阅读说明：本技术 适用于导弹的发射箱接口及发射箱 (Launching box interface suitable for guided missile and launching box ) 是由 张晓宏 付丽强 窦怡彬 邵庆 樊浩 许斌 刘广 李建东 张斌 于 2021-01-14 设计创作，主要内容包括：本发明提供了一种适用于导弹的发射箱接口,包括：第一支撑框、第二支撑框、防旋凸台和固弹坑,其中,第一支撑框和第二支撑框分别与导轨面接触；导弹的重量通过第一支撑框和第二支撑框的轴向面积分散到导轨上；防旋凸台与导轨的两侧接触,允许导弹进入发射箱时滚转角不动；固弹坑设置在导弹舱的尾端,允许约束弹道轴向向前的自由度。本发明使得导弹在发射箱内可以通过简单的机械接口进行约束,同时使得导弹的气动外形更优、发射箱支撑结构的简化、受力的优化、并使得发射箱的轮廓更小,适合箱弹小型化的趋势需求。(The invention provides a launching box interface suitable for a missile, which comprises: the device comprises a first supporting frame, a second supporting frame, an anti-rotation boss and a bullet fixing pit, wherein the first supporting frame and the second supporting frame are respectively contacted with a guide rail surface; the weight of the missile is dispersed on the guide rail through the axial areas of the first support frame and the second support frame; the anti-rotation bosses are in contact with the two sides of the guide rail, so that the rolling angle of the missile is allowed to be fixed when the missile enters the launching box; the bullet fixing pit is arranged at the tail end of the bullet guide cabin and allows the degree of freedom of the ballistic trajectory in the axial forward direction to be restrained. The invention leads the missile to be restrained in the launching box through a simple mechanical interface, simultaneously leads the pneumatic appearance of the missile to be better, simplifies the supporting structure of the launching box, optimizes the stress, leads the outline of the launching box to be smaller and is suitable for the trend demand of the miniaturization of the box missile.)

1. A launch box interface adapted for use with a missile, comprising: a first supporting frame (1), a second supporting frame (2), an anti-rotation boss (3) and a bullet fixing pit (4),

the first supporting frame (1) and the second supporting frame (2) are in surface contact with the guide rail (7) respectively;

the weight of the missile is dispersed on the guide rail (7) through the axial areas of the first support frame (1) and the second support frame (2);

the anti-rotation boss (3) is in contact with two sides of the guide rail (7) to allow the missile to have a constant roll angle when entering the launching box;

the bullet fixing pit (4) is arranged at the tail end of the bullet guide cabin and allows the degree of freedom of the constrained trajectory in the axial forward direction.

2. The interface of launch box for missiles according to claim 1, characterised by further comprising a cradle (5), said cradle (5) being in contact with the missile tail end, allowing the missile to be constrained in axial rearward freedom.

3. The interface of launch box for missiles according to claim 1, characterised in that the datum plane of the cradle (5) is in contact with the end face of the missile tail bin end.

4. The missile-adapted launch box interface of claim 1, further comprising a locking bar (6), the locking bar (6) being disposed on an extension of the second support frame (2).

5. The interface of launch box adapted for missiles according to claim 4, characterized in that the head of the lock rod (6) is provided with a hook, and the bullet holding pit (4) hooks the missile by the hook to restrain the missile from axial forward freedom.

6. The launch box interface adapted for missiles according to claim 1, characterized in that said first support frame (1) and said second support frame (2) are 3mm higher than the missile bay.

7. The interface of launch box adapted for missiles as claimed in claim 1, wherein a metal sheet is mounted on the rear wall of the bullet-holding pit (4).

8. The interface of launch box adapted for a missile according to claim 1, characterised in that the anti-rotation boss (3) is a protrusion of the surface of the projectile body at the tail end of the trajectory, and the front end of the anti-rotation boss (3) is provided with a smooth surface.

9. The launch box interface for missiles according to claim 1, characterized in that at least one-half of the surfaces of said first (1) and second (2) support frames are coated with a dry wear-resistant lubricating coating.

10. A launch box comprising the launch box interface for a missile of any one of claims 1 to 9.

Technical Field

The invention relates to the technical field of missile overall design, in particular to a launching box interface and a launching box suitable for a missile.

Background

The restraint of the existing missile in the launching box is mainly characterized in that the transverse degree of freedom of the existing missile is restrained through the interaction between a hanger of the missile and a guide rail in the launching box, the axial backward degree of freedom of the existing missile is restrained through a support at the rear end of the launching box, the axial forward degree of freedom of the existing missile is restrained through a separation socket of the launching box and a sliding block of the existing missile, the transverse degree of freedom of the existing missile is restrained through an auxiliary support at the position where a front missile body can be added to the launching box, all degrees of freedom of the existing missile in the launching box are restrained through the combined action, the restraint interface is generally complex in form, a special movement mechanism and the sliding block are required to interact with each other, the size of the launching box is larger, and the pneumatic resistance of. In order to promote the development of missile technology, the pneumatic appearance of the missile needs to be optimized, the loading capacity of a single-vehicle missile needs to be increased, the requirement of miniaturization of a box missile is provided, and the traditional missile box internal fixed interface form cannot meet the existing requirement.

Through retrieval, patent document CN210793684U discloses a simple conjoined rail frame type cubic satellite launching device, which adopts a push plate with four support legs to limit the degree of freedom of a satellite in a launcher cabin, avoids the disturbance of a spring to the satellite, and improves the launching reliability; two guide rails are designed on each side plate, and the surface of each guide rail is easy to obtain higher shape precision through processing, so that the formed guide rail pair has high precision and reliability. However, the prior art has the defects of complex structure and emphasis on protecting the guide rail of the miniature launching device, and the prior art hardly focuses on the assembly influence caused by the fixed interface form of the missile in the launching box.

Therefore, it is necessary to develop a fixed interface form of the missile in the launching box, optimize the pneumatic appearance of the missile, and meet the requirement of miniaturization of the box missile.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide a launching box interface and a launching box suitable for a guided missile so as to meet the new requirements of box missile miniaturization and guided missile pneumatic shape optimization on box missiles.

According to the invention, the launching box interface suitable for the missile comprises: a first supporting frame, a second supporting frame, an anti-rotation boss and a bullet fixing pit,

the first supporting frame and the second supporting frame are respectively contacted with the guide rail surface;

the weight of the missile is dispersed on the guide rail through the axial areas of the first support frame and the second support frame;

the anti-rotation bosses are in contact with the two sides of the guide rail, so that the rolling angle of the missile is allowed to be fixed when the missile enters the launching box;

the bullet fixing pit is arranged at the tail end of the bullet guide cabin and allows the degree of freedom of the ballistic trajectory in the axial forward direction to be restrained.

Preferably, the missile further comprises a hanging seat, wherein the hanging seat is in contact with the tail end of the missile, and the missile is allowed to have a degree of freedom in the axial backward direction.

Preferably, the reference surface of the lifting seat is in contact with the end surface of the tail end of the missile.

Preferably, the locking device further comprises a locking rod arranged on the extension section of the second supporting frame.

Preferably, the head of the lock rod is provided with a hook, and the bullet holding pit hooks the lock rod to restrain the missile from axially moving forwards through the hook.

Preferably, the first and second support frames are 3mm higher than the missile bay section.

Preferably, a metal sheet is mounted on the rear wall of the bullet-fixing pit.

Preferably, the rotation-preventing boss is a protrusion on the surface of the projectile body at the tail end of the trajectory, and the front end of the rotation-preventing boss is provided with a smooth surface.

Preferably, at least one half of the surfaces of the first support frame and the second support frame are coated with a dry wear-resistant lubricating coating.

According to the invention, the launching box comprises the launching box interface suitable for the missile.

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

1. the invention forms the interface form of the missile fixed in the launching box through the front supporting frame, the rear supporting frame, the anti-rotation boss and the missile fixing pit, and the missile is stably and reliably restrained in the launching box through the simple mechanical interface form and the corresponding interface action of the launching box.

2. According to the invention, by arranging the interface form for fixing the missile in the launching box, the missile can be restrained in the launching box through a simple mechanical interface, and meanwhile, the missile is better in pneumatic appearance, the supporting structure of the launching box is simplified, the stress is optimized, the outline of the launching box is smaller, and the missile launching box is suitable for the trend requirement of miniaturization of the box missile.

3. The invention ensures that the missile can keep the designed position state in the launching box, and finally ensures that the surface of the missile has better pneumatic appearance, the launching box has simpler support for the missile, and the enveloping section of the box is smaller.

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 front view of the present invention;

FIG. 2 is a top view of the present invention;

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

FIG. 4 is a view A-A of the present invention;

fig. 5 is a sectional view of the present invention.

In the figure:

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.

As shown in fig. 1-5, the present invention provides a launch box interface for a missile, comprising: the device comprises a first supporting frame 1, a second supporting frame 2, an anti-rotation boss 3, a bullet fixing pit 4, a hanging seat 5 and a lock rod 6.

The first support frame 1 and the second support frame 2 are in surface contact with the guide rail 7 respectively, the missile is supported, the weight of the missile is dispersed onto the guide rail 7 through the axial areas of the first support frame 1 and the second support frame 2, and the pressure on the guide rail 7 is small; the tail end of the missile is contacted with the hanging seat 5 of the launching box, the degree of freedom of the missile in the axial backward direction can be restrained, and meanwhile, the contact position of the tail end of the missile is used as an indication basis for the missile in the box entering process. The anti-rotation bosses 3 are in contact with two sides of the guide rail 7, so that the rolling freedom of the missile is restrained, the rolling angle of the missile is allowed to be constant when the missile enters the launching box, and the position state of the missile is kept; the bullet fixing pit 4 is positioned at the rear part of the missile cabin section, the rear wall of the bullet fixing pit is hooked through a hook at the head part of a lock rod 6 on the launching box, the degree of freedom of the bullet path in the axial forward direction can be restrained, and therefore the missile is restrained in the launching box together with all the restraint, and the designed position state of the missile is kept.

Furthermore, the missile supports the weight of the whole missile through the contact between the first support frame 1 and the second support frame 2 and the guide rail 7 of the launching box, and the diameter of the missile body of the missile except for one half of the first support frame 1 and the second support frame 2 is smaller than that of the first support frame 1 and the second support frame 2, so that other parts of the missile body cannot contact with the guide rail.

Still further, the first supporting frame 1 and the second supporting frame 2 are higher than the missile cabin section by 3mm, smooth transition is formed between the front and the rear of the first supporting frame and the rear of the second supporting frame, the aerodynamic appearance of the missile is not affected, the first supporting frame and the second supporting frame are mainly located at the front end and the rear end of one cabin section of an engine, the processing amount of one process is the same, the manufacturability is good, the design of the internal shape of the engine is combined, the weight of the engine is not increased, the axial length of the engine can be designed, and the guide rail 7 of the launching box is enabled to be most suitable for the bearing distribution pressure of the missile.

Still further, the missile fixing pit 4 can be combined with a simple lever type hook on the launching box by digging a small pit in the missile tail cabin to pull and restrain the missile to the degree of freedom of the missile in the axial forward direction, the missile fixing pit 4 can be reliably restrained when the missile is overloaded due to transportation impact in the box and missile transportation process, and a high-hardness and high-wear-resistant steel material can be independently installed on the rear wall of the missile fixing pit, so that the force of the launching box hook can be uniformly dispersed on the whole tail cabin of the missile in the large-impact transportation overload process, and the stress condition of the position is obviously improved.

Continuing further, the anti-rotation boss 3 is a small protrusion located on the surface of the projectile body at the tail end of the trajectory, a large smooth surface is arranged at the front end of the anti-rotation boss 3 to improve the aerodynamic appearance of the projectile body, the anti-rotation boss 3 is matched with the guide rail 7 to form one surface of the anti-rotation boss 3, the degree of freedom of the missile in the rotation direction can be restrained by the anti-rotation boss 3 and two opposite surfaces of two sides of the guide rail 7 in contact, meanwhile, the anti-rotation boss 3 plays a guiding role in the missile box entering process, and the box entering process is simplified into a simple thrust mode to enable the missile to enter the box. And the missile is tightly restrained in the box by other restraining interface forms, so that the designed position state of the missile can be kept unchanged.

The working principle is as follows:

in the process of pushing the missile into the launching box, one half of the first supporting frame 1 and the second supporting frame 2 and the guide rail 7 are rubbed to enter in a full range, and at least one half of the surfaces of the first supporting frame 1 and the second supporting frame 2 are coated with a dry wear-resistant lubricating coating, so that the friction in the box entering process is small; after the missile is pushed into the launching box to be in place, the tail end of the last missile cabin section of the missile body collides with a hanging seat 5 of the launching box, so that the missile can be judged to be in place after entering the box; after the guided missile enters the box in place, the launching box rotates the lock rod 6 through a mechanism, so that a head hook of the lock rod 6 can be tightly contacted with the rear wall of the missile fixing pit 4, and the guided missile is restrained in the axial forward and backward directions through the hanging seat 5 and the lock rod 6.

In the case entering and final restraining states of the guided missile, the anti-rotation boss 3 on the surface of the missile body at the tail of the guided missile is in close contact with the guide rail 7 of the launching case and two corresponding contact parts of the guide rail through the surfaces on two sides of the anti-rotation boss 3, so that the guided missile is prevented from rotating due to the mutual contact of the anti-rotation boss 3 and the guide rail 5 in the case entering process, and the guided missile is restrained in the rotation freedom degree at all times in the launching case.

Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, units provided by the present invention as pure computer readable program code, the system and its various devices, modules, units provided by the present invention can be fully implemented by logically programming method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units included in the system for realizing various functions can also be regarded as structures in the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.

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.