CN114111465A

CN114111465A - Aviation projectile body

Info

Publication number: CN114111465A
Application number: CN202111315326.XA
Authority: CN
Inventors: 王巧云; 胡善刚; 刘庆; 陈兴峰; 戴肇鹏; 范开春; 杨锐
Original assignee: General Designing Institute of Hubei Space Technology Academy
Current assignee: General Designing Institute of Hubei Space Technology Academy
Priority date: 2021-11-08
Filing date: 2021-11-08
Publication date: 2022-03-01
Anticipated expiration: 2041-11-08
Also published as: CN114111465B

Abstract

The application relates to the aerospace missile field, in particular to an aerospace projectile, which comprises: a body of the projectile; the end socket is provided with a connecting end used for connecting the projectile body, a first connecting hole penetrates through the connecting end, and the inner wall of the first connecting hole is of a smooth through hole structure; the connecting assembly is arranged between the end and the projectile body and comprises a first connecting part and a connecting rod, the connecting rod is configured to penetrate through the first connecting hole and then fixedly connected with the projectile body, and the first connecting part can be connected with the other side of the connecting end and tightly connected with the connecting end. The stable connection relation between the end head and the projectile body is guaranteed, so that the scheme can be used in the end head connection process of large-size and large-mass tungsten copper infiltrated materials, and relevant blanks in the field are made up.

Description

Aviation projectile body

Technical Field

The application relates to the field of aviation missiles, in particular to an aviation missile body.

Background

The tungsten copper infiltration material is an immiscible special composite material obtained by infiltrating metal copper into a sintered tungsten framework with high melting point and high strength, integrates the advantages of tungsten and copper, has good performances of high temperature resistance, ablation resistance, high strength, high hardness and the like, and is mainly applied to the high-temperature field of aerospace. The nose cone is often used as a missile in aerospace.

However, the tungsten infiltrated copper is a highly brittle material. The large-size and large-mass tungsten copper infiltrated end cannot be directly provided with a threaded hole on the surface and is connected with an elastomer by using a screw, so that stress is easily concentrated on the threaded hole, and the internal threaded structure of the threaded hole is damaged to influence the connection effect. Although the tungsten-infiltrated aircraft tip with the mass of 100kg is very rare at present, the problem of how to effectively connect the projectile body with the tungsten-infiltrated aircraft tip still has great significance to be explored in the field.

Disclosure of Invention

The embodiment of the application provides an aviation projectile body to solve the problem that in the prior art, a large-size and large-mass tungsten copper infiltrated end cannot be effectively connected with the projectile body.

An aerospace projectile, comprising:

a body of the projectile;

the end socket is provided with a connecting end used for connecting the projectile body, a first connecting hole penetrates through the connecting end, and the inner wall of the first connecting hole is of a smooth through hole structure;

the connecting assembly is arranged between the end and the projectile body and comprises a first connecting part and a connecting rod, one end of the connecting rod penetrates through the first connecting hole and then is fixedly connected with the projectile body, and the first connecting part is connected to the other end of the connecting rod and abuts against the connecting end and the projectile body.

In some embodiments, the projectile body is provided with a butt joint end, and the butt joint end is provided with a second connecting hole through which the connecting rod passes; and the number of the first and second electrodes,

the connecting assembly further comprises a second connecting part which is movably connected with the end part of the connecting rod penetrating through the butt joint end and is configured to be capable of moving to abut against the butt joint end.

In some embodiments, the connecting rod slides through the first connecting portion, and a tightening cap is disposed at one end of the connecting rod for driving the first connecting portion to be tightened, a threaded section is disposed at the other end of the connecting rod, and the second connecting portion is a connecting nut in threaded engagement with the threaded section.

In some embodiments, an operating structure is arranged on the end of the connecting rod far away from the abutting cap, so that an operator can pull the connecting rod.

In some embodiments, the first connecting portion is detachably and fixedly connected with the connecting end.

In some embodiments, third connection holes are formed through the connection end and the first connection portion, the third connection holes are in a through hole structure with a smooth inner wall, and a locking screw and a locking nut are arranged between the first connection portion and the connection end and configured such that the locking nut can be connected to the end portion of the locking screw passing through the first connection portion and the connection end to cooperate with a nut of the locking nut to clamp and fixedly connect the first connection portion.

In some embodiments, a first cavity is formed in the tip, the connection end is formed between the first cavity and the end surface of the tip, and the first connection portion is disposed in the first cavity;

the projectile body is internally provided with a second cavity, the butt joint end is formed between the second cavity and the end face of the projectile body, and the connecting rod body is connected with the second connecting portion in the second cavity.

In some embodiments, at least two sets of the first connecting portion and the second connecting portion are disposed correspondingly and respectively located at two sides of the first cavity and the second cavity.

In some embodiments, the first cavity has a cavity opening on an inner wall of a side close to the end surface, and the cavity opening penetrates through the end surface and has an area smaller than that of the inner wall of the side of the first cavity.

In some embodiments, a second cavity extending inward is formed in an end surface of the projectile body, and the connection rod body is connected with the second connection portion in the second cavity.

In some embodiments, the tip is made entirely of a copper tungsten infiltrated material.

The beneficial effect that technical scheme that this application provided brought includes:

the embodiment of the application provides an aviation projectile body, because the connecting rod passes behind the link through first connecting hole with projectile body fixed connection to utilize first connecting portion to support tightly in the link opposite side after being connected with the connecting rod other end, realize fixed connection projectile body and end. Only need set up the through-hole that the inner wall is the plain noodles on the end when end and body of bullet body coupling, and then need not to carry out the seting up of screw hole on the end, stress concentration when having avoided the end of jumbo size big quality and body of bullet to be connected is on the helicitic texture, and causes the condition of tungsten copper infiltration material damage, and because first connecting portion have increased the biography power area between end and the body of bullet body, be convenient for transmit load, guarantee end and body of bullet body have stable relation of connection, make this scheme can be used to the end connection in-process of jumbo size big quality tungsten copper infiltration material, compensate relevant blank in this field.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

FIG. 1 is a schematic overall structure diagram provided in an embodiment of the present application;

FIG. 2 is a cross-sectional view of a connecting rod structure provided in an embodiment of the present application;

FIG. 3 is a cross-sectional view of a locking screw structure provided in an embodiment of the present application;

fig. 4 is a schematic structural diagram of a first connection portion according to an embodiment of the present application.

In the figure:

1. a body of the projectile; 10. a butt joint end; 100. a second connection hole; 11. a second cavity;

2. a tip; 20. a connecting end; 200. a first connection hole; 201. a third connection hole; 202. sinking a groove; 21. a first cavity;

3. a connecting assembly; 30. a first connection portion; 300. sinking the nut; 301. perforating; 31. a connecting rod; 310. abutting the cap; 311. a threaded segment; 312. threading holes; 32. a second connecting portion;

4. a locking screw; 40. and locking the nut.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

Accordingly, embodiments of the present application provide an aerospace projectile that addresses the above-mentioned problems.

Referring to fig. 1 and 2, an aerospace projectile includes:

an elastomer body 1;

the end head 2 is provided with a connecting end 20 used for connecting the projectile body 1, a first connecting hole 200 penetrates through the connecting end 20, and the inner wall of the first connecting hole 200 is of a through hole structure with a smooth surface;

coupling assembling 3, it is located end 2 with between the body of bullet body 1, including first connecting portion 30 and connecting rod 31, connecting rod 31 one end passes behind first connecting hole 200 with body of bullet body 1 fixed connection, just first connecting portion 30 connect in the connecting rod 31 other end, and support tightly link 20 with body of bullet body 1.

Wherein, connecting rod 31 passes through connecting end 20 through first connecting hole 200 after with body 1 fixed connection to utilize first connecting portion 30 to support tightly in connecting end 20 opposite side after being connected with the connecting rod 31 other end, realize fixed connection body 1 and end 2.

Set up like this, only need set up the through-hole that the inner wall is the plain noodles on end 2 when realizing that end 2 is connected with projectile body 1, and then need not to carry out the seting up of screw hole on end 2, reduce the complexity of relevant connection structure on end 2, stress concentration is on screw thread structure and probably causes the condition of damage when having avoided end 2 and projectile body to be connected, and because first connecting portion 30 has increased the biography power area between end 2 and projectile body 1, be convenient for transmit load, ensure the stable connection between end 2 and projectile body 1, make this scheme can be used to 2 connection processes of end of jumbo size large-mass quality tungsten copper infiltration material.

Referring to fig. 2, optionally, a butt end 10 is disposed on the projectile body 1, and a second connection hole 100 through which the connection rod 31 passes is disposed on the butt end 10; and the connecting assembly 3 further includes a second connecting portion 32 movably connected to the end of the connecting rod 31 passing through the docking end 10 and configured to move to abut against the docking end 10.

Referring to fig. 4, a plurality of connecting rods 31 may be disposed between the first connecting portion 30 and the second connecting portion 32, in this embodiment, three connecting rods 31 are disposed between the first connecting portion 30 and the second connecting portion 32, so as to further improve the connection stability between the tip 2 and the projectile body 1.

Set up like this, operating personnel can connect second connecting portion 32 connecting rod 31 after connecting rod 31 passes butt joint end 10 through second connecting hole 100 to adjust its position on connecting rod 31, in order to support tight butt joint end 10, realize that the first connecting portion 30 of the cooperation connecting rod 31 other end supports tightly end 2 and body of bullet 1 from both sides. Finally, the end head 2 and the elastic body 1 can be quickly and fixedly connected, and the end head 2 and the elastic body 1 are provided with larger force transmission areas for load transmission.

Referring to fig. 2, optionally, the connecting rod 31 slides through the first connecting portion 30, and is provided with a tightening cap 310 at one end for tightening and driving the first connecting portion 30, the other end of the connecting rod 31 is provided with a threaded section 311, and the second connecting portion 32 is a connecting nut in threaded fit with the threaded section 311.

The first connecting portion 30 is provided with a nut sinking platform 300 corresponding to the connecting rod 31, a through hole 301 penetrating through the first connecting portion 30 is formed in the bottom of the nut sinking platform 300, so that when the rod body of the connecting rod 31 penetrates through the first connecting portion 30, the abutting cap 310 of the connecting rod 31 can abut against the nut sinking platform 300, and further when the connecting rod 31 penetrates through the first connecting portion 30, the abutting cap 310 tightly abuts against one side of the first connecting portion 30, which is far away from the connecting end 20.

The connecting nut as the second connecting portion 32 can be screwed on the threaded section 311 of the connecting rod 31 extending out of the butt joint end 10 after the connecting rod 31 passes through the first connecting portion 30, the connecting end 20 and the butt joint end 10, and tightly abuts against the butt joint end 10, so that the first connecting portion 30 is matched to complete the fixed connection between the end head 2 and the projectile body 1.

Meanwhile, in order to facilitate the rotating assembly of the connecting nut as the second connecting portion 32 on the connecting rod 31, the abutting cap 310 of the connecting rod 31 may be disposed in a polygonal shape, and the nut platform 300 is matched with the abutting cap 310 to be disposed in a polygonal shape, so as to effectively limit the rotation of the connecting rod 31, thereby facilitating the assembly of the connecting nut.

Referring to fig. 2, optionally, an operating structure is provided on an end of the connecting rod 31 far from the tightening cap 310, so that an operator can pull the connecting rod 31.

Wherein, the operation structure specifically runs through the threading hole 312 arranged on the rod body at the end part of the connecting rod 31 along the radial direction in the embodiment, and then when actually assembling the second connecting part 32, the rope body can be utilized to pass through the threading hole 312, so that the operator can quickly tighten the connecting rod 31 by holding the rope body. When the connecting nut as the second connecting portion 32 is rotated, the connecting rod 31 is prevented from moving in the axial direction, which may cause the first connecting portion 30 and the second connecting portion 32 at the two ends of the connecting rod 31 to be unable to quickly clamp the connecting end 20 of the end 2 and the butt end 10 of the projectile body 1.

In addition, in other embodiments, the operating structure may be any form of pulling ring, pulling rod, or slot for inserting an external insertion rod, which is disposed on the end surface of the connecting rod 31.

Optionally, the first connecting portion 30 is detachably and fixedly connected with the connecting end 20.

By such arrangement, the first connecting portion 30 can be firstly fixedly connected to one side of the connecting end 20, and then the connecting rod 31 is installed by only controlling the abutting cap 310 to abut against the first connecting portion 30, so that a moving space possibly existing between the abutting cap 310 and the connecting end 20 of the first connecting portion 30 is avoided, and the stability of the first connecting portion 30 when abutting against the connecting end 20 is further enhanced.

Referring to fig. 3, optionally, third connection holes 201 are formed through the connection end 20 and the first connection portion 30, the third connection holes 201 are in a through hole structure with smooth inner walls, a locking screw 4 and a locking nut 40 are disposed between the first connection portion 30 and the connection end 20, and the locking nut 40 is configured to be connectable to an end portion of the locking screw 4 passing through the first connection portion 30 and the connection end 20 so as to cooperate with a nut of the locking nut 40 to clamp and fixedly connect the first connection portion 30.

Wherein, link 20 just offers the heavy groove 202 that supplies the nut of locking screw 4 to place on the terminal surface of body of bullet 1, and heavy groove 202 is the through-hole setting that the diameter is greater than third connecting hole 201, and third connecting hole 201 sets up in heavy groove 202 bottom, and then does not influence link 20 and body of bullet 1's conflict behind locking screw 4 wears to establish link 20 and connects first connecting portion 30 and be connected. And because the connection of first connecting portion 30 is for supporting tightly the connection from both ends with the help of locking screw 4 equally, and then avoid adopting the mode of screw hole to connect for third connecting hole 201 can directly adopt the through-hole structure, and when finally making first connecting portion 30 install on link 20 and pass power, both can have better stability.

Set up like this, realize the removable fixed connection of link 20 and first connecting portion 30, and then can install first connecting portion 30 and connecting rod 31 in link 20 one side in advance, be convenient for follow-up when fixed connection body of bullet 1 and end 2, operating personnel operates second connecting portion 32 and connects the action bars and support and tightly can realize fixed connection body of bullet 1 and end 2 behind the butt joint end 10.

Referring to fig. 2, optionally, a first cavity 21 is disposed in the tip 2, the connecting end 20 is formed between the first cavity 21 and the end surface of the tip 2, and the first connecting portion 30 is disposed in the first cavity 21;

the projectile body 1 is internally provided with a second cavity 11, the butt joint end 10 is formed between the second cavity 11 and the end face of the projectile body 1, and the connecting rod 31 is connected with the second connecting portion 32 in the second cavity 11.

Set up like this, first connecting portion 30, connecting rod 31, second connecting portion 32 isotructure all are located end 2 or projectile body 1 inside, make it avoid changing the shape structure of end 2 and projectile body 1 outer wall, avoid leading to changing the flight stress state of end 2 and projectile body 1 because it sets up in the outside, and then influence the guidance of whole guided missile or aircraft, flight process.

Optionally, at least two sets of the first connecting portion 30 and the second connecting portion 32 are correspondingly disposed, and are respectively located at two sides of the first cavity 21 and the second cavity 11.

Wherein, the two first limiting parts and the second limiting part are respectively clung to the inner walls of two sides of the first cavity 21.

Set up like this, realize further increase end 2 and the body of bullet 1 between the stability of being connected to improve the biography power area between the two, but make the effective transmission load when using, ensure end 2 and body of bullet 1 smooth use.

Referring to fig. 2, optionally, a cavity is formed in the first cavity 21 on an inner wall of a side close to the end surface of the tip 2, and the cavity penetrates through the end surface of the tip 2 and has an area smaller than that of the inner wall of the side of the first cavity 21.

Set up like this, realize being convenient for operating personnel and put into first cavity 21 with structures such as connecting rod 31, first connecting portion 30 and install, also make first cavity 21 have the accent simultaneously, can form the link 20 that supplies connecting rod 31 to wear to establish, the installation of connecting rod 31 and first connecting portion 30 between the terminal surface of first cavity 21 and end 2.

Optionally, the tip 2 is made of a tungsten-infiltrated copper material as a whole.

It is worth to be noted that when the length of the end 2 made of the tungsten copper infiltrated material is not less than 300mm and the mass is not less than 50kg, a stable connection cannot be formed by a conventional method of directly forming a threaded hole on the end 2 for connection, and at this time, the scheme provided by the present application needs to be adopted for connecting the large-size large-mass end 2 and the projectile body 1. Furthermore, it will be appreciated that the solution provided by the present application can still be used when the length of the head 2 is less than 300mm and the mass is less than 50kg, and is more stable than the conventional way of directly using threaded hole bolt connection.

In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

It is noted that, in the present application, relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.

The above description is merely exemplary of the present application and is presented to enable those skilled in the art to understand and practice the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An aerospace projectile, comprising:

a body (1);

the end head (2) is provided with a connecting end (20) used for being connected with the projectile body (1), a first connecting hole (200) penetrates through the connecting end (20), and the inner wall of the first connecting hole (200) is of a through hole structure with a smooth surface;

coupling assembling (3), its locate end (2) with between body of bullet body (1), including first connecting portion (30) and connecting rod (31), connecting rod (31) one end is passed behind first connecting hole (200) with body of bullet body (1) fixed connection, just first connecting portion (30) connect in connecting rod (31) the other end, and support tightly link (20) with body of bullet body (1).

2. The aerial projectile of claim 1, wherein the projectile body (1) is provided with a butt end (10), and the butt end (10) is provided with a second connecting hole (100) for the connecting rod (31) to pass through; and the number of the first and second electrodes,

the connecting assembly (3) further comprises a second connecting portion (32) which is movably connected to the end portion of the connecting rod (31) penetrating through the butt joint end (10) and is configured to be movable to abut against the butt joint end (10).

3. The aerospace projectile of claim 2, wherein the connecting rod (31) slides through the first connection portion (30) and has a retaining cap (310) at one end for retaining and driving the first connection portion (30), the connecting rod (31) has a threaded section (311) at the other end, and the second connection portion (32) is a connecting nut that is threaded to the threaded section (311).

4. The aerial projectile of claim 3, wherein the end of said connecting rod (31) remote from said abutment cap (310) is provided with an operating structure for the operator to pull said connecting rod (31).

5. An aerospace projectile according to claim 2, wherein the first connection portion (30) is removably fixedly connected to the connection end (20).

6. The aerial projectile body as claimed in claim 5, wherein a third connecting hole (201) is formed through each of the connecting end (20) and the first connecting portion (30), the third connecting hole (201) has a through hole structure with a smooth inner wall, a locking screw (4) and a locking nut (40) are disposed between the first connecting portion (30) and the connecting end (20), and the locking nut (40) is configured to be connectable to an end portion of the locking screw (4) passing through the first connecting portion (30) and the connecting end (20) so as to cooperate with a nut of the locking nut (40) to clamp and fixedly connect the first connecting portion (30).

7. The aerial projectile of claim 1, wherein a first cavity (21) is provided in said tip (2), said connection end (20) being formed between said first cavity (21) and an end surface of said tip (2), said first connection portion (30) being provided in said first cavity (21);

be equipped with second cavity (11) in projectile body (1), second cavity (11) with form between projectile body (1) the terminal surface butt joint end (10), connecting rod (31) body with second connecting portion (32) are in connect in second cavity (11).

8. The aerial projectile of claim 7, wherein said first and second connecting portions (30, 32) are provided in at least two groups, respectively located on both sides of said first and second cavities (21, 11).

9. The aerospace projectile of claim 7, wherein the first cavity (21) has a port on an inner wall of a side thereof adjacent to the end face of the tip (2), the port extending through the end face of the tip (2) and having a smaller area than the inner wall of the side of the first cavity (21).

10. Aeronautical projectile according to any of claims 1 to 9, characterized in that the head (2) is made entirely of a tungsten-infiltrated copper material.