CN215296027U

CN215296027U - Low-cost movable rudder trajectory correction assembly

Info

Publication number: CN215296027U
Application number: CN202121126414.0U
Authority: CN
Inventors: 张伟; 张俊良; 杨爱霞; 杨玲霞
Original assignee: Xi'an Zhixinzhonghe Defense Technology Co ltd
Current assignee: Xi'an Zhixinzhonghe Defense Technology Co ltd
Priority date: 2021-05-25
Filing date: 2021-05-25
Publication date: 2021-12-24
Anticipated expiration: 2031-05-25

Abstract

The utility model discloses a low-cost movable rudder trajectory correcting component, which comprises a warhead cabin, wherein the bottom of the warhead cabin is sequentially connected with a control cabin, a rudder cabin and a battery cabin from top to bottom; the bullet cabin, the control cabin, the rudder cabin and the battery cabin are electrically connected; rudder cabin is including the cabin body, a plurality of movable slots have been seted up to cabin body outer wall annular, cabin body axial direction is rotated and is connected with a plurality ofly and movable slot complex air brake, the internal portion of cabin is close to the axle center and is provided with a plurality of electromagnetic plates, and slide at the inside and air brake vertical direction of rudder cabin, and the inner both sides of air brake are arranged in to per two sets of electromagnetic plates, and mutual actuation, be independent between every electromagnetic plate and the hydraulic cylinder, the in-process of use, can adjust the inclination of the air brake of each position, and then at the in-process of projectile flight, can adjust the angle of flight, moreover, the steam generator is simple in structure, and the cost is lower.

Description

Low-cost movable rudder trajectory correction assembly

Technical Field

The utility model relates to a field is revised to movable rudder trajectory, especially relates to a subassembly is revised to movable rudder trajectory of low cost.

Background

After traditional ammunition is ejected from the trajectory, because in the process of launching and flying, the projectile body is influenced by the external environment, the trajectory of the projectile body can be deviated, so that in order to keep the normal traveling track of the trajectory, the supply of injection fuel at the bottom of the projectile body and the injection rate and the injection angle need to be adjusted, the requirement on the whole operating equipment in the process is high, the manufacturing cost is high, and the injection of the injection fuel is frequently switched, more fuel is wasted, and the flying stroke of the projectile body is greatly reduced.

SUMMERY OF THE UTILITY MODEL

In order to overcome the not enough of prior art, the utility model provides a subassembly is revised to low-cost movable rudder trajectory, the trajectory is revised, and the cost is lower.

In order to solve the technical problem, the utility model provides a following technical scheme: a low-cost movable rudder trajectory correcting assembly comprises a bullet cabin, wherein the bottom of the bullet cabin is sequentially connected with a control cabin, a rudder cabin and a battery cabin from top to bottom;

the bullet cabin, the control cabin, the rudder cabin and the battery cabin are electrically connected;

the rudder cabin is including the cabin body, and a plurality of movable grooves have been seted up to cabin body outer wall annular, cabin body axial direction rotates and is connected with a plurality ofly and movable groove complex air brake, the internal portion of cabin is close to the axle center and is provided with a plurality of electromagnetic plates, and slides with the air brake vertical direction in rudder cabin is inside, and the inner both sides of air brake are arranged in to per two sets of electromagnetic plates, and mutual actuation.

As an optimal technical scheme of the utility model, warhead under-deck inside is provided with fuze, satellite navigation, wireless binding integration module, and all with battery compartment electric connection.

As an optimized technical scheme of the utility model, the rudder cabin rotates with the control cabin to be connected.

As an optimal technical scheme of the utility model, every group the electromagnetic plate is kept away from air brake one side and is provided with hydraulic cylinder.

Compared with the prior art, the utility model discloses the beneficial effect that can reach is:

1. through the electromagnetic plate that sets up, hydraulic cylinder, after the projectile body orbital deviation appears at the in-process of operation, hydraulic cylinder moves to the direction of both sides respectively, through the circular telegram of one side electromagnetic plate, with the direction actuation of air brake to the electromagnetic plate, the air brake is under the effect of rotation axis, make the air brake to the direction motion opposite with the direction of electromagnetic plate, be independent between every electromagnetic plate and the hydraulic cylinder, consequently at the in-process that uses, can adjust the inclination of the air brake of each side position, and then at the in-process that the projectile body flies, can adjust the angle of flight, moreover, the steam generator is simple in structure, and the cost is lower.

2. The projectile trajectory continuous correction method comprises the steps that a fuze, satellite navigation and wireless binding integrated module is arranged, a satellite navigation receiver is adopted to measure projectile speed and position information, a geomagnetic component is adopted to measure rolling attitude information, a rudder cabin is used as an execution mechanism, a composite guidance algorithm is utilized to quickly solve a fixed rudder control command, a fixed rudder continuously rotates when trajectory correction is not performed, the rudder cabin is driven to rotate to a required angle by adopting a rolling attitude servo control technology during trajectory correction, the rudder cabin and a ground inertial coordinate system are relatively static, the projectile trajectory continuous correction is realized, the shooting accuracy CEP can be not more than 10 meters by a trajectory correction component, and the projectile trajectory continuous correction method can be applied to weapon platforms such as 120 mm projectile and 122 mm rocket projectiles.

Drawings

Fig. 1 is a schematic structural view of the present invention;

fig. 2 is a schematic diagram of the explosion structure of the present invention;

FIG. 3 is a schematic cross-sectional structure of a rudder engine room of the present invention;

fig. 4 is a schematic view of the cross-sectional structure of the cabin of the present invention.

Wherein:

1. a bullet cabin; 2. a control cabin; 3. a rudder engine room; 31. a cabin body; 311. a movable groove; 32. a speed reduction plate; 321. a strong magnetic plate; 33. an electromagnetic plate; 34. a hydraulic cylinder; 4. and a battery compartment.

Detailed Description

In order to make the technical means, the creation features, the achievement purposes and the functions of the invention easy to understand, the invention is further explained below with reference to the specific embodiments, but the following embodiments are only the preferred embodiments of the invention, not all. Based on the embodiments in the implementation, other embodiments obtained by those skilled in the art without any creative work belong to the protection scope of the present invention. The experimental methods in the following examples are conventional methods unless otherwise specified, and materials, reagents and the like used in the following examples are commercially available unless otherwise specified.

Example (b):

as shown in fig. 1-4, the utility model provides a low-cost movable rudder trajectory correcting assembly, which comprises a bullet cabin 1, wherein the bottom of the bullet cabin 1 is sequentially connected with a control cabin 2, a rudder cabin 3 and a battery cabin 4 from top to bottom; the bullet cabin 1, the control cabin 2, the rudder cabin 3 and the battery cabin 4 are electrically connected; the rudder cabin 3 comprises a cabin body 31, a plurality of movable grooves 311 are annularly formed in the outer wall of the cabin body 31, the cabin body 31 is axially and rotatably connected with a plurality of speed reducing plates 32 matched with the movable grooves 311, a plurality of electromagnetic plates 33 are arranged inside the cabin body 31 close to the axis and slide in the direction perpendicular to the speed reducing plates 32 inside the rudder cabin 3, and every two groups of electromagnetic plates 33 are arranged on two sides of the inner end of each speed reducing plate 32 and attract each other.

In the embodiment, fuse, satellite navigation and wireless binding integrated modules are arranged in the warhead cabin 1 and are electrically connected with the battery cabin 4, and the rudder cabin 3 is rotationally connected with the control cabin 2;

the method comprises the steps of measuring speed and position information of a projectile by using a satellite navigation receiver, measuring rolling attitude information by using a geomagnetic component, using a rudder cabin 3 as an execution mechanism, rapidly resolving a control instruction of a fixed rudder by using a composite guidance algorithm, continuously rotating the fixed rudder when trajectory correction is not performed, driving the rudder cabin 3 to rotate to a required angle by using a rolling attitude servo control technology during trajectory correction, enabling the rudder cabin 3 and a ground inertial coordinate system to be relatively static, and realizing continuous correction of trajectory of the projectile, wherein the trajectory correction component can realize shooting accuracy CEP not more than 10 meters, and can be applied to weapon platforms such as 120 mm projectile and 122 mm rocket projectile.

Besides, the two sides of the speed reducing plate 32 close to the electromagnetic plates 33 are provided with strong magnetic plates 321, the strength of the speed reducing plate in the process of being absorbed by the electromagnetic plates 33 is improved, one side of each group of electromagnetic plates 33, which is far away from the speed reducing plate 32, is provided with a hydraulic oil cylinder 34, the displacement of the electromagnetic plates 33 is controlled through the extension and retraction of the hydraulic oil cylinder 34, and the opening and closing angle of the speed reducing plate 32 is controlled conveniently.

The electromagnetic plate 33 operates as known to those skilled in the art: when the iron core is inserted inside the energized solenoid, the iron core is magnetized by the magnetic field of the energized solenoid. The magnetized core also becomes a magnet, so that the magnetism of the solenoid is greatly enhanced because the two magnetic fields are superposed with each other.

When the missile is used, when the missile flies linearly, the electromagnetic plates 33 on two sides are simultaneously extruded towards the direction of the speed reducing plate 32 through the hydraulic oil cylinder 34, so that the speed reducing plate 32 is in an axial vertical state, and meanwhile, the electromagnetic plates 33 are not electrified;

after the track of the projectile deviates in the operation process, the hydraulic oil cylinders 34 move towards the directions of two sides respectively, the electromagnetic plates 33 on one side are electrified, the speed reducing plates 32 are attracted towards the electromagnetic plates 33, the speed reducing plates 32 move towards the directions opposite to the directions of the electromagnetic plates 33 under the action of the rotating shafts, and each electromagnetic plate 33 and each hydraulic oil cylinder 34 are independent, so that the inclination angle of each position of the speed reducing plates 32 can be adjusted in the use process, and further, in the projectile flying process, the flying angle can be adjusted.

In the present disclosure, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact between the first and second features, or may comprise contact between the first and second features not directly. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.

The foregoing shows and describes the general principles, essential features, and advantages of the invention. It should be understood by those skilled in the art that the present invention is not limited by the above embodiments, and the description in the above embodiments and the description is only preferred examples of the present invention, and is not intended to limit the present invention, and that the present invention can have various changes and modifications without departing from the spirit and scope of the present invention, and these changes and modifications all fall into the scope of the claimed invention. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims

1. A low-cost movable rudder trajectory modification assembly comprises a bullet cabin (1) and is characterized in that: the bottom of the bullet cabin (1) is sequentially connected with a control cabin (2), a rudder cabin (3) and a battery cabin (4) from top to bottom;

the bullet cabin (1), the control cabin (2), the rudder cabin (3) and the battery cabin (4) are electrically connected;

rudder cabin (3) including the cabin body (31), a plurality of movable groove (311) have been seted up to cabin body (31) outer wall annular, cabin body (31) axial direction is connected with a plurality of and movable groove (311) complex air brake (32), cabin body (31) inside is close to the axle center and is provided with a plurality of electromagnetic plates (33), and slides in rudder cabin (3) inside and air brake (32) vertical direction, and arranges air brake (32) inner both sides in per two sets of electromagnetic plates (33), and mutual actuation.

2. A low cost movable rudder ballistic trim assembly as in claim 1 wherein: fuse, satellite navigation, wireless binding integration module are provided with in bullet cabin (1), and all with battery compartment (4) electric connection.

3. A low cost movable rudder ballistic trim assembly as in claim 1 wherein: the rudder cabin (3) is rotationally connected with the control cabin (2).

4. A low cost movable rudder ballistic trim assembly as in claim 1 wherein: and strong magnetic plates (321) are arranged on the two sides of the speed reducing plate (32) close to the electromagnetic plate (33).

5. A low cost movable rudder ballistic trim assembly as in claim 1 wherein: and a hydraulic oil cylinder (34) is arranged on one side, away from the speed reducing plate (32), of each group of electromagnetic plates (33).