A rocket air rudder rotating mechanism and assembly method thereof

Abstract

The present invention discloses a rocket air rudder rotating mechanism and an assembly method thereof, which belongs to the field of rocket flight control technology, and includes a rocket bulkhead, an outer ring support seat, an inner ring support seat, a rudder shaft system and an outer rocker arm; the rudder shaft system includes a rudder shaft; one end of the rudder shaft is fixedly arranged in an outer mounting cavity and an inner mounting cavity inside the rocket bulkhead, and the other end is used to fix the rudder surface and extends out of the rocket bulkhead; the outer rocker arm is configured to be able to drive the rudder shaft to rotate around its axis under the action of an external driving force; the rocket air rudder rotating mechanism is configured so that when the rudder shaft system is installed, the rudder shaft system is inserted into the outer mounting cavity and the inner mounting cavity as a whole, and is fixedly connected to the outer ring support seat. The present invention can insert the rudder shaft system as a whole into the outer mounting cavity and the inner mounting cavity when the rudder shaft system is assembled, so as to realize modular installation, reduce the requirements for the operating space, and effectively reduce the assembly difficulty of the linear servo rotation mechanism.

Description

Technical Field

[0001] The invention relates to the technical field of rocket flight control, and in particular to a rocket air rudder rotating mechanism and an assembly method thereof. Background Art

[0002] The air rudder is one of the important components of the launch vehicle's attitude control. The deflection of the air rudder is controlled by the servo to change the air flow, thereby generating a control torque so that the rocket can reach a specific attitude.

[0003] Servos are divided into linear servos and rotary servos. Rotary servos are difficult to achieve large torque, while linear servos are easy to achieve large torque, so they are widely used in the field of launch vehicle servos. A servo rotary mechanism is required for force conversion between the linear servo and the control surface.

[0004] The linear servo rotation mechanism involves the rudder shaft, rudder surface, bearings, rocker arms and support seats. The traditional installation method of the linear servo rotation mechanism is to install the involved components on the rocket cabin wall in sequence, so it has high requirements for the operating space.

[0005] In daily practice, the inventors found that the existing technical solutions have the following problems:

[0006] The Chinese invention patent with application number 201710470426.7 discloses an air rudder transmission structure. For small launch vehicles, due to the limitations of their structure and volume, the operating space is limited when the linear servo rotation mechanism is installed, which will increase the assembly time and difficulty.

[0007] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the invention

[0008] In order to solve the above-mentioned technical problems, the present application provides a rocket air rudder rotation mechanism, which adopts a modular structure. When the rudder shaft system is assembled, the rudder shaft system can be inserted into the outer mounting cavity and the inner mounting cavity as a whole, thereby realizing modular installation, reducing the requirements for operating space, and effectively reducing the assembly difficulty of the linear servo rotation mechanism.

[0009] A rocket air rudder rotating mechanism, comprising: a rocket bulkhead, a rudder shaft system, an outer rocker arm, and an outer ring support seat and an inner ring support seat;

[0010] A rudder shaft mounting hole is provided on the rocket cabin wall;

[0011] The outer ring support seat is fixedly connected to the inner wall surface of the rocket cabin wall; the outer ring support seat is provided with an outer mounting cavity;

[0012] The inner ring support seat is fixedly connected to the outer ring support seat; an inner mounting cavity is provided on the inner ring support seat; the outer mounting cavity, the inner mounting cavity and the rudder shaft mounting hole are interconnected in the radial direction of the arrow body;

[0013] The rudder shaft system comprises a rudder shaft and a fixing mechanism; the inner end of the rudder shaft is arranged in the outer mounting cavity and the inner mounting cavity through the fixing mechanism; the outer end of the rudder shaft is used to fix the rudder surface and extends out of the rocket cabin wall; the rudder shaft is fixedly connected to the outer ring support seat through the fixing mechanism in its axial direction;

[0014] The outer rocker arm is arranged in the rocket cabin wall; the outer rocker arm is configured to be able to drive the rudder shaft to rotate around its axis under the action of an external driving force;

[0015] The rocket air rudder rotating mechanism is configured such that when the rudder shaft system is installed, the rudder shaft system is inserted into the outer mounting cavity and the inner mounting cavity as a whole and is fixedly connected to the outer ring support seat.

[0016] Preferably, the fixing mechanism includes a bearing sleeve and a baffle; the rudder shaft is fixed in the bearing sleeve through a bearing; the baffle is used to fix the rudder shaft system to the outer ring support seat; the baffle cover is arranged at the outer port of the bearing sleeve and is fixedly connected to the outer end surface of the bearing sleeve; the outer wall of the bearing sleeve is adapted to the outer mounting cavity and the inner mounting cavity, so that the bearing sleeve can be inserted into the outer mounting cavity and the inner mounting cavity from the outside of the arrow body.

[0017] Preferably, the baffle is adapted to the rudder shaft mounting hole, can be inserted into the rudder shaft mounting hole and fixedly connected to the outer ring support seat.

[0018] Preferably, the rudder shaft comprises a shaft body and a limit block arranged on the shaft body; a limit hole is provided on the baffle; and the limit block is adapted to the limit hole.

[0019] Preferably, the bearing comprises an outer support bearing and an inner support bearing; the outer support bearing is arranged close to the outer port of the bearing sleeve; and the inner support bearing is arranged close to the inner port of the bearing sleeve.

[0020] Preferably, the rudder shaft system also includes an inner rocker arm connected to the outer rocker arm for transmitting driving force; the inner rocker arm is arranged between the outer support bearing and the inner support bearing; the inner rocker arm is rotationally connected to the rudder shaft through a shear pin; the shear pin is arranged perpendicular to the length direction of the rudder shaft.

[0021] Preferably, the fixing mechanism also includes a bearing inner ring fixing shoulder and a bearing outer ring fixing shoulder, which are arranged at the inner end of the rudder shaft for limiting the inner support bearing; the bearing inner ring fixing shoulder is fixedly connected to the inner end of the rudder shaft; the bearing outer ring fixing shoulder is fixedly connected to the inner end of the bearing sleeve.

[0022] Preferably, the fixing mechanism also includes an outer bearing retaining ring and an inner bearing retaining ring which are sleeved on the rudder shaft; the outer bearing retaining ring is arranged between the outer support bearing and the inner rocker arm; the outer end of the outer bearing retaining ring is in conflict with the inner ring of the outer support bearing, and the inner end of the outer bearing retaining ring is in conflict with the inner rocker arm; the inner bearing retaining ring is arranged between the inner rocker arm and the inner support bearing; the outer end of the inner bearing retaining ring is in conflict with the inner rocker arm, and the inner end of the inner bearing retaining ring is in conflict with the inner ring of the inner support bearing.

[0023] Preferably, the fixing mechanism also includes an inner bearing outer ring clearance adjustment gasket and an outer bearing outer ring clearance adjustment gasket; the inner bearing outer ring clearance adjustment gasket is arranged between the baffle and the outer support bearing; the outer bearing outer ring clearance adjustment gasket is arranged between the inner support bearing and the bearing outer ring fixed shoulder.

[0024] Preferably, the inner bearing outer ring clearance adjustment gasket and the outer bearing outer ring clearance adjustment gasket are both made of brass material.

[0025] According to another aspect of the present invention, a method for assembling a rocket air rudder rotating mechanism is provided, wherein assembling the rocket air rudder rotating mechanism comprises:

[0026] The inner end of the rudder shaft passes through the limiting hole of the baffle plate, so that the limiting block contacts the limiting hole;

[0027] Install the outer bearing outer ring clearance adjustment shim and the outer support bearing into the rudder shaft in sequence;

[0028] Install the bearing sleeve on the outer surface of the outer ring of the outer support bearing, and fix the outer end surface of the bearing sleeve to the baffle through bolts;

[0029] Install the outer bearing retaining ring and the inner rocker arm on the rudder shaft in sequence. After the inner rocker arm is installed to the preset position, the shear pin passes through both the inner rocker arm and the rudder shaft and is fixed to the rudder shaft.

[0030] Install the inner bearing retaining ring and the inner support bearing in the bearing sleeve and on the rudder shaft located inside the inner rocker arm in sequence, so that the outer ring of the inner support shaft contacts the inner wall of the bearing sleeve;

[0031] Install the bearing inner ring fixing shoulder on the inner end face of the rudder shaft to fix the inner ring of the inner support bearing;

[0032] The bearing outer ring fixed shoulder is fixed to the inner end face of the bearing sleeve by bolts, and the inner bearing outer ring clearance adjustment gasket is installed between the inner end face of the inner support bearing and the bearing outer ring fixed shoulder; thus, the assembly of the rudder shaft system is completed;

[0033] Insert the bearing sleeve into the outer mounting cavity on the outer ring support seat and the inner mounting cavity on the inner ring support seat in sequence, realize positioning by relying on the limiting function of the bearing sleeve, and embed the baffle into the rudder shaft installation hole to realize the overall insertion of the rudder shaft system;

[0034] The baffle plate and the outer ring support seat are fixedly connected by bolts to realize the overall fixed connection of the rudder shaft system;

[0035] The outer rocker arm and the inner rocker arm are fixedly connected by bolts to complete the assembly of the rocket air rudder rotation mechanism.

[0036] Compared with the prior art, this application has at least the following beneficial effects:

[0037] 1. The rocket air rudder rotation mechanism of the present invention adopts a modular structure. When the rudder shaft system is assembled, the rudder shaft system can be inserted into the outer mounting cavity and the inner mounting cavity as a whole, thereby realizing modular installation, reducing the requirements for the operating space, effectively reducing the assembly difficulty of the linear servo rotation mechanism, and improving the assembly efficiency.

[0038] 2. The rocket air rudder rotating mechanism of the present invention adopts inner and outer ring clearance adjustment gaskets, which reduces the requirements for the dimensional tolerances of other parts, facilitates the adjustment of the bearing clearance, and simplifies the installation and disassembly of the rudder shaft. The rudder shaft and inner support bearing and related components can be installed before the rudder shaft system is installed with an arrow. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale. In the accompanying drawings:

[0040] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0041] Figure 2 It is a structural schematic diagram of the rudder shaft system of the present invention;

[0042] Figure 3 It is a structural schematic diagram of the rudder shaft of the present invention.

[0043] The above drawings include the following reference numerals:

[0044] 1. Rudder shaft system; 2. Outer ring support seat; 3. Rocket cabin wall; 4. Inner ring support seat; 5. Outer rocker arm; 11. Rudder shaft; 12. Baffle; 13. Outer support bearing; 14. Bearing sleeve; 15. Outer bearing retaining ring; 16. Inner rocker arm; 17. Shear pin; 18. Inner bearing retaining ring; 19. Inner support bearing; 101. Shaft body; 102. Limit block; 110. Bearing inner ring fixed shoulder; 111. Bearing outer ring fixed shoulder; 112. Inner bearing outer ring clearance adjustment gasket; 113. Outer bearing outer ring clearance adjustment gasket. DETAILED DESCRIPTION

[0045] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.

[0046] like Figure 1-3 The rocket air rudder rotating mechanism comprises: a rocket cabin wall 3, an outer ring support seat 2, an inner ring support seat 4, a rudder shaft system 1 and an outer rocker arm 5.

[0047] A rudder shaft mounting hole is provided on the rocket cabin wall 3.

[0048] The outer ring support seat 2 is fixedly connected to the inner wall surface of the rocket cabin wall 3 by bolts. The outer ring support seat 2 is provided with an outer mounting cavity.

[0049] The inner ring support seat 4 is fixedly connected to the outer ring support seat 2 by bolts. An inner mounting cavity is provided on the inner ring support seat 4. The outer mounting cavity, the inner mounting cavity and the rudder shaft mounting hole are interconnected in the radial direction of the arrow body, so that the rudder shaft system 1 can be inserted as a whole and installed and fixed.

[0050] The rudder shaft system 1 includes a rudder shaft 11 and a fixing mechanism. The inner end of the rudder shaft 11 is arranged in the outer mounting cavity and the inner mounting cavity through the fixing mechanism. The outer end of the rudder shaft 11 is used to fix the rudder surface and extends out of the rocket cabin wall 3. The rudder shaft 11 is fixedly connected to the outer ring support seat 2 in its axial direction through the fixing mechanism.

[0051] The outer rocker arm 5 is arranged in the rocket cabin wall 3. The outer rocker arm 5 is configured to be able to drive the rudder shaft 11 to rotate around its axis under the action of an external driving force.

[0052] The rocket air rudder rotating mechanism is configured so that when the rudder shaft system 1 is installed, the rudder shaft system 1 is inserted into the outer mounting cavity and the inner mounting cavity as a whole and is fixedly connected to the outer ring support seat 2.

[0053] The fixing mechanism includes a bearing sleeve 14 and a baffle 12. The rudder shaft 11 is fixed in the bearing sleeve 14 through a bearing; the baffle 12 is used to fix the rudder shaft system 1 with the outer ring support seat 2; the baffle 12 is covered at the outer end of the bearing sleeve 14 and fixedly connected to the outer end surface of the bearing sleeve 14; the outer wall of the bearing sleeve 14 is adapted to the outer mounting cavity and the inner mounting cavity, so that the bearing sleeve 14 can be inserted into the outer mounting cavity and the inner mounting cavity from the outside of the arrow body.

[0054] Preferably, a positioning ring is provided at the outer end of the bearing sleeve 14 for positioning the rudder shaft system 1 when it is installed and matched with the outer ring support seat 2.

[0055] The baffle plate 12 is adapted to the rudder shaft mounting hole so that it can be inserted into the rudder shaft mounting hole and fixedly connected to the outer ring support seat 2 .

[0056] The rudder shaft 11 includes a shaft body 101 and a limit block 102 arranged on the shaft body 101; a limit hole is opened on the baffle 12; the limit block 102 is adapted to the limit hole, so that the limit block 102 can be at least partially inserted into the limit hole to realize the positioning of the rudder shaft 11.

[0057] The bearing includes an outer support bearing 13 and an inner support bearing 19 ; the outer support bearing 13 is arranged close to the outer port of the bearing sleeve 14 ; the inner support bearing 19 is arranged close to the inner port of the bearing sleeve 14 .

[0058] In addition, a stepped shaft for positioning the external support bearing 13 is provided on the shaft body 101 .

[0059] In addition, the rudder shaft system 1 further includes an inner rocker arm 16 connected to the outer rocker arm 5 for transmitting driving force. The inner rocker arm 16 is arranged between the outer support bearing 13 and the inner support bearing 19, and the inner rocker arm 16 is rotatably connected to the rudder shaft 11 through a shear pin 17; the shear pin 17 is arranged perpendicular to the length direction of the rudder shaft 11.

[0060] In addition, the side wall of the bearing sleeve 14 is provided with an opening for connecting the inner rocker arm 16 and the outer rocker arm 5 and providing a sufficiently large swinging space for the inner rocker arm 16 to ensure the effective transmission of torque.

[0061] The fixing mechanism also includes a bearing inner ring fixing shoulder 110 and a bearing outer ring fixing shoulder 111, which are arranged at the inner end of the rudder shaft 11 for limiting the inner support bearing 19. The bearing inner ring fixing shoulder 110 is fixedly connected to the inner end of the rudder shaft 11; the bearing outer ring fixing shoulder 111 is fixedly connected to the inner end of the bearing sleeve 14.

[0062] The fixing mechanism also includes an outer bearing retaining ring 15 and an inner bearing retaining ring 18 which are sleeved on the rudder shaft 11; the outer bearing retaining ring 15 is arranged between the outer support bearing 13 and the inner rocker arm 16; the outer end of the outer bearing retaining ring 15 conflicts with the inner ring of the outer support bearing 13, and the inner end of the outer bearing retaining ring 15 conflicts with the inner rocker arm 16; the inner bearing retaining ring 18 is arranged between the inner rocker arm 16 and the inner support bearing 19; the outer end of the inner bearing retaining ring 18 conflicts with the inner rocker arm 16, and the inner end of the inner bearing retaining ring 18 conflicts with the inner ring of the inner support bearing 19.

[0063] That is to say, the outer support bearing 13, the outer bearing retaining ring 15, the inner rocker arm 16, the inner bearing retaining ring 18, and the inner support bearing 19 are connected to the shaft body 101 in sequence from the outside to the inside, and the outer support bearing 13, the outer bearing retaining ring 15, the inner rocker arm 16, the inner bearing retaining ring 18, and the inner support bearing 19 are tightly fitted at the contact position to achieve the axial upper limit positioning of the outer support bearing 13 and the inner support bearing 19 on the shaft body 101 to ensure their fixation.

[0064] As another embodiment of the present invention, the fixing mechanism further includes an inner bearing outer ring clearance adjustment shim 112 and an outer bearing outer ring clearance adjustment shim 113. The inner bearing outer ring clearance adjustment shim 112 is arranged between the baffle 12 and the outer support bearing 13; the outer bearing outer ring clearance adjustment shim 113 is arranged between the inner support bearing 19 and the bearing outer ring fixed shoulder 111. The arrangement of the inner bearing outer ring clearance adjustment shim 112 and the outer bearing outer ring clearance adjustment shim 113 can ensure that the clearances of the outer support bearing 13 and the inner support bearing 19 are adjusted to a suitable and feasible range, reduce the dimensional tolerance requirements for the baffle 12, the outer bearing retaining ring 15, the inner rocker arm 16, the inner bearing retaining ring 18 and the bearing inner ring fixed shoulder 110, and facilitate the simultaneous adjustment of the bearing clearances of the outer support bearing 13 and the inner support bearing 19.

[0065] Preferably, the inner bearing outer ring clearance adjustment gasket 112 and the outer bearing outer ring clearance adjustment gasket 113 are both made of brass material.

[0066] According to another aspect of the present invention, a method for assembling a rocket air rudder rotating mechanism is provided, wherein assembling the rocket air rudder rotating mechanism comprises:

[0067] The inner end of the rudder shaft passes through the limiting hole of the baffle plate, so that the limiting block contacts the limiting hole;

[0068] Install the outer bearing outer ring clearance adjustment shim and the outer support bearing into the rudder shaft in sequence;

[0069] Install the bearing sleeve on the outer surface of the outer ring of the outer support bearing, and fix the outer end surface of the bearing sleeve to the baffle through bolts;

[0070] Install the outer bearing retaining ring and the inner rocker arm on the rudder shaft in sequence. After the inner rocker arm is installed to the preset position, the shear pin passes through both the inner rocker arm and the rudder shaft and is fixed to the rudder shaft.

[0071] Install the inner bearing retaining ring and the inner support bearing in the bearing sleeve and on the rudder shaft located inside the inner rocker arm in sequence, so that the outer ring of the inner support shaft contacts the inner wall of the bearing sleeve;

[0072] Install the bearing inner ring fixing shoulder on the inner end face of the rudder shaft to fix the inner ring of the inner support bearing;

[0073] The bearing outer ring fixed shoulder is fixed to the inner end face of the bearing sleeve by bolts, and the inner bearing outer ring clearance adjustment gasket is installed between the inner end face of the inner support bearing and the bearing outer ring fixed shoulder; thus, the assembly of the rudder shaft system is completed;

[0074] Insert the bearing sleeve into the outer mounting cavity on the outer ring support seat and the inner mounting cavity on the inner ring support seat in sequence, realize positioning by relying on the limiting function of the bearing sleeve, and embed the baffle into the rudder shaft installation hole to realize the overall insertion of the rudder shaft system;

[0075] The baffle plate and the outer ring support seat are fixedly connected by bolts to realize the overall fixed connection of the rudder shaft system;

[0076] The outer rocker arm and the inner rocker arm are fixedly connected by bolts to complete the assembly of the rocket air rudder rotation mechanism.

[0077] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0078] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0079] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0080] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A rocket air rudder rotation mechanism, comprising a rocket bulkhead (3), a rudder shaft system (1) and an outer rocker arm (5); It is characterized in that Also includes: An outer ring support seat (2) and an inner ring support seat (4); The rocket cabin wall (3) is provided with a rudder shaft mounting hole; The outer ring support seat (2) is fixedly connected to the inner wall surface of the rocket cabin wall (3); an outer mounting cavity is provided on the outer ring support seat (2); The inner ring support seat (4) is fixedly connected to the outer ring support seat (2); an inner mounting cavity is provided on the inner ring support seat (4); the outer mounting cavity, the inner mounting cavity and the rudder shaft mounting hole are interconnected in the radial direction of the arrow body; The rudder shaft system (1) comprises a rudder shaft (11) and a fixing mechanism; the inner end of the rudder shaft (11) is arranged in the outer mounting cavity and the inner mounting cavity through the fixing mechanism; the outer end of the rudder shaft (11) is used to fix the rudder surface and extends out of the rocket cabin wall (3); the rudder shaft (11) is fixedly connected to the outer ring support seat (2) in its axial direction through the fixing mechanism; The outer rocker arm (5) is arranged in the rocket cabin wall (3); the outer rocker arm (5) is configured to be able to drive the rudder shaft (11) to rotate around its axis under the action of an external driving force; The rocket air rudder rotating mechanism is configured such that when the rudder shaft system (1) is installed, the rudder shaft system (1) is inserted into the outer mounting cavity and the inner mounting cavity as a whole, and is fixedly connected to the outer ring support seat (2); The fixing mechanism comprises a bearing sleeve (14) and a baffle (12); the rudder shaft (11) is fixedly arranged in the bearing sleeve (14) via a bearing; the baffle (12) is used to fix the rudder shaft system (1) to the outer ring support seat (2); the baffle (12) is arranged at the outer end of the bearing sleeve (14) and is fixedly connected to the outer end surface of the bearing sleeve (14); the outer wall of the bearing sleeve (14) is adapted to the outer mounting cavity and the inner mounting cavity, so that the bearing sleeve (14) can be inserted into the outer mounting cavity and the inner mounting cavity from the outside of the arrow body.

2. The rocket air rudder rotating mechanism as claimed in claim 1, It is characterized in that The baffle (12) is adapted to the rudder shaft mounting hole, can be inserted into the rudder shaft mounting hole and fixedly connected to the outer ring support seat (2).

3. The rocket air rudder rotating mechanism as claimed in claim 2, It is characterized in that The rudder shaft (11) comprises a shaft body (101) and a limit block (102) arranged on the shaft body (101); a limit hole is provided on the baffle plate (12); and the limit block (102) is adapted to the limit hole.

4. The rocket air rudder rotating mechanism as claimed in claim 3, It is characterized in that The bearing comprises an outer support bearing (13) and an inner support bearing (19); the outer support bearing (13) is arranged close to an outer port of the bearing sleeve (14); and the inner support bearing (19) is arranged close to an inner port of the bearing sleeve (14).

5. The rocket air rudder rotating mechanism as claimed in claim 4, It is characterized in that The rudder shaft system (1) further comprises an inner rocker arm (16) connected to the outer rocker arm (5) for transmitting driving force; the inner rocker arm (16) is arranged between the outer support bearing (13) and the inner support bearing (19); the inner rocker arm (16) is rotatably connected to the rudder shaft (11) via a shear pin (17); the shear pin (17) is arranged perpendicular to the length direction of the rudder shaft (11).

6. The rocket air rudder rotating mechanism as claimed in claim 5, It is characterized in that The fixing mechanism further comprises a bearing inner ring fixing shoulder (110) and a bearing outer ring fixing shoulder (111) which are arranged at the inner end of the rudder shaft (11) and are used to limit the inner support bearing (19); the bearing inner ring fixing shoulder (110) is fixedly connected to the inner end of the rudder shaft (11); and the bearing outer ring fixing shoulder (111) is fixedly connected to the inner end of the bearing sleeve (14).

7. The rocket air rudder rotating mechanism as claimed in claim 6, It is characterized in that The fixing mechanism further comprises an outer bearing retaining ring (15) and an inner bearing retaining ring (18) which are sleeved on the rudder shaft (11); the outer bearing retaining ring (15) is arranged between the outer support bearing (13) and the inner rocker arm (16); the outer end of the outer bearing retaining ring (15) abuts against the inner ring of the outer support bearing (13), and the inner end of the outer bearing retaining ring (15) abuts against the inner rocker arm (16); the inner bearing retaining ring (18) is arranged between the inner rocker arm (16) and the inner support bearing (19); the outer end of the inner bearing retaining ring (18) abuts against the inner rocker arm (16), and the inner end of the inner bearing retaining ring (18) abuts against the inner ring of the inner support bearing (19).

8. The rocket air rudder rotating mechanism as claimed in claim 7, It is characterized in that The fixing mechanism further comprises an inner bearing outer ring clearance adjustment gasket (112) and an outer bearing outer ring clearance adjustment gasket (113); the inner bearing outer ring clearance adjustment gasket (112) is arranged between the baffle (12) and the outer support bearing (13); and the outer bearing outer ring clearance adjustment gasket (113) is arranged between the inner support bearing (19) and the bearing outer ring fixed shoulder (111).

9. A method for assembling a rocket air rudder rotating mechanism, It is characterized in that Assembling the rocket air rudder rotating mechanism of claim 8 comprises: The inner end of the rudder shaft (11) passes through the limiting hole of the baffle (12), so that the limiting block (102) contacts the limiting hole; Install the outer bearing outer ring clearance adjustment shim (113) and the outer support bearing (13) into the rudder shaft (11) in sequence; Installing the bearing sleeve (14) on the outer surface of the outer ring of the outer support bearing (13), and fixing the outer end surface of the bearing sleeve (14) to the baffle (12) by means of bolts; The outer bearing retaining ring (15) and the inner rocker arm (16) are sequentially mounted on the rudder shaft (11); after the inner rocker arm (16) is mounted to a preset position, the shear pin (17) is passed through both the inner rocker arm (16) and the rudder shaft (11) and fixed to the rudder shaft (11); The inner bearing retaining ring (18) and the inner support bearing (19) are sequentially installed in the bearing sleeve (14) and on the rudder shaft (11) located inside the inner rocker arm (16), so that the outer ring of the inner support shaft contacts the inner wall of the bearing sleeve (14); Install the bearing inner ring fixing shoulder (110) on the inner end surface of the rudder shaft (11) to fix the inner ring of the inner support bearing (19); The bearing outer ring fixing shoulder (111) is fixed to the inner end surface of the bearing sleeve (14) by means of bolts, and an inner bearing outer ring clearance adjustment gasket (112) is installed between the inner end surface of the inner support bearing (19) and the bearing outer ring fixing shoulder (111); thereby, the assembly of the rudder shaft system (1) is completed; Inserting the bearing sleeve (14) into the outer mounting cavity on the outer ring support seat (2) and the inner mounting cavity on the inner ring support seat (4) in sequence, positioning the bearing sleeve (14) by means of the limiting function, and embedding the baffle plate (12) into the rudder shaft mounting hole, thereby realizing the overall insertion of the rudder shaft system (1); The baffle plate (12) is fixedly connected to the outer ring support seat (2) by means of bolts to achieve an integral fixed connection of the rudder shaft system (1); The outer rocker arm (5) and the inner rocker arm (16) are fixedly connected by bolts to complete the assembly of the rocket air rudder rotating mechanism.

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