CN211346558U

CN211346558U - Miniature rocket bomb

Info

Publication number: CN211346558U
Application number: CN201921422234.XU
Authority: CN
Inventors: 黄春光; 邓宏彬; 周惠民; 文颀; 彭腾; 熊镐; 刘野; 顾虎; 周志昊
Original assignee: Wuhan Honghai Xingmin Technology Co ltd; Beijing Hongda Hechuang Defense Technology Research Institute Co ltd; Beijing Institute of Technology BIT
Current assignee: Wuhan Honghai Xingmin Technology Co ltd; Beijing Hongda Hechuang Defense Technology Research Institute Co ltd; Beijing Institute of Technology BIT
Priority date: 2019-08-29
Filing date: 2019-08-29
Publication date: 2020-08-25
Anticipated expiration: 2029-08-29

Abstract

The utility model belongs to the technical field of rocket projectile technique and specifically relates to a miniature rocket projectile, including tail-hood, fin, rocket engine, warhead, fuze cabin, the fuze cabin passes through the screw and installs on warhead top along projectile body axial fixity, rocket engine passes through the screw and installs in warhead bottom along projectile body axial fixity, fin fixed mounting is on rocket engine afterbody shell, rocket engine afterbody fixed mounting has the tail-hood, the fin is taken in the back through the tail-hood and is hugged closely and set up with rocket engine shell. The utility model has the advantages of small size, light weight and small impact on the platform during launching.

Description

Miniature rocket bomb

Technical Field

The utility model relates to a rocket projectile technical field especially relates to a miniature rocket projectile.

Background

In recent years, micro rotor unmanned aerial vehicles are receiving more and more attention from military, armed police and special public security combat troops due to the characteristics of small volume, low cost, low requirement on take-off and landing sites, convenient carrying and use and vertical take-off, landing and hovering capabilities, and are widely used for executing light-weight tasks such as aerial reconnaissance, field monitoring and the like, wherein an integrated weapon station is equipped for the micro rotor unmanned aerial vehicles, so that the micro rotor unmanned aerial vehicles are utilized to execute air-to-ground reconnaissance and attack tasks in low-altitude complex environments, and the micro rotor unmanned aerial vehicles are one of important development directions.

Due to the weak impact resistance of the micro rotor unmanned aerial vehicle, the load capacity is very limited (generally not more than 5 kg). The traditional lethal and non-lethal ammunition has the advantages of large overload, short firing range, high quality, large volume, single damage mode, high cost of accurately guided ammunition and difficulty in realizing miniaturization, so that the traditional lethal and non-lethal ammunition is not suitable for a miniature unmanned aerial vehicle platform weapon station, and the miniature ammunition with small size, light weight and small impact on a platform during firing needs to be designed to meet the requirement.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving the problem that the size is large, the weight is large, and the impact on the platform is large during the launching process, thereby providing a miniature rocket projectile.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

the design is a miniature rocket projectile, which comprises a tail cover, a tail wing, a rocket engine, a fighting part and a fuze cabin and is characterized in that the fuze cabin is fixedly installed at the top end of the fighting part along the axial direction of the projectile body through screws, the rocket engine is fixedly installed at the bottom end of the fighting part along the axial direction of the projectile body through screws, the tail wing is fixedly installed on a shell at the tail part of the rocket engine, the tail cover is fixedly installed at the tail part of the rocket engine, and the tail wing is tightly attached to the shell of the rocket engine after being accommodated through the tail cover.

Preferably, the empennage comprises a connecting shaft, a plurality of rolling arc wings and torsion springs, the four sections of rolling arc wings are evenly arranged on a rocket engine shell in an X shape, the root of each rolling arc wing is provided with the connecting shaft, the rolling arc wings can be rotatably arranged on the connecting shaft, each section of rolling arc wing is fixedly arranged on a fixing ring of the rocket engine shell in a hole shaft connection mode, and each connecting shaft is provided with one torsion spring in a compression state.

Preferably, the warhead can be a plurality of types of warheads such as armor piercing, explosion killing, detonation, lacrimation, smoking and the like.

The utility model provides a pair of miniature rocket projectile, beneficial effect lies in: the whole bomb adopts a modular design, and can be quickly installed without tools. The rocket projectile has small size, light weight and small impact on the platform during launching, and can be provided with various warheads such as armor piercing, explosion killing, knocking, lacrimation, fuming and the like.

Drawings

Fig. 1 is a schematic view of the overall structure of a miniature rocket projectile according to the present invention;

fig. 2 is a schematic view of the internal structure of a micro rocket projectile according to the present invention;

fig. 3 is the utility model provides a tail wing mounting structure schematic diagram of miniature rocket projectile.

In the figure: tail cover 81, tail wing 82, rocket motor 83, warhead 84, fuze cabin 85, connecting shaft 86, rolling arc wing 87 and torsion spring 88.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.

Referring to fig. 1-3, a micro rocket projectile comprises a tail cover 81, a tail wing 82, a rocket motor 83, a warhead 84 and a fuze cabin 85, and each component is designed in a modularized manner, so that the utility model can replace each component according to the use requirement to realize different striking effects; when a certain component is failed, the components of other rocket projectiles can be directly replaced, and meanwhile, in the subsequent improvement and upgrade process, the independent components can be upgraded, so that the improvement is more flexible, and various models which are suitable for different combat requirements can be derived. The warhead 84 can be a plurality of types of warheads such as armor piercing, explosion killing, knocking, lacrimation, fuming and the like, so that different fighting requirements can be met.

Fuze cabin 85 is through the screw along projectile body axial fixity installation on warhead 84 top, rocket engine 83 passes through the screw along projectile body axial fixity installation in warhead 84 bottom, fin 82 fixed mounting is on rocket engine 83 afterbody shell, through the fix with screw for the dismantlement of whole rocket is all convenient more quick with the installation, when the combat demand that faces the difference, the warhead of the different models of change that can be quick more, thereby has improved combat efficiency greatly. The tail wing 82 comprises a connecting shaft 86, rolling arc wings 87 and torsion springs 88, wherein four sections of the rolling arc wings 87 are uniformly arranged on the rocket engine 83 shell in an X shape, the root of each rolling arc wing 87 is provided with the connecting shaft 86, the rolling arc wings 87 can be rotatably arranged on the connecting shaft 86, each section of the rolling arc wings 87 is fixedly arranged on a fixing ring of the rocket engine 83 shell in a hole shaft connection mode, each connecting shaft 86 is provided with one torsion spring 88 in a compression state, and the torsion springs 88 are special torsion springs and can provide torque rotating and moving along the axis. A tail cover 81 is fixedly arranged at the tail part of the rocket motor 83, and the tail wing 82 is closely attached to the shell of the rocket motor 83 after being accommodated by the tail cover 81.

Before the rocket projectile is launched, all the winding wings 87 are tightly attached to the rocket motor 83 casing, the torsion spring 88 is compressed, and the winding wings 87 are accommodated outside by the tail cover 81 to prevent the winding wings from being unfolded. After the rocket projectile is launched, the rocket engine 83 sprays airflow to push the tail cover 81 open, the rolling arc wings 87 are released, the rolling arc wings 87 are unfolded to reach the maximum wingspan position under the action of the torsion spring 88, and at the moment, the torsion spring 88 pushes the rolling arc wings into the clamping grooves for fixing.

The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.

Claims

1. The utility model provides a miniature rocket projectile, includes tail-hood (81), fin (82), rocket engine (83), warhead (84), fuze cabin (85), its characterized in that, fuze cabin (85) are installed on warhead (84) top along projectile body axial fixity through the screw, rocket engine (83) are installed in warhead (84) bottom along projectile body axial fixity through the screw, fin (82) fixed mounting is on rocket engine (83) afterbody shell, rocket engine (83) afterbody fixed mounting has tail-hood (81), fin (82) are taken in the back through tail-hood (81) and are hugged closely and rocket engine (83) shell setting.

2. The micro rocket projectile according to claim 1, wherein the tail wing (82) comprises a connecting shaft (86), a plurality of arc-rolling wings (87) and torsion springs (88), the four arc-rolling wings (87) are uniformly arranged on the rocket engine (83) shell in an X shape, the root of each arc-rolling wing (87) wing is provided with the connecting shaft (86), the arc-rolling wings (87) can be rotatably installed on the connecting shaft (86), each arc-rolling wing (87) is fixedly installed on a fixing ring of the rocket engine (83) shell in a hole-shaft connection mode, and each connecting shaft (86) is provided with one torsion spring (88) in a compression state.

3. The micro-rocket projectile of claim 1 wherein said warhead (84) is of the type that can be armor piercing, blast, detonation, tear, smoke.