CN112985189A

CN112985189A - Projectile body structure for improving pneumatic stability of non-rotating projectile

Info

Publication number: CN112985189A
Application number: CN201911387904.3A
Authority: CN
Inventors: 沈剑; 祝青钰; 王晓光
Original assignee: North University of China
Current assignee: North University of China
Priority date: 2019-12-18
Filing date: 2019-12-18
Publication date: 2021-06-18

Abstract

The invention relates to a projectile body structure for improving the aerodynamic stability of a non-rotating projectile, which comprises a projectile head, wherein the projectile head is in the shape of a conventional bullet, the middle and rear sections of the projectile head are connected with a projectile wing part, the projectile wing is in a projectile body embedded form, the projectile wing comprises four wing surfaces, the wing surfaces are separated by four transition steps, each transition step consists of two sections of conical surfaces, each conical surface comprises a section of small-cone conical surface and a section of large-cone conical surface, the rear part of each large-cone conical surface is connected with a cylindrical part of the projectile body, and the diameter of the cylindrical part is the diameter of the projectile body. Aiming at the problem of insufficient stable reserve of non-rotating and hypersonic launching projectiles, the invention considers the limitation of a launching system on the size of the projectiles, adopts an embedded mode to form four projectile wings, and guides the air flow through transition steps, so that the static stability of the projectile body is improved and the flight stability is ensured under the hypersonic flight condition of the projectiles.

Description

Projectile body structure for improving pneumatic stability of non-rotating projectile

Technical Field

The invention relates to the field of projectile pneumatic structures, in particular to a projectile body structure for improving the pneumatic stability of a non-rotating projectile.

Background

At present, the requirements of three-dimensional warfare on space and time are higher and higher, the requirements on the range and the precision of a weapon system are more and more urgent, and meanwhile, the response speed and the shooting speed of the weapon system are required to be higher. The higher initial speed of the projectile means that the range is farther, and on the premise of a certain range, the higher initial speed means shorter flight time and greater power, so that the hit rate and damage degree of the projectile on a target can be improved.

With the emergence of launching technologies such as electromagnetic coil acceleration, electromagnetic orbit energy and the like, the initial speed of a projectile muzzle can reach more than 2000m/s and even higher. If the gun is launched at hypersonic speed, the stable reserve capacity of the traditional pneumatic bullet is seriously insufficient, and the requirement of stable flight cannot be met. Therefore, there is a need to develop a bullet with a good aerodynamic profile to adapt to more advanced ultra high speed launch platforms.

The appearance of a projectile body structure that improves the aerodynamic stability of a non-rotating projectile can improve the static stability of the projectile, but the aerodynamic stability of the non-rotating projectile at the present stage has many disadvantages, such as low static stability, instability after leaving the muzzle, landing, poor shooting accuracy, and the like.

Disclosure of Invention

The invention aims to provide a projectile body structure for improving the pneumatic stability of a non-rotating projectile so as to solve the problems of unstable flight and small shooting precision of the existing hypersonic projectile.

In order to achieve the purpose, the invention provides the following technical scheme: the utility model provides an improve projectile body structure of non-rotation shot aerodynamic stability, includes the warhead, the warhead is conventional bullet warhead shape, back end connects the warwing part in the warhead, the warwing is the embedded form of projectile body, the warwing contains four wings, separate by four transition steps between the wing, the transition step comprises two sections conical surfaces, the conical surface includes one section little cone-shaped pyramid face and one section big cone-shaped pyramid face, connect projectile body cylinder portion behind the big cone-shaped pyramid face, cylinder portion diameter is projectile body diameter.

Preferably, the bullet body consists of the bullet head, the bullet wing, the small taper angle surface of the transition step, the large taper angle surface of the transition step and the cylindrical part of the bullet body.

Preferably, the warhead shape is identical to the size and shape of the front section of a conventional warhead.

Preferably, the missile wing is provided with four missile wings, the four missile wings are uniformly distributed on the missile body, and the wing chord of the missile wing is not higher than the outer contour of the missile body.

Preferably, a transition step structure is arranged between the missile wings.

Preferably, the missile wing and the transition step are connected with the cylindrical part of the missile body.

Compared with the prior art, the invention has the beneficial effects that: for new launching mechanisms (e.g., electromagnetic launch), the projectile is not typically given an initial rotational velocity, which requires stabilization of the projectile with the projectile wings. The special missile wing structure can realize molding by adopting a simple process under the condition of not changing the prior missile body. When the projectile flies at hypersonic speed in the air, the airflow can smoothly pass through the transition step structure, and the four projectile wings ensure that the projectile body does not have instability phenomena such as rolling and the like in the air.

Drawings

FIG. 1 is a schematic structural diagram of the present invention.

In the figure: 1-warhead, 2-warwing, 3-1-transition step small cone angle surface, 3-2-transition step large cone angle surface and 4-bomb cylindrical portion.

Detailed Description

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

Referring to fig. 1, in an embodiment of the present invention, a projectile structure for improving aerodynamic stability of a non-rotating projectile includes a projectile head 1, the projectile head 1 is in a conventional projectile head shape, a rear section of the projectile head 1 is connected to a portion of a projectile wing 2, the projectile wing 2 is in a projectile body embedded form, the projectile wing 2 includes four wing pieces, the wing pieces are separated by four transition steps, the transition steps are composed of two sections of conical surfaces, the conical surfaces include a section of small cone-shaped conical surface 3-1 and a section of large cone-shaped conical surface 3-2, the large cone-shaped conical surface is connected to a cylindrical portion 4 of the projectile body, and the diameter of the cylindrical portion 4 is the diameter of the projectile body.

The working principle of the invention is as follows: when the apparatus is in use, a projectile is fired (without self-rotation) by a firing device and after the projectile exits the muzzle, a stream of air flows over the projectile at a hypersonic velocity. The air flow flows through the surfaces of the transition steps to form a low-pressure area on the step surfaces, and the four transition steps and the wing surfaces are stressed uniformly, so that the stability of the projectile body under the action of air resistance can be ensured, and the projectile body is not overturned and unstabilized.

It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Claims

1. The utility model provides an improve projectile body structure of non-rotatory shot aerodynamic stability, includes warhead (1), its characterized in that: the bullet head (1) is in a conventional bullet head shape, the middle and rear sections of the bullet head (1) are connected with the part of the bullet wing (2), the bullet wing (2) is in a bullet body embedded form, the bullet wing (2) comprises four wing pieces, the wing pieces are separated by four transition steps, each transition step consists of two sections of conical surfaces, the rear part of the large-cone conical surface is connected with the cylindrical part (4) of the bullet body, and the diameter of the cylindrical part (4) is the diameter of the bullet body.

2. A projectile body structure for enhancing the aerodynamic stability of a non-rotating projectile as defined in claim 1, wherein: the wingspan of the missile wing (2) does not exceed the outer surface of the arc-shaped part of the missile head (1).

3. A projectile body structure for enhancing the aerodynamic stability of a non-rotating projectile as defined in claim 1, wherein: four wing surfaces of the missile wing (2) are symmetrically arranged, and adjacent wing surfaces are perpendicular to each other.

4. A projectile body structure for enhancing the aerodynamic stability of a non-rotating projectile as defined in claim 1, wherein: the four wing surfaces of the missile wing (2) are mutually isolated through transition steps.

5. A projectile body structure for enhancing the aerodynamic stability of a non-rotating projectile as defined in claim 1, wherein: the transition step is composed of two sections of conical surfaces, and the conical surfaces comprise a section of small cone-shaped pyramid surface (3-1) and a section of large cone-shaped pyramid surface (3-2).

6. A projectile body structure for enhancing the aerodynamic stability of a non-rotating projectile as defined in claim 1, wherein: the missile wing (2) and the transition step play roles of separating a wing surface, guiding air and stabilizing a missile body. The air flow flows through the conical surface of the transition step, a low-pressure area is formed in the conical surface area, the four transition steps and the wing surfaces are stressed uniformly, and the stability of the projectile body under the action of air resistance can be ensured without overturning instability.