Air vane mounting structure

Abstract

The application discloses an air rudder mounting structure and belongs to the technical field of rocket air rudders. The air rudder mounting structure comprises a rocket cabin section with an air rudder mounting cavity, an air rudder mounting support, a rudder body and a rudder body driving device. The air rudder mounting support is detachably fixed in the air rudder mounting cavity. The rudder body comprises an integrally formed air rudder surface and a rudder shaft. The rudder shaft is rotationally connected with the air rudder mounting support. The rudder shaft is located in the air rudder mounting cavity as a whole. The rudder body driving device is arranged in the air rudder mounting cavity. The rudder body driving device is configured to drive the air rudder surface to deflect parallel to or at a certain angle to the rocket axis according to a rocket flight control command. The rudder body is integrally designed, and the connecting piece between the air rudder surface and the rudder shaft is omitted, so that the weight is lighter, and the rudder shaft has no protruding rocket body part, and the aerodynamic shape is better.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket air rudders, and in particular to an air rudder mounting structure. Background Art

[0002] The air rudder is an important component of the launch vehicle. It is used to adjust the attitude during flight, ensure the stability of the aircraft, and fly according to the predetermined trajectory.

[0003] Traditional air rudder installation involves bolts connecting the outer rudder shaft to the rudder surface, with the bolts protruding from the rocket. The rudder shaft passes through two bearings, mounted back-to-back or face-to-face, and clamped on the inside with nuts. A keyway is built into the inside of the rudder shaft, and the servo output torque is controlled through the rudder shaft keyway to control servo swing. This air rudder installation method features a separate rudder shaft and rudder surface, requiring numerous connection steps, with bolts protruding from the rocket body, resulting in a poor aerodynamic appearance and large installation dimensions.

[0004] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the Invention

[0005] In order to solve the above technical problems, the present application provides an air rudder installation structure, in which the rudder body is an integrated design, eliminating the connecting parts between the air rudder surface and the rudder shaft, making it lighter in weight, and the rudder shaft has no protruding part of the arrow body, and has a better aerodynamic shape.

[0006] An air rudder mounting structure, comprising:

[0007] A rocket compartment; the rocket compartment includes an air rudder mounting cavity;

[0008] An air rudder mounting support; the air rudder mounting support is detachably fixed in the air rudder mounting cavity;

[0009] The rudder body comprises an integrally formed air rudder surface and a rudder shaft; the rudder shaft is rotatably connected to the air rudder mounting support; the rudder shaft is integrally located in the air rudder mounting cavity;

[0010] A rudder body drive device; the rudder body drive device is arranged in the air rudder installation cavity; the rudder body drive device is configured to drive the air rudder surface to be parallel to the rocket axis or deflected at a certain angle according to the rocket flight control command.

[0011] Preferably, the rudder body driving device includes a servo and a transmission connecting member; the transmission connecting member is arranged between the servo and the rudder body; the servo includes a servo mounting part and a servo actuating part; the servo mounting part is fixedly connected to the rocket compartment; one end of the transmission connecting member is transmission-connected to the servo actuating part; the other end of the transmission connecting member is transmission-connected to the rudder shaft.

[0012] Preferably, the rudder shaft is internally provided with a rudder body transmission hole for transmission connection with the transmission connecting piece; the rudder actuator part comprises a plurality of mutually parallel transmission pins; the transmission connecting piece comprises a transmission connecting plate and a transmission connecting shaft fixedly connected with the transmission connecting plate; the transmission connecting plate comprises a plurality of transmission grooves adapted to the transmission pins; the transmission pins are inserted into the transmission grooves; the transmission connecting shaft is adapted to the rudder body transmission hole; and the transmission connecting shaft is inserted into the rudder body transmission hole.

[0013] Preferably, the air rudder mounting structure further comprises a fastening bolt for fixed connection of the transmission connecting shaft with the rudder shaft in the axial direction of the rudder shaft; the transmission connecting piece further comprises a fastener mounting hole penetrating through the transmission connecting piece; the rudder shaft is internally further provided with a threaded hole in communication with the rudder body transmission hole; one end of the fastening bolt is arranged in the fastener mounting hole; and the other end of the fastening bolt is connected with the threaded hole.

[0014] Preferably, the rudder body transmission hole is a multi-prism structure hole.

[0015] Preferably, the air rudder mounting support comprises a bearing mounting hole; the air rudder mounting structure further comprises a bearing fixedly arranged around the rudder shaft for radial fixation of the rudder shaft; and the bearing is fixedly arranged in the bearing mounting hole.

[0016] Preferably, the bearing mounting hole is 2; and the 2 bearing mounting holes have an intermediate ring.

[0017] Preferably, the bearing is a conical roller bearing.

[0018] Preferably, the rudder body further comprises a circular sealing cover; the sealing cover is fixedly connected with the rudder shaft; the outer diameter of the sealing cover is larger than the outer diameter of the rudder shaft; the sealing cover is adapted to the air rudder mounting cavity opening; and the sealing cover is arranged at the air rudder mounting cavity opening.

[0019] Compared with the prior art, the application has at least the following beneficial effects:

[0020] 1. The air rudder surface and the rudder shaft are designed in an integrated manner, and the connecting pieces such as bolts are omitted, so that the weight is lighter.

[0021] 2. The air rudder surface does not need to be tightened by bolts, and the operation steps are less during installation.

[0022] 3. The rudder shaft of the application does not have a protruding arrow part, and the aerodynamic shape is better.

[0023] 4. The rudder shaft of the application is designed in a hollow manner, and the weight is lighter.

[0024] 5、The bearing of the application adopts fastening bolt pre-tightening, the whole structure has smaller installation size in the rudder shaft axis direction, and occupies smaller space on the rocket body. BRIEF DESCRIPTION OF DRAWINGS

[0025] Some specific embodiments of the application will be described in detail below with reference to the attached drawings, which are provided by way of example and are not limiting of the application. Like references denote like elements or parts throughout the drawings. It should be understood that these drawings are not necessarily to scale. In the drawings:

[0026] Figure 1 is a whole perspective sectional view of the air rudder mounting structure of the application;

[0027] Figure 2 is a whole front sectional view of the air rudder mounting structure of the application;

[0028] Figure 3 is a structural schematic view of the air rudder mounting support of the application;

[0029] Figure 4 is a three-dimensional structural schematic view of the rudder body from a first perspective of the application;

[0030] Figure 5 is a three-dimensional structural schematic view of the rudder body from a second perspective of the application;

[0031] Figure 6 is Figure 5 is a local enlarged view of position A;

[0032] Figure 7 is a three-dimensional structural schematic view of the rudder body from a first perspective of the application;

[0033] Figure 8 is a three-dimensional structural schematic view of the rudder body from a second perspective of the application;

[0034] Figure 9 is a three-dimensional structural schematic view of the rudder body from a second perspective of the application.

[0035] In the above drawings, the following reference signs are used:

[0036] 1, rudder body, 2, rocket cabin section, 3, air rudder mounting support, 4, rudder machine, 5, bearing, 6, transmission connecting piece, 7, fastening bolt, 11, air rudder surface, 12, rudder shaft, 13, sealing cover, 14, threaded hole, 15, rudder body transmission hole, 31, support body, 32, bearing mounting hole, 33, intermediate ring, 34, fixing hole, 41, rudder machine mounting part, 42, rudder machine actuating part, 43, transmission pin, 61, transmission connecting plate, 62, transmission connecting shaft, 63, transmission groove, 64, fastener mounting hole, 641, fastener end hole, 642, fastener connecting body hole. EMBODIMENTS

[0037] In order to make the purposes, technical solutions and advantages of the present application clearer, the technical solutions of the present application will be described clearly and completely below in connection with the embodiments of the present application and corresponding drawings. Obviously, the described embodiments are only some of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort belong to the scope of protection of the present application.

[0038] Figures 1-9 As shown in the figure, an air vane mounting structure comprises a vane body 1, a rocket cabin section 2, an air vane mounting support 3 and a vane body driving device. The rocket cabin section comprises an air vane mounting cavity. The air vane mounting support 3 is adapted to the air vane mounting cavity and has a fixing hole 34, which is penetrated by a fastener to be detachably fixed in the air vane mounting cavity in a threaded connection manner. The vane body 1 comprises an integrally formed air vane surface 11 and a vane shaft 12, the vane shaft 12 is rotationally connected with the air vane mounting support 3, and the vane shaft 12 is located entirely in the air vane mounting cavity. Since the vane shaft 12 is located entirely in the air vane mounting cavity, there is no protruding rocket body part, and the aerodynamic shape is better. The vane body driving device is arranged in the air vane mounting cavity, and the vane body driving device is configured to drive the air vane surface 11 to deflect parallel to or at a certain angle to the axis of the rocket according to the rocket flight control command.

[0039] The vane body driving device comprises a vane machine 4 and a transmission connecting piece 6. The vane machine 4 is selected from a shelf product. The transmission connecting piece 6 is arranged between the vane machine 4 and the vane body 1. The vane machine 4 comprises a vane machine mounting part 41 and a vane machine actuating part 42. The vane machine mounting part 41 is fixedly connected with the rocket cabin section 2. One end of the transmission connecting piece 6 is in transmission connection with the vane machine actuating part 42, and the other end is in transmission connection with the vane shaft 12.

[0040] Specifically, the vane shaft 12 is internally provided with a vane body transmission hole 15 for transmission connection with the transmission connecting piece 6. The vane machine actuating part 42 comprises a plurality of mutually parallel transmission pins 43. The transmission connecting piece 6 comprises a transmission connecting plate 61 and a transmission connecting shaft 62 fixedly connected with the transmission connecting plate 61. The transmission connecting plate 61 comprises a plurality of transmission grooves 63 adapted to the transmission pins 43, and the transmission pins 43 are inserted into the transmission grooves 63. The transmission connecting shaft 62 is adapted to the vane body transmission hole 15 and arranged in the vane body transmission hole 15.

[0041] In addition, the air vane mounting structure further comprises a fastening bolt 7 for fixedly connecting the transmission connecting shaft 62 and the vane shaft 12 in the axial direction of the vane shaft 12. The transmission connecting member 6 further comprises a fastener mounting hole 64 penetrating the transmission connecting member 6. The fastener mounting hole 64 comprises a fastener end hole 641 and a fastener connecting body hole 642 which are in communication with each other. The diameter of the fastener end hole 641 is larger than that of the fastener connecting body hole 642, so that the head of the fastening bolt 7 can enter the fastener end hole 641 and be limited at the connecting position of the fastener end hole 641 and the fastener connecting body hole 642. The vane shaft 12 is further provided with a threaded hole 14 which is in communication with the vane body transmission hole 15. One end of the fastening bolt 7 is arranged in the fastener mounting hole 64, and the other end is connected with the threaded hole 14.

[0042] Preferably, the vane body transmission hole 15 is a multi-prism structure hole. In order to facilitate processing and ensure the transmission of torque, in the embodiment, the vane body transmission hole 15 is selected as a cuboid structure hole.

[0043] In addition, the air vane mounting structure further comprises a bearing 5 which is fixedly arranged on the vane shaft 12 in the circumferential direction and is used for fixing the vane shaft 12 in the radial direction. The air vane mounting support 3 comprises a bearing mounting hole 32, and the bearing 5 is fixedly arranged in the bearing mounting hole 32. The bearing 5 is preferably a conical roller bearing.

[0044] Preferably, the bearing mounting hole 32 is 2, and the two bearing mounting holes 32 have a middle ring. The bearing 5 is pre-tightened by the fastening bolt 7, and the whole structure has a smaller installation size in the axial direction of the vane shaft 12, thereby occupying less space on the rocket body.

[0045] As an embodiment of the present application, the vane body 1 further comprises a circular sealing cover 13 which is fixedly connected with the vane shaft 12 and has an outer diameter larger than that of the vane shaft 12, thereby facilitating installation and sealing. The sealing cover 13 is adapted to the opening of the air vane mounting cavity, and the sealing cover 13 is arranged at the opening of the air vane mounting cavity.

[0046] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used herein to describe the spatial positional relationship of a device or feature to other devices or features as shown in the figures. 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 figures. For example, if the device in the 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.

[0047] 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, they indicate the presence of features, steps, tasks, devices, components and / or combinations thereof.

[0048] It should be noted that the terms "first," "second," and the like in the specification and claims of this application and the accompanying drawings are used to distinguish similar objects and are not necessarily used to describe a specific order or precedence. It should be understood that the terms used in this manner are interchangeable where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than that illustrated or described herein.

[0049] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. An air rudder mounting structure, characterized in that: include: rocket module; The rocket compartment includes an air rudder installation cavity; Air rudder mounting bracket; The air rudder mounting support is detachably fixed in the air rudder mounting cavity; The rudder body comprises an integrally formed air rudder surface and a rudder shaft; the rudder shaft is rotatably connected to the air rudder mounting support; the rudder shaft is integrally located in the air rudder mounting cavity; A rudder body drive device; the rudder body drive device is disposed in the air rudder mounting cavity; the rudder body drive device is configured to drive the air rudder surface to be parallel to the rocket axis or deflected at a certain angle according to the rocket flight control command; The rudder body drive device includes a steering gear and a transmission connecting member; the transmission connecting member is arranged between the steering gear and the rudder body; the steering gear includes a steering gear mounting portion and a steering gear actuating portion; the steering gear mounting portion is fixedly connected to the rocket compartment; one end of the transmission connecting member is transmission-connected to the steering gear actuating portion; the other end of the transmission connecting member is transmission-connected to the rudder shaft; A rudder body transmission hole for transmission connection with the transmission connecting piece is provided inside the rudder shaft; the servo actuating part includes a plurality of transmission pins parallel to each other; the transmission connecting piece includes a transmission connecting plate and a transmission connecting shaft fixedly connected to the transmission connecting plate; the transmission connecting plate includes a plurality of transmission grooves adapted to the transmission pins; the transmission pins are inserted into the transmission grooves; the transmission connecting shaft is adapted to the rudder body transmission hole; the transmission connecting shaft is inserted into the rudder body transmission hole.

2. The air rudder mounting structure according to claim 1, wherein: The air rudder mounting structure also includes a fastening bolt for fixedly connecting the transmission connecting shaft and the rudder shaft in the axial direction of the rudder shaft; the transmission connecting member also includes a fastener mounting hole passing through the transmission connecting member; a threaded hole connected to the rudder body transmission hole is also provided inside the rudder shaft; one end of the fastening bolt is provided in the fastener mounting hole; the other end of the fastening bolt is connected to the threaded hole.

3. The air rudder mounting structure according to claim 1 or 2, characterized in that: The rudder body transmission hole is a polygonal column structure hole.

4. The air rudder mounting structure according to claim 1, wherein: The air rudder mounting support includes a bearing mounting hole; the air rudder mounting structure also includes a bearing fixedly arranged on the circumference of the rudder shaft for fixing the rudder shaft radially; the bearing is fixedly arranged in the bearing mounting hole.

5. The air rudder mounting structure according to claim 4, wherein: There are two bearing mounting holes; and there is an intermediate annular rib between the two bearing mounting holes.

6. The air rudder mounting structure according to claim 5, characterized in that: The bearing is a tapered roller bearing.

7. The air rudder mounting structure according to claim 1, wherein: The rudder body also includes a circular sealing cover; the sealing cover is fixedly connected to the rudder shaft; the outer diameter of the sealing cover is larger than the outer diameter of the rudder shaft; the sealing cover is adapted to the opening of the air rudder installation cavity; the sealing cover is arranged at the opening of the air rudder installation cavity.

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