CN110864584A

CN110864584A - Adjustable gas jet flow guiding device for rocket missile launching

Info

Publication number: CN110864584A
Application number: CN201810978464.8A
Authority: CN
Inventors: 夏文嘉; 任杰; 乐贵高; 王恒; 王久赫; 蒯腾飞
Original assignee: Nanjing University of Science and Technology
Current assignee: Nanjing University of Science and Technology
Priority date: 2018-08-27
Filing date: 2018-08-27
Publication date: 2020-03-06
Anticipated expiration: 2038-08-27
Also published as: CN110864584B

Abstract

The invention discloses an adjustable gas jet flow guiding device for rocket missile launching, which comprises a guiding grid plate, a secondary guiding plate, a rotary base and a connecting piece, wherein the guiding grid plate is arranged on the upper surface of the rotary base; the bottom of the rotary base is provided with a first rotating shaft which is rotatably connected with the base of the transmitting tube and can do rotary motion relative to the transmitting tube; the flow guide grid plate comprises a shell, a plurality of flow guide cones and a mounting rack, wherein the flow guide cones are fixed in the shell; the mounting frame is connected with the rotary base through a second rotating shaft; the second rotating shaft is axially vertical to the first rotating shaft at the bottom of the rotary seat and can do pitching motion relative to the transmitting tube; the diversion cones are arranged in the shell in an array manner; a plurality of flow guide holes are formed among the flow guide cones; the bottom of the shell is provided with a mounting rack; the secondary guide plate is connected with the guide grid plate through a connecting piece and is arranged at the rear end of the guide grid plate; a gap is arranged between the secondary guide plate and the guide grid plate; the flow guide direction of the flow guide device can be flexibly selected, and the emission system can be effectively protected.

Description

Adjustable gas jet flow guiding device for rocket missile launching

Technical Field

The invention belongs to the field of guide devices of rocket missiles, and particularly relates to an adjustable gas jet flow guide device for rocket missile launching.

Background

Generally, the gas jet generated during the launching of the rocket or missile belongs to high-temperature and high-speed jet, and the jet can generate larger impact force on a rocket launching system and cause larger damage to the launching system. How to avoid or reduce the damage caused by the gas jet to the launching system is an important factor to be considered when designing the launching system.

At present, two methods are mainly used for solving the problem, one method is to enable the gas jet to avoid a launching system as much as possible during launching, the scheme is more applied to shipboard launching, for example, the gas jet is enabled to be shot to the water surface during launching, and the direct impact on a deck is avoided, the method has the defects that the shooting direction is limited when being selected, particularly, the shipboard running body is slow in steering, and the launching direction needs to be adjusted in a large amount of time; the other method is to install a flow guide mechanism in the direction of gas jet flow, but the flow guide mechanism is mainly applied to vertical emission at present, and the flow guide mechanism is generally fixed on an emission system, the flow guide direction is fixed, the adjustment cannot be carried out according to different emission systems, and the adaptability is not strong when different emission requirements are met.

For example, patent CN 107131794 a discloses a vehicle-mounted missile launching double-arc-shaped flow guider, which is composed of a flow guiding body and a base, and changes the direction of gas jet flow by means of the curved surface of the flow guiding body to avoid the launching system from being impacted and ablated, but the device can only play an effective role in guiding the flow when the gas jet flow impacts the flow guiding body on the front side, and if the lateral launching is carried out, the flow guiding body cannot play a role in guiding the flow.

Disclosure of Invention

The invention aims to provide an adjustable gas jet flow guide device for rocket missile launching, so as to adjust the direction of flow guide according to different requirements.

The technical solution for realizing the purpose of the invention is as follows:

an adjustable gas jet flow guiding device for rocket missile launching comprises a flow guiding grid plate, a secondary flow guiding plate, a rotary base and a connecting piece;

the bottom of the rotary base is provided with a first rotating shaft which is rotatably connected with the base of the transmitting tube and can do rotary motion relative to the transmitting tube; the flow guide grid plate comprises a shell, a plurality of flow guide cones and a mounting rack, wherein the flow guide cones are fixed in the shell; the mounting frame is connected with the rotary base through a second rotating shaft; the second rotating shaft is axially vertical to the first rotating shaft at the bottom of the rotary seat and can do pitching motion relative to the transmitting tube; the diversion cones are arranged in the shell in an array manner; a plurality of flow guide holes are formed among the flow guide cones; the bottom of the shell is provided with a mounting rack; the secondary guide plate is connected with the guide grid plate through a connecting piece and is arranged at the rear end of the guide grid plate; a gap is arranged between the secondary guide plate and the guide grid plate; the gas jet flow generated by the emission tube is dispersed by the diversion cone of the diversion grid plate and is transmitted to the secondary diversion plate through the diversion hole, and the secondary diversion plate disperses the gas jet flow to the periphery.

Compared with the prior art, the invention has the following remarkable advantages:

(1) the flow guide direction of the flow guide device can be flexibly selected, the flow guide device can perform rotary motion around the base of the transmitting tube and also perform pitching motion, and the final flow guide direction of secondary flow guide can be adjusted by adjusting the side plates so as to adjust the final flow direction of the gas jet.

(2) The flow guide device has wide applicability and can be suitable for different emission systems and other systems generating fuel gas jet flow.

(3) The flow guide device effectively protects the emission system and prevents the emission system from being impacted and ablated by high-temperature fuel gas jet flow.

(4) The guide device can effectively save the space of the emission system, and the part which is originally impacted by the fuel gas jet can be placed with other elements or the emission system can be assembled in multiple ways, thereby effectively improving the space utilization rate of the emission system.

The present invention is described in further detail below with reference to the attached drawing figures.

Drawings

Fig. 1 is a schematic structural diagram of the gas jet flow guiding device of the invention.

Fig. 2 is a schematic view of a flow guiding grid plate of the gas jet flow guiding device of the invention.

FIG. 3 is a schematic view of the connection between the grid plate and the rotary base.

Fig. 4 is a schematic view of a deflector structure of the gas jet flow deflector of the present invention.

Fig. 5 is a schematic view of a flow guide cone of the gas jet flow guide device.

Fig. 6 is a schematic view of the use state of the gas jet flow guiding device of the invention.

Detailed Description

For the purpose of illustrating the technical solutions and technical objects of the present invention, the present invention will be further described with reference to the accompanying drawings and specific embodiments.

With reference to fig. 1-3, the adjustable gas jet flow guiding device for rocket missile launching of the invention is arranged at the tail part of a launching tube and comprises a flow guiding grid plate 1, a secondary flow guiding plate 2, a rotary base 3 and a connecting piece 4;

the bottom of the rotary base 3 is provided with a first rotating shaft which is rotatably connected with the base of the transmitting tube, so that the rotary base 3 can do rotary motion relative to the transmitting tube; the flow guiding grid plate 1 comprises a shell 12, a plurality of flow guiding cones 11 fixed in the shell 12 and a mounting rack 14; the mounting frame 14 is connected with the rotary base 3 through a second rotating shaft; the second rotating shaft is axially vertical to the first rotating shaft at the bottom of the rotary seat 3 and can do pitching motion relative to the transmitting tube; the guide cones 11 are arranged in the shell 12 in an array to form a grid-shaped distribution; a plurality of guide holes 13 are formed between the guide cones 11; a mounting frame 14 is arranged at the bottom of the shell 12; the secondary guide plate 2 is connected with the flow guiding grid plate 1 through a connecting piece 4 and is arranged at the rear end of the flow guiding grid plate 1; a gap is formed between the secondary guide plate 2 and the guide grid plate 1 through a connecting piece 4; the gas jet flow generated by the emission tube is dispersed by the diversion cone 31 of the diversion grid plate 1, so that the effects of first diversion and reduction of gas jet flow impact on the secondary diversion plate are achieved; the gas jet flow dispersed by the first diversion is transmitted to the secondary diversion plate 2 through the diversion holes 13, and the secondary diversion plate 2 disperses the gas jet flow to the periphery.

Further, referring to fig. 4, the secondary baffle 2 includes a bottom plate 21 and four side plates 22; the bottom plate 21 is arranged at the rear end of the flow guiding grid plate 1; the four side plates 22 are respectively connected to the periphery of the bottom plate 21 through four rotating shafts; the four side plates 22 are all positioned between the flow guiding grid plate 1 and the bottom plate 21; the inner space enclosed by the four side plates 22 is larger than the size of the flow guiding grid plate 1; the bottom plate 21 further blocks the dispersed jet flow, and prevents the gas jet flow from continuously impacting backwards so as to disperse around. While the side plates 22 are rotatable with respect to the base plate 21, the final direction of the gas jet can be controlled by erecting and laying.

Further, the side plate 22 may be a flat plate or an arc plate.

Further, with reference to fig. 5(a-c), the guide cone 11 is a conical structure, the generatrix of the guide cone 11 can be selected from a concave curve, a linear curve and a convex curve, and the included angle between the generatrix and the bottom surface can be selected within a range of 0 to 90 degrees according to design requirements.

Furthermore, the mounting rack 14 is embedded in the flow guiding grid plate 1, so that the mounting space of the whole device can be effectively reduced.

Referring to fig. 6, the deflector of the present invention is connected to the launching system through the rotating base 3 and installed behind the launching tube 100; the number of the diversion cones 31 is determined according to the number of the gas jet flows, and each gas jet flow direction corresponds to one diversion cone 31.

The complete working flow of the flow guide device is as follows: when the gas jet is emitted, the gas jet is dispersed by the guide cone 11 in the guide grid plate 1, so that the secondary guide plate 2 is prevented from being directly impacted by the gas jet, and then the final guide is carried out by the secondary guide plate 2. The whole flow guide device can perform rotary motion and pitching motion around the base within a certain range, so that the flow guide direction can be adjusted according to the emission directions of different emission systems, the included angle of the side plate 22 relative to the bottom plate 21 can be adjusted, and the final flow direction of the gas jet flow can be adjusted. After the direction of each rotating shaft is adjusted, the rotating shafts can be locked and fixed, or the corresponding rotating shafts are driven to rotate by a stepping motor. The flow guide device can effectively protect the emission system, avoid the emission system from being impacted and ablated by high-temperature gas jet, save the space of the emission system, improve the space utilization rate of the emission system, and meanwhile, the design scheme of secondary flow guide can also protect the flow guide device, thereby effectively prolonging the service life of the flow guide device.

Claims

1. An adjustable gas jet flow guiding device for rocket missile launching is characterized by comprising a guiding grid plate (1), a secondary guiding plate (2), a rotary base (3) and a connecting piece (4);

the bottom of the rotary base (3) is provided with a first rotating shaft which is rotatably connected with the base of the transmitting tube and can do rotary motion relative to the transmitting tube; the flow guide grid plate (1) comprises a shell (12), a plurality of flow guide cones (11) fixed in the shell (12) and a mounting rack (14); the mounting rack (14) is connected with the rotary base (3) through a second rotating shaft; the second rotating shaft is axially vertical to the first rotating shaft at the bottom of the rotary seat (3) and can do pitching motion relative to the transmitting tube; the guide cones (11) are arranged in the shell (12) in an array manner; a plurality of guide holes (13) are formed among the guide cones (11); a mounting frame (14) is arranged at the bottom of the shell (12); the secondary guide plate (2) is connected with the guide grid plate (1) through a connecting piece (4) and is arranged at the rear end of the guide grid plate (1); a gap is arranged between the secondary guide plate (2) and the guide grid plate (1); the gas jet flow generated by the emission tube is dispersed by the diversion cone (31) of the diversion grid plate (1) and is transmitted to the secondary diversion plate (2) through the diversion hole (13), and the gas jet flow is dispersed around by the secondary diversion plate (2).

2. Adjustable gas jet guiding device for rocket missile launching according to claim 1, characterized in that the secondary deflector (2) comprises a bottom plate (21) and four side plates (22); the bottom plate (21) is arranged at the rear end of the flow guide grid plate (1); the four side plates (22) are respectively connected to the periphery of the bottom plate (21) through four rotating shafts; the four side plates (22) are all positioned between the flow guide grid plate (1) and the bottom plate (21); the inner space of the enclosed city of the four side plates (22) is larger than the size of the flow guiding grid plate (1).

3. Adjustable gas jet deflector for rocket missile launching according to claim 1, characterized in that the side plates (22) can be flat or curved plates.

4. The adjustable gas jet deflector for rocket missile launching according to claim 1, characterized in that the generatrix of the deflector cone (11) is concave, linear or convex.

5. The adjustable gas jet deflector for rocket missile launching according to claim 1, wherein the included angle between the generatrix and the bottom surface is in the range of 0 to 90 °.

6. Adjustable gas jet deflector for rocket missile launching according to claim 1, characterized in that the mounting (14) is embedded in the deflector grid plate (1).