other end face of the second planetary carrier, and a groove is provided on the outer surface of the shaft end. Three second planetary gears are mounted on the three protruding shafts of the second planetary carrier. All three second planetary gears simultaneously mesh with the second sun gear and the internal gear ring. Each second planetary gear shares a common axis of rotation with its corresponding protruding shaft on the second planetary carrier. All three second planetary gears of the second-row planetary reducer simultaneously mesh with the internal gear ring. The first bearing is mounted on the extended shaft of the second planetary carrier. The primary gear pair also has a first flat key and a second open retaining ring; the first gear is mounted on the extension shaft of the second planetary carrier via the first flat key, and the first gear and the second planetary carrier have a common axis; the second open retaining ring is engaged in a groove on the extension shaft of the second planetary carrier; The second open retaining ring serves to prevent the first gear from falling off the second planetary carrier; The second gear transmits torque via the second flat key.

3. The aerospace drive mechanism as described in claim 1, characterized in that, The sensor output shaft has a straight protrusion, and a straight groove is formed on the left end face of the first spline shaft. The protrusion of the sensor output shaft is inserted into the groove on the left end face of the first spline shaft.

4. The aerospace drive mechanism as described in claim 1, characterized in that, The drive motor is an adjustable speed brushless DC motor.

5. The aerospace drive mechanism as described in claim 1, characterized in that, The second gear has a protruding structure at one end, and the protruding end face of the second gear is close to the shoulder end face of the first worm. The second bearing has one end face close to the non-protruding end face of the second gear, and the other end face of the second bearing is axially positioned by the second protective cover.

6. The aerospace drive mechanism as described in claim 1, characterized in that, The partition is provided with a bearing chamber for placing and supporting the third bearing; the partition is positioned by a positioning pin; the partition has threaded holes for installing wire clamps, and the lead wire of the angular displacement sensor is fixed by the wire clamps.

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