CN110145412B

CN110145412B - Gate type solid rocket engine

Info

Publication number: CN110145412B
Application number: CN201910446867.2A
Authority: CN
Inventors: 孙烨真; 魏志军; 张璐佳
Original assignee: Beijing Institute of Technology BIT
Current assignee: Beijing Institute of Technology BIT
Priority date: 2019-05-27
Filing date: 2019-05-27
Publication date: 2020-11-03
Anticipated expiration: 2039-05-27
Also published as: CN110145412A

Abstract

The invention discloses a gate type solid rocket engine, and belongs to the technical field of solid rocket engines. The engine is internally provided with a storage chamber and a combustion chamber, the storage chamber and the combustion chamber are internally provided with a plurality of independent and corresponding sub-storage chamber channels and sub-combustion chamber channels, the tail ends of the sub-storage chamber channels and the sub-combustion chamber channels are respectively sealed by sub-storage chamber channel doors and sub-combustion chamber channel doors which are arranged on the sub-storage chamber channels, a section of spring and a plurality of sections of grains are sequentially arranged in the sub-storage chamber, the grains are compressed and sealed in the sub-storage chamber channels by the sub-storage chamber channel doors, and an igniter is arranged outside each sub-combustion chamber door; after the sub-storage chamber channel door is opened, a section of the explosive column is pushed into the sub-combustion chamber channel by a spring and then is closed, and the sub-combustion chamber door is opened and is ignited by an igniter; the invention realizes the control of the thrust of the engine by controlling one or more branch combustion chamber channels to ignite simultaneously or circularly.

Description

Gate type solid rocket engine

Technical Field

The invention relates to the technical field of solid rocket engines, in particular to a gate type solid rocket engine.

Background

The solid rocket engine is a chemical rocket engine using a solid propellant, and has the advantages of simple structure, high propellant density, capability of storing the propellant in a combustion chamber for standby application, convenience and reliability in operation and the like. However, the solid rocket engine has the disadvantages of short working time, large acceleration, difficult control of thrust and difficult repeated starting, so that the use of the solid rocket engine is limited.

The reason for the short operating time of solid rocket engines is mainly that the heated components usually have no effective cooling measures and can only operate for a short time under high temperature, high pressure and high velocity gas flow conditions. Although heat-resistant materials and various passive thermal protection measures can be adopted, the working time is still greatly limited; on the other hand, the burning time cannot last too long, limited by the charge size.

Once the solid rocket engine is ignited, the solid rocket engine cannot be flamed out and restarted at will and only works according to a preset thrust scheme until the combustion is finished. Therefore, the solid rocket engine is difficult to artificially adjust the thrust according to temporary needs or realize repeated starting for many times.

Disclosure of Invention

In view of the above, the present invention provides a gate-type solid rocket engine capable of effectively controlling the operating thrust of the engine by controlling the amount of the combustion grains and having the capability of repeated starting.

A door type solid rocket engine is provided with a storage chamber and a combustion chamber, wherein a plurality of independent and corresponding sub-storage chamber channels and sub-combustion chamber channels are arranged in the storage chamber and the combustion chamber, the tail ends of the sub-storage chamber channels and the sub-combustion chamber channels are respectively sealed by sub-storage chamber channel doors and sub-combustion chamber channel doors which are arranged on the sub-storage chamber channels and the sub-combustion chamber channels, a section of spring and a plurality of sections of grains are sequentially arranged in the sub-storage chamber, the grains are compressed and sealed in the sub-storage chamber channels by the sub-storage chamber channel doors, and an igniter is arranged outside each sub-combustion chamber door; after the sub-storage chamber channel door is opened, one section of the explosive column is pushed into the sub-combustion chamber channel by a spring and then is closed, and the sub-combustion chamber door is opened and is ignited by an igniter; the control of the thrust of the engine is realized by controlling one or more branch combustion chamber channels to ignite simultaneously or circularly.

Further, the sub-reservoir passage and the sub-combustion passage are provided by a reservoir door frame and a combustion chamber door frame provided in the engine case, which are formed by machining a plurality of axially independent through-holes in a solid cylindrical structure.

Furthermore, the two ends of the explosive column are provided with conical structures, and the conical structures are convenient for the passage doors of the storage chambers to be clamped at the conical ends, so that the explosive column is separated.

Has the advantages that:

1. the invention realizes the control of the combustion amount of the explosive columns by arranging the corresponding storage channels and the combustion chamber channels in the storage chamber and the combustion chamber to combust the explosive columns in different channels, and can solve the problem that the thrust of the existing fixed rocket engine is difficult to control.

2. The combustion of the explosive column is mainly carried out in the branch combustion chamber channel, so that the requirement on the heat protection of the engine shell is reduced, and the working time of the engine can be effectively prolonged.

2. The engine can continuously work and quickly respond, so that the working efficiency is improved; the connection between the combustion chamber and the storage chamber is blocked by the switch combination of the sub-storage chamber access door and the sub-combustion chamber access door, so that the combustible gas is not allowed to enter the storage chamber to cause spontaneous combustion.

Drawings

FIG. 1 is a schematic view of the rocket motor of the present invention;

FIG. 2 is a schematic plan view of a storage compartment door of the present invention;

fig. 3 is a plan view of the burner door of the present invention.

Wherein, 1-spring, 2-grain, 3-storage chamber door frame, 4-combustion chamber door frame, 5-spray pipe, 6-combustion chamber, 7-storage chamber, 8-ignition device, 9-branch combustion chamber door, 10-branch combustion chamber channel, 11-branch storage chamber channel and 12-branch storage chamber channel door.

Detailed Description

The invention is described in detail below by way of example with reference to the accompanying drawings.

As shown in figure 1, the invention provides a gate-type solid rocket engine, which comprises a shell, a storage chamber door frame 3, a combustion chamber door frame 4, a spray pipe 5, a spring 1 and a grain 2;

wherein, casing one end is sealed, and the other end is connected with spray tube 5, and spray tube 5 realizes that the gas inflation is accelerated, produces thrust. The storage chamber door frame 3 and the combustion chamber door frame 4 are coaxially arranged in the shell, and the storage chamber door frame 3 and the combustion chamber door frame 4 are formed by processing a plurality of axial independent through holes on a solid cylindrical structure; a through hole on a storage chamber door frame 3 forms a storage chamber channel 11, a spring 1 and two explosive columns 2 are sequentially arranged in the sub-storage chamber channel 11, one end of the spring is in contact with the inner wall of the shell, the other end of the spring is in contact with the end face of the first explosive column, and the end face of the sub-storage chamber channel 11 is connected with a sub-storage chamber channel door 12 through a rotating shaft, as shown in figure 2; when the sub-storage chamber passage door 12 is closed, the two explosive columns are sealed in the sub-storage chamber passage 11, and the spring 1 is in a compressed state.

The through hole on the combustion chamber door frame 4 forms a branch combustion chamber channel 10, the position of the branch combustion chamber channel 10 corresponds to the storage chamber channel 11, and the tail end of the branch combustion chamber channel 10 is provided with a branch combustion chamber door 9 for opening or closing the branch combustion chamber channel in the same structure, as shown in figure 3; the exterior of each branch combustion chamber door 9 is provided with an ignition device 8.

The area of the storage chamber door frame 3 in the housing forms a storage chamber 7 of the engine, the area of the combustion chamber door frame 4 in the housing forms a combustion chamber 6 of the engine,

wherein, the spring 1 is used as a thrust device and pushes the grain 2 into the branch combustion chamber channel when needed; the two ends of the explosive column 2 are of conical structures, and the conical structures facilitate the passage door 12 of the storage chamber to be clamped at the conical ends, so that the explosive column is separated. The storage compartment door frame 3 provides a mounting base for the storage compartment access door. The ignition device 8 is used to ignite the charge 2 inside the combustion chamber, one ignition device 8 at a time. The opening or closing of the branch combustion chamber door 9 is used to control the combustion behavior of the branch combustion chamber channel. The sub-combustor channel 10 is used for combustion of the conical shaped charge. The sub-storage chamber channel 11 is used for storing the conical explosive column. When the sub-storage chamber passage door 12 is opened, the conical explosive columns 2 are controlled to be pushed into the sub-combustion chamber passage, and when the sub-storage chamber passage door is closed, the front and rear explosive columns are separated, so that the separation of the explosive columns is realized.

The working process is as follows: the explosive column 2 in the sub-storage chamber channel 11 is aligned with the sub-combustion chamber door 9 in advance, when an instruction is obtained, the sub-storage chamber channel door 12 is opened, the sub-storage chamber channel door 12 rotates to a vacant position in the center of the cross section of the door around a rotating shaft of a connecting point, the explosive column 2 is pushed in by the spring 1, then the sub-storage chamber channel door 12 is closed, the sub-storage chamber channel door 12 is just clamped at a conical end seam, the explosive column 2 before and after separation, and the sub-storage chamber channel door 12 resets in a rotating mode around a shaft. The branch combustion chamber door 9 is opened, and the branch combustion chamber door 9 rotates to the vacant position in the center of the cross section of the door around the rotating shaft of the connecting point. A plurality of ignition devices 8 corresponding to the tail end positions of the branch combustion chamber channels 10 are arranged at the rear part of the combustion chamber 6, ignition is needed to consume one ignition powder in the ignition device 8 each time, each ignition device 8 can be electrified to ignite independently, so that the powder columns 2 in the branch combustion chamber channels 10 are ignited, and the ignition devices 8 which are not operated are not ignited by mistake due to ignition of high-temperature gas in the combustion chamber. The explosive column 2 is combusted in the branch combustion chamber channel 10, and the generated jet flow expands and accelerates through the spray pipe 5 to generate thrust. After complete combustion, the branch combustion chamber door 9 is closed, and the branch combustion chamber door 9 is reset in a rotating mode around the shaft. Opening branch storage chamber access door 12, repeat the operation, put into next powder column 2 to branch combustion chamber passageway 10 by the spring force, later close storage chamber access door 12, the corresponding door 12 of storage chamber passageway blocks in awl end seam department just, and powder column 2 before and after the separation opens branch combustion chamber door 9, and powder column 2 burns in branch combustion chamber passageway 10.

In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The door type solid rocket engine is characterized in that a storage chamber and a combustion chamber are arranged in the engine, a plurality of independent and corresponding sub-storage chamber channels and sub-combustion chamber channels are arranged in the storage chamber and the combustion chamber, the tail ends of the sub-storage chamber channels and the sub-combustion chamber channels are respectively sealed by sub-storage chamber channel doors and sub-combustion chamber channel doors which are arranged on the sub-storage chamber channels, a section of spring and a plurality of sections of explosive columns are sequentially arranged in the sub-storage chamber, the explosive columns are compressed and sealed in the sub-storage chamber channels by the sub-storage chamber channel doors, and an igniter is arranged outside each sub-combustion chamber door; after the sub-storage chamber channel door is opened, one section of the explosive column is pushed into the sub-combustion chamber channel by a spring and then is closed, and the sub-combustion chamber door is opened and is ignited by an igniter; the control of the thrust of the engine is realized by controlling one or more branch combustion chamber channels to ignite simultaneously or circularly;

the sub-reserve chamber passage and the sub-combustion chamber passage are provided by a reserve chamber door frame and a combustion chamber door frame provided in the engine case, which are formed by machining a plurality of axially independent through-holes on a solid cylindrical structure.

2. The door-type solid rocket engine according to claim 1, wherein the two ends of said grain have a tapered structure, the tapered structure facilitates the passage door of the sub-storage chamber to be clamped at the tapered end, thereby realizing grain separation.