CN112444163A

CN112444163A - Resistance stabilized water-entering projectile

Info

Publication number: CN112444163A
Application number: CN201910829657.1A
Authority: CN
Inventors: 赵子杰; 曹丁楠
Original assignee: Nanjing University of Science and Technology
Current assignee: Nanjing University of Science and Technology
Priority date: 2019-09-03
Filing date: 2019-09-03
Publication date: 2021-03-05

Abstract

The invention discloses a resistance-stabilized water-entering missile, which comprises a warhead (1), a connection mechanism for delayed separation and a projectile tail wing (5); shortly after firing, the thermally reactive material of the coiled spring-like portion is ignited. The tail fin of the projectile enables the projectile to have better aerodynamic properties before it enters the water. Before entering water, the thermal reaction material is burnt, so that the bullet head 1 of the projectile body is unhooked from the whole tail wing, and the bullet head 1 of the projectile body is ensured not to have the tail wing when entering water, thereby ensuring the stability of formation of supercavitation. The invention has better aerodynamic characteristics, ensures the stability of forming supercavity when entering water, and ensures that the empennage does not interfere the stability of forming supercavity.

Description

Resistance stabilized water-entering projectile

Technical Field

The invention relates to the technical field of weapon engineering, in particular to a projectile stable in water by resistance from air to water.

Background

The research on water entry problems is subject to a wide range of problems, with important problems focused on the weapon field, such as the development of aerial torpedoes, deep water bombs, and supercavity projectiles. The process of entry into the water is an important link in the transition of such weapons from air ballistic trajectory to underwater ballistic trajectory. The process has the characteristics of strong instantaneous, unsteady and high load, and the like, and has great influence on the ballistic characteristics and the structural characteristics of the weapon. The existing water-entering projectile has unstable resistance in the air flight stage before entering water.

Projectiles having fins or similar resistive stabilizing elements are known to have better aerodynamic stability, but are less stable in the form of cavitation bubbles formed after entry into water. During the penetration of the projectile into the water, drag stabilizing elements of the type like tail fins can cause instability during penetration of the projectile into the water. Especially in the case of projectiles entering water at low angles of incidence, the resistive stabilizing elements eventually lead to self-destruction of the projectile. Accordingly, there is a need for improvements in resistance stabilized water entry projectiles that employ arrangements whereby the resistance stabilizing elements are disengaged from the projectile prior to entry into the water.

Disclosure of Invention

It is an object of the present invention to provide an air-to-water drag stabilized water entry projectile having fins or similar drag stabilizing elements, which has good aerodynamic stability and which can be detached from the projectile prior to entry into the water to effect stable formation of cavitation bubbles.

The technical solution for realizing the purpose of the invention is as follows: a resistance stabilized water-entering missile comprises a warhead, a connection mechanism which is separated in a delayed manner and a projectile tail wing;

the warhead consists of a cavitator, a fuse, a warhead part and a semi-hollow cylindrical barrel at the tail part of the warhead part; the outer wall of the semi-hollow cylindrical barrel at the tail part is sleeved with an empennage outer barrel, and a time delay fixing mechanism for fixing and separating the empennage is inserted into the barrel wall; a hole is formed in the semi-hollow cylindrical barrel wall at the tail part of the warhead part, close to the warhead part, and used for inserting a hook at the inner side of the spring-shaped delay fixing mechanism;

the connecting mechanism for delayed separation consists of a cylindrical core, a spring-shaped delay mechanism coated with a thermal reaction material and a strip-shaped circular ring lengthening part; the spring-shaped time delay mechanism is sleeved on the cylindrical copper core, and the spring-shaped time delay mechanism and the cylindrical copper core are sleeved with the elongated part and then are simultaneously inserted into the semi-hollow cylindrical barrel at the tail part of the warhead; hooks for fixing are arranged at two ends of the spring-shaped time delay mechanism; the inner hook is inserted into a hole on the semi-hollow cylindrical barrel; the outer hook extends out for fixing the empennage part sleeved on the outer wall of the cylindrical barrel.

The projectile tail wing part is divided into a hollow cylindrical barrel, and three empennages are equally distributed on the outer wall of the cylindrical barrel in three parts; the projectile tail fin outer cylinder is sleeved on the semi-hollow outer cylinder wall at the rear end of the warhead part and is fixed by a time delay connection mechanism from a small hole in the outer cylinder wall.

Compared with the prior art, the invention has the following remarkable advantages: the spring-shaped time delay mechanism part of the invention is equivalent to a time delay mechanism, which ensures that the tail wing is connected with the projectile in the stage of flying in the air after launching, but the tail wing is separated from the projectile body in the stage of entering water, thereby not only having better aerodynamic characteristics, but also ensuring the stability of forming supercavity in water, and leading the tail wing not to interfere the stability of forming the supercavity.

Drawings

Figure 1 is a schematic diagram of the overall construction of a resistance stabilized water projectile.

Figure 2 is a schematic view of a time delay attachment mechanism coated with a thermally reactive material to attach the tail and projectile.

Detailed Description

The technical solution of the present invention is further explained with reference to the drawings and the embodiments.

As shown in fig. 1, the projectile is initially placed in the shell and then both are placed together in the barrel of the artillery. In the first phase, the assembly of the projectile and the shell is launched from the barrel. After leaving the cartridge, the shell will decelerate relative to the projectile and disengage from the projectile. The cartridge casing is divided at the front end into three separate sections by three longitudinal slots. The projectile further comprises a set of resistive stabilizers, such as three fins. After the separation of the shell and the projectile, the projectile will fly in the air until the tail separation phase is entered. During the flight separation phase, the three flights will separate from the projectile. After the tail separation phase, the projectile as a whole will continue to fly in air for a period of time until the water-in phase is entered, but this time will be shorter than the time before the projectile had a tail in air. The projectile will subsequently fly into the water during the launch phase and therefore will not experience the destabilizing effects that would occur if three wings a, b, c were not detached. The projectile will then form a super-void moving through the water until it reaches the target location.

The projectile includes three drag stabilizing features, fins a, b, c, at the rear as shown. The projectile comprises a connection mechanism consisting of a coiled spring-like portion 3 and an elongate portion 4, as shown in figure 2, for connecting the three fins a, b, c to the tail body of the projectile. The attachment mechanism may contain a thermally reactive material that will cause the attachment mechanism to collapse in a controlled manner upon ignition. The controlled burning of the connection means results in a timely detachment of the three fins at the controlled point in time. The thermally reactive material may be a metal foil or film, possibly applied by welding. The separate tail is made of a material which is sufficiently compatible with this connection by means of a welded foil. Ideally, the thermally reactive material is an active nano-platelet material developed by nanotechnology (RNT). However, other thermally reactive materials that may also be used to separate the ballast features from the projectile may be preferred.

Each part of the connecting mechanism is connected with each other through welding. After the active sensitive part is ignited, the coiled part 3 connected to it is also ignited, followed by the expanded part, then the circular band part, and finally the elongated parts a, b and c. In this way the coiled part 3 functions like a time delay mechanism, just like a fuse, wherein the length of the coiled part directly affects the duration of the time delay. All of the above parts comprise a thermally reactive material to improve the fire properties of the coupling. The thermally reactive material may be a nano-coating material applied to the attachment mechanism and formed in the form of a sputter coating.

Shortly after firing, the thermally reactive material of the coiled spring-like portion is ignited. The tail fin of the projectile enables the projectile to have better aerodynamic properties before it enters the water. Before entering water, the thermal reaction material is burnt, so that the bullet head 1 of the projectile body is unhooked from the whole tail wing, and the bullet head 1 of the projectile body is ensured not to have the tail wing when entering water, thereby ensuring the stability of formation of supercavitation.

Claims

1. A resistance stabilized water-entering missile is characterized in that: comprises a bullet (1), a connection mechanism which is separated in a delayed way, and a projectile empennage (5);

the warhead (1) consists of a cavitator, a fuse, a warhead and a semi-hollow cylindrical barrel at the tail part of the warhead; the outer wall of the semi-hollow cylindrical barrel at the tail part is sleeved with an empennage outer barrel, and a time delay fixing mechanism for fixing and separating the empennage is inserted into the barrel wall; a hole is arranged at the position, close to the warhead, of the semi-hollow cylindrical barrel wall at the tail part of the warhead and used for inserting a hook at the inner side of the spring-shaped delay fixing mechanism (3);

the connection mechanism for delayed separation consists of a cylindrical core (2), a spring-shaped delay mechanism (3) coated with a thermal reaction material and a strip-shaped circular ring elongation part (4); the spring-shaped time delay mechanism (3) is sleeved on the cylindrical copper core (2), and the two are sleeved with the elongated part (4) and then simultaneously inserted into the semi-hollow cylindrical barrel at the tail part of the warhead part; both ends of the spring-shaped time delay mechanism (3) are provided with hooks for fixing; the inner hook is inserted into a hole on the semi-hollow cylindrical barrel; the outer hook extends out and is used for fixing the empennage part sleeved on the outer wall of the cylindrical barrel; the projectile tail wing (5) part is a hollow cylindrical barrel, and three tail wings are equally distributed on the outer wall of the cylindrical barrel in three parts; the projectile tail fin outer cylinder is sleeved on the semi-hollow outer cylinder wall at the rear end of the warhead part and is fixed by a time delay connection mechanism from the hole on the outer cylinder wall.