阅读说明：本技术 适用于空气舵与舵机系统连接的结构 (Structure suitable for air rudder and steering engine system connection ) 是由 张晓宏 邵庆 任智毅 夏鹏 程广益 陈寅玺 樊浩 许斌 宋波涛 于 2020-05-12 设计创作，主要内容包括：本发明提供了一种适用于空气舵与舵机系统连接的结构,包括舵轴、轴套以及连接件,所述舵轴安装在空气舵上,所述轴套安装在舵机上,所述舵轴通过连接件安装在轴套上,所述轴套内部还设置有第二容纳空间,所述第二容纳空间的一侧与外部连通,所述第二容纳空间的另一侧与第一容纳空间相连通,所述连接件匹配安装在第二容纳空间中并延伸到第一容纳空间与安装柄连接,本发明采用舵轴通过连接件安装在轴套上的结构既减轻了导弹的质量,结构紧凑,又减少了导弹飞行的阻力,装配简单,增加了空气舵与舵机的连接强度,能够承受更大的弯矩、扭矩和剪力能力,能够满足空气舵气动力的承载要求。(The invention provides a structure suitable for connecting an air rudder and a steering engine system, which comprises a rudder shaft, a shaft sleeve and a connecting piece, the rudder shaft is arranged on the air rudder, the shaft sleeve is arranged on the steering engine, the rudder shaft is arranged on the shaft sleeve through a connecting piece, a second accommodating space is also arranged in the shaft sleeve, one side of the second accommodating space is communicated with the outside, the structure that the rudder shaft is arranged on the shaft sleeve through the connecting piece reduces the quality of the missile, has a compact structure, reduces the flying resistance of the missile, is simple to assemble, increases the connecting strength of the air rudder and the steering engine, can bear larger bending moment, torque and shearing force, and can meet the bearing requirement of aerodynamic force of the air rudder.)

1. A structure suitable for connecting an air rudder and a steering engine system is characterized by comprising a rudder shaft (1), a shaft sleeve (2) and a connecting piece (3);

the rudder shaft (1) is arranged on an air rudder, and the shaft sleeve (2) is arranged on a steering engine;

the rudder shaft (1) is arranged on the shaft sleeve (2) through a connecting piece (3).

2. The structure suitable for connecting the air rudder and the steering engine system according to claim 1, wherein a mounting handle (4) is arranged on the rudder shaft (1), and a first accommodating space is arranged inside the shaft sleeve (2);

the mounting handle (4) extends into the first accommodating space from one end of the shaft sleeve (2) and is connected with the connecting piece (3) mounted from the other end of the shaft sleeve (2).

3. The structure suitable for being connected with an air rudder and a steering engine system according to claim 2, wherein a mounting pipe (11) is arranged on the rudder shaft (1), and a reinforcing support seat (12) is arranged between the mounting pipe (11) and the mounting handle (4).

4. The structure suitable for being connected with an air rudder and a steering engine system according to claim 2, wherein the mounting pipe (11), the reinforcing support seat (12) and the mounting handle (4) are integrally connected in sequence.

5. The structure suitable for being connected with an air rudder and a steering engine system according to claim 3, wherein the mounting pipe (11) is provided with an anti-rotation protrusion (13).

6. The structure suitable for connecting the air rudder and the steering engine system according to claim 4, wherein a first mounting table (5) is arranged on the mounting handle (4), and two support wings (6) extend from the reinforcing support base (12);

a first table board (7) and a second table board (8) are arranged on the shaft sleeve (2);

the first mounting table (5) is supported on the first table top (7) in a matching manner;

the two support wings (6) are supported on the second table top (8).

7. The structure suitable for connecting the air rudder and the steering engine system according to claim 1, wherein a second accommodating space is further arranged inside the shaft sleeve (2), one side of the second accommodating space is communicated with the outside, and the other side of the second accommodating space is communicated with the first accommodating space;

the connecting piece (3) is installed in the second accommodating space in a matching mode and extends into the first accommodating space to be connected with the installation handle (4).

8. The structure suitable for connecting the air rudder and the steering engine system according to claim 7, wherein an internal thread hole is formed in the mounting handle (4), and an external thread is formed in the connecting piece (3);

and one end of the connecting piece (3) connected with the mounting handle (4) is mounted in the internal thread hole in a matching manner.

9. The structure suitable for connecting the air rudder and the steering engine system according to claim 1, further comprising a fixing member, wherein an installation shaft is arranged on the air rudder, and a first fixing hole (9) and a second fixing hole (10) are arranged on the rudder shaft (1);

the mounting shaft is fixedly mounted on the rudder shaft (1) through fixing pieces respectively mounted on the first fixing hole (9) and the second fixing hole (10).

10. The structure suitable for being connected with an air rudder and a steering engine system according to claim 2, wherein the mounting handle (4) is a stepped integrated piece formed by two cylinders with different diameters which are concentrically arranged in sequence.

Technical Field

The invention relates to the field of missile general design, in particular to a structure suitable for connecting an air rudder and a steering engine system.

Background

Along with the fact that the flying speed of the missile is faster and higher, the requirement on maneuverability is higher and higher, the aerodynamic force borne by the missile is larger and larger, and the air rudder is used as a main pneumatic control torque to output and needs to bear very large pneumatic load.

At present air vane and steering wheel system's connection generally adopts a flange that part adds thickly, be connected through screw and steering wheel system, the bolt is as mainly resisting aerodynamic force's structure and need bear huge pulling force and shear force, all show in the air vane strength test experiment of various models that this department is the weak link of intensity of air vane, and in order to reduce the atress of bolt, often need the interval of increase adjacent screw, cause this department flange size to increase, the passive quality of guided missile has been increased in the intangible, and because there is great shape sudden change here with the air vane appearance, also can increase the flight resistance of guided missile.

Patent document CN106976550B discloses an aircraft rudder and air rudder linkage mechanism. The mechanism comprises: the combustion chamber, the spray pipe outer cover, the ball screw transmission mechanism, the gas rudder deflection mechanism and the air rudder deflection mechanism, wherein a servo motor rotor is connected with a screw rod through a coupler, the screw rod rotates to drive a screw rod nut to do linear motion, an actuating rod and a piston actuator are driven to control the gas rudder and the air rudder to be in linkage deflection, and deflection angles are close to the same; the motor fixing frame and the screw rod supporting frame are fixed with the inner surface of the spray pipe outer cover in a superposition mode through the arc-shaped surface, the screw rod nut and the air rudder are in transmission in a matched mode through a cylinder barrel piston structure, but the air rudder is complex in connecting structure and not suitable for connection of the air rudder and a steering engine.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide a structure suitable for connecting an air rudder and a steering engine system.

The structure suitable for connecting the air rudder and the steering engine system comprises a rudder shaft, a shaft sleeve and a connecting piece, wherein the rudder shaft is connected with the shaft sleeve through the connecting piece;

the rudder shaft is arranged on the air rudder, and the shaft sleeve is arranged on the steering engine;

the rudder shaft is arranged on the shaft sleeve through a connecting piece.

Preferably, the rudder shaft is provided with a mounting handle, and a first accommodating space is arranged inside the shaft sleeve;

the mounting shank extends from one end of the boss to the inside of the first receiving space and is connected to a connecting member mounted from the other end of the boss.

Preferably, the rudder shaft is provided with a mounting pipe, and a reinforcing support seat is arranged between the mounting pipe and the mounting handle.

Preferably, the installation pipe, the reinforcing support seat and the installation handle are sequentially and integrally connected.

Preferably, the mounting tube is provided with an anti-rotation protrusion.

Preferably, the mounting handle is provided with a first mounting platform, and the reinforcing support seat extends out of two support wings;

the shaft sleeve is provided with a first table surface and a second table surface;

the first mounting table is supported on the first table top in a matching manner;

the two support wings are supported on the second table top.

Preferably, a second accommodating space is further arranged in the shaft sleeve, one side of the second accommodating space is communicated with the outside, and the other side of the second accommodating space is communicated with the first accommodating space;

the connecting piece is installed in the second accommodating space in a matched mode and extends into the first accommodating space to be connected with the installation handle.

Preferably, the mounting handle is provided with an internal thread hole, and the connecting piece is provided with an external thread;

and one end of the connecting piece, which is connected with the mounting handle, is mounted in the internal thread hole in a matching manner.

Preferably, the air rudder further comprises a fixing piece, wherein an installation shaft is arranged on the air rudder, and a first fixing hole and a second fixing hole are formed in the rudder shaft;

the mounting shaft is fastened and mounted on the rudder shaft through fixing pieces respectively mounted on the first fixing hole and the second fixing hole.

Preferably, the mounting shank is a stepped integral piece formed by two cylinders of different diameters arranged concentrically one after the other.

Compared with the prior art, the invention has the following beneficial effects:

1. the structure that the rudder shaft is arranged on the shaft sleeve through the connecting piece reduces the quality of the guided missile, has compact structure, reduces the flying resistance of the guided missile, is simple to assemble, and increases the connection strength of the air rudder and the steering engine.

2. The rudder shaft and the shaft sleeve are easy to process, assembly can be completed only by directly inserting and installing the connecting piece at the tail end, the rudder shaft and the shaft sleeve form a solid structure form of an assembly body center, and the rudder shaft and the shaft sleeve can bear larger bending moment, torque and shearing force capability and meet the bearing requirement of aerodynamic force of the air rudder.

3. The connection of the air rudder and the steering engine system only needs one screw for fastening, and the screw only needs to bear the aerodynamic force component in the spreading direction of the air rudder, so that the screw is completely in a great strength storage state in the whole missile flying process, the connection of the air rudder is more reliable, the bearing capacity of the air rudder on aerodynamic force is stronger, the bearing mode is more accordant with the force bearing characteristic of the structure, and the assembly of the air rudder and the steering engine system structure is more simple, convenient and reliable.

4. According to the invention, the first mounting platform and the two support wings are respectively matched with the first table top and the second table top, so that the structure is more stable and firm.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic side view of the present invention taken along the length of the mounting tube;

FIG. 3 is a schematic top view of the present invention;

fig. 4 is a schematic structural view of the air rudder installation device of the present invention.

The figures show that:

mounting tube 11 for support wing 6 of rudder shaft 1

First table surface 7 reinforcing support seat 12 of shaft sleeve 2

Anti-rotation projection 13 of second table surface 8 of connecting piece 3

First fixing hole 9 of mounting handle 4

Second fixing hole 10 of first mounting table 5

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

The invention provides a structure suitable for system connection of an air rudder and a steering engine, which comprises a rudder shaft 1, a shaft sleeve 2 and a connecting piece 3, wherein the rudder shaft 1 is arranged on the air rudder, the shaft sleeve 2 is arranged on the steering engine, and the rudder shaft 1 is arranged on the shaft sleeve 2 through the connecting piece 3, as shown in figures 1, 3 and 4.

Further, as shown in fig. 1 and 4, the rudder shaft 1 belongs to a part of an air rudder, the shaft sleeve 2 belongs to a part of a steering engine system, and the connection structure of the air rudder and the steering engine system is tightly connected through a connection screw, so that the air rudder and the steering engine system can be reliably and tightly connected

Specifically, as shown in fig. 1 and 2, a second accommodating space is further provided inside the shaft sleeve 2, one side of the second accommodating space is communicated with the outside, the other side of the second accommodating space is communicated with the first accommodating space, and the connecting member 3 is mounted in the second accommodating space in a matching manner and extends into the first accommodating space to be connected with the mounting shank 4. At one isPreferred embodiment(s) of the invention The mounting handle 4 is provided with an internal threaded hole, the connecting piece 3 is provided with external threads, the connecting piece 3 adopts a high-strength inner hexagonal single-head bolt, and the threaded end of the inner hexagonal single-head bolt is mounted in the internal threaded hole in a matching manner.

Further, as shown in fig. 1 and 2, the mounting handle 4 is a stepped integrated member formed by two cylinders with different diameters concentrically arranged in sequence, and the mounting handle 4 adopts a solid structure form, so that the mounting handle can bear larger bending moment, torque and shearing force, and the bearing requirement of aerodynamic force of the air rudder is met.

Specifically, as shown in fig. 1 and fig. 2, the rudder shaft 1 is provided with an installation handle 4, and a first accommodating space is arranged inside the shaft sleeve 2; the mounting shank 4 extends from one end of the boss 2 into the interior of the first receiving space and is connected to the connecting member 3 mounted from the other end of the boss 2 at one endPreferred embodiment(s) of the inventionThe mounting handle 4 is provided with a first mounting table 5, the reinforcing support seat 12 extends to form two support wings 6, the shaft sleeve 2 is provided with a first table surface 7 and a second table surface 8, and the first mounting table 5 is supported on the first table surface 7 in a matching manner; the two support wings 6 are supported on a second table top 8.

Specifically, as shown in fig. 1, the rudder shaft 1 is provided with a mounting tube 11, a reinforcing support base 12 is arranged between the mounting tube 11 and the mounting shank 4, and one reinforcing support base is arrangedPreferred embodiment(s) of the inventionIn the middle of, installation pipe 11, strengthen supporting seat 12, installation handle 4 are connected as an organic whole in proper order, have increased the intensity of support connection.

Specifically, as shown in fig. 1 and 2, the mounting tube 11 is provided with an anti-rotation protrusion 13 to prevent the air vane from rotating, which is beneficial to firm connection and stable fixation of the air vane.

Specifically, as shown in fig. 1, the rudder further includes a fixing member, an installation shaft is disposed on the air rudder, and a first fixing hole 9 and a second fixing hole 10 are disposed on the rudder shaft 1; the mounting shaft is fastened and mounted on the rudder shaft 1 through fasteners respectively mounted on the first fixing hole 9 and the second fixing hole 10, for example, the fasteners are screws.

The rudder shaft 1 is mainly matched with the corresponding plane of the shaft sleeve 2 through two parallel planes, and bears the bending moment, the torque and the shearing force transmitted by the aerodynamic force of the air rudder through the combination body, and the cross section shape of the rudder shaft 1 is suitable for bearing the load, so that a smaller structural appearance is kept while a larger aerodynamic load is borne, the shape mutation of the root part of the air rudder is smaller, and the integral aerodynamic appearance of the air rudder is more optimized; the connecting screw is connected with the thread of a slender shaft on the rudder shaft 1 in a screwing way to tighten and fixedly connect the rudder shaft 1 with the shaft sleeve 2, wherein the connecting screw only needs to bear the component force of the aerodynamic force of the air rudder in the unfolding direction, and the force is small, so that the connecting structure of the air rudder is simple, convenient, stable and reliable.

In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.