CN210769062U

CN210769062U - Liquid starter structure and attitude control power system

Info

Publication number: CN210769062U
Application number: CN201921451508.8U
Authority: CN
Inventors: 不公告发明人
Original assignee: Shaanxi Landspace Co ltd
Current assignee: Shaanxi Landspace Co ltd
Priority date: 2019-09-03
Filing date: 2019-09-03
Publication date: 2020-06-16
Anticipated expiration: 2029-09-03

Abstract

The utility model discloses a liquid starter structure and an attitude control power system, which comprises a gas generating structure, a cutting structure, a propellant storage structure and a shell structure; the shell structure has the gas passage export, gas generation structure intercommunication gas passage, the cutting structure is located inside the gas passage, propellant storage structure fixed set up in one side of shell structure, gas generation structure is used for producing high temperature gas, in order to promote cutting structure cutting propellant storage structure, propellant storage structure inboard is equipped with the piston one side of piston is provided with first magnet and second magnet relatively, through the circular telegram, sets up in the propellant storage structure first magnet with the mutual repulsion of second magnet promotes the storage and is in piston extrusion propellant, so that the propellant is followed liquid medium channel export flows, compares with prior art, has reasonable in design, improves the reliability of system.

Description

Liquid starter structure and attitude control power system

Technical Field

The utility model relates to a liquid rocket gas pressure boost driving system field, in particular to liquid starter structure and appearance accuse driving system.

Background

With the rapid development of the aerospace industry, various technologies related to rockets also realize the rapid advance. The starter is used as an important component of the fuel gas pressurization power system and provides initial starting pressure for the fuel gas pressurization power system. At present, solid charge is adopted in a starter, and when the solid charge is combusted, a large amount of solid particles are generated, so that a valve of a power system is blocked, the working reliability of a fuel gas pressurization power system is reduced, and the safe operation of a rocket is influenced.

Therefore, how to provide a starter with reasonable design, safety and reliability to solve the defect that a large amount of solid particles are generated during the operation of the solid starter to cause the blockage of a valve, and the problem to be solved at present is to improve the operational reliability of a gas pressurization power system.

Disclosure of Invention

The utility model aims at providing a liquid starter structure and appearance accuse driving system has reasonable in design, and safe and reliable can solve solid starter during operation and produce a large amount of solid particles and cause the shortcoming of valve jam, improves advantages such as gas pressure boost driving system's operational reliability.

In order to achieve the above object, the utility model provides a following technical scheme: a liquid starter structure comprises a gas generating structure, a cutting structure, a propellant storage structure and a shell structure; the shell structure is provided with a gas channel and a liquid medium channel outlet, the gas generation structure is communicated with the gas channel of the shell structure, the cutting structure is positioned in the gas channel of the shell structure, the propellant storage structure is fixedly arranged at one side of the shell structure, the part for storing propellant is arranged in the shell structure in a manner of being matched with the cutting structure, the gas generation structure is used for generating high-temperature gas to push the cutting structure to cut the propellant storage structure positioned in the shell structure, a piston is arranged at the inner side of the propellant storage structure, the propellant storage structure is used for storing propellant at one side of the piston, a first magnet and a second magnet are oppositely arranged at the other side of the piston, and the first magnet and the second magnet which are arranged in the propellant storage structure repel each other after being electrified, pushing the piston to squeeze the propellant stored in the propellant storage structure so that the propellant rapidly flows out from the liquid medium passage outlet.

Preferably, the gas generating structure is an electric detonator, and one end of the electric detonator in the shell structure is communicated with the gas channel.

Preferably, the cutting structure comprises a main body part, a cutting part and a diversion part, the propellant storage structure comprises a storage tank, the cutting part is abutted against the bottom of the storage tank, and when the gas generation structure generates high-pressure gas, the cutting part is pushed to move so as to cut the bottom of the storage tank, so that the propellant stored in the storage tank enters the liquid medium channel outlet through the diversion part.

Preferably, the cutting part includes a channel hole, the flow guide part includes a first flow guide channel and a second flow guide channel which are arranged along a first direction and are spaced in a movement direction of the cutting structure, the first flow guide channel includes the channel hole, center lines of the first flow guide channel and the second flow guide channel are located on the same straight line, and one end of the bottom of the storage tank is located in the channel hole and is tightly attached to an inner wall of the channel hole.

Preferably, the aperture of the passage hole is larger than the aperture of the first flow guide passage on the side of the passage hole away from the storage structure.

Preferably, the main body portion is circular in shape at two ends, and sinking planes are arranged at the middle part of the main body portion and close to two sides of the storage box, and the sinking planes are perpendicular to the first direction.

Preferably, the propellant storage structure further comprises a storage tank, a sealing ring and a liquid propellant, the first magnet and the second magnet are respectively an electromagnet and a permanent magnet, the electromagnet, the permanent magnet and the piston are located inside the storage tank, the storage tank is a sealing structure, the first magnet and the permanent magnet are arranged on one side of the piston in a facing manner, the other side of the electromagnet far away from the permanent magnet is tightly attached to the inner surface of the upper end of the storage tank, and the side of the permanent magnet far away from the electromagnet is tightly attached to the piston, so that a repulsive force is generated between the electromagnet and the permanent magnet which are electrified to push the piston to move; the propellant storage structure is used for storing liquid propellant on the other side of the piston, and the sealing ring is sleeved on the outer surface of the piston and is tightly attached to the inner surface of the storage tank; the outer edge of the piston is provided with a groove, the groove is of a structure which is concave towards the center direction of the storage tank, and the sealing ring is located in the groove and is tightly attached to the groove.

Preferably, the tank comprises a first tank and a second tank, the first tank and the second tank are cylindrical in shape, the diameter of the first tank is larger than that of the second tank, and the first tank is connected with the second tank through a circular plate with a through hole.

Preferably, shell structure contains shell main part, goes up protruding post, cone and protruding post down, it is located to go up protruding post and protruding post down the both sides of shell main part, and both central lines are located same straight line, the inboard of going up protruding post is equipped with the internal thread, propellant storage structure is equipped with the external screw thread, propellant storage structure is through its external screw thread screw in the internal thread is fixed in shell structure, protruding post forms down the liquid medium passageway export, the cone is used for right the cutting structure is spacing, the cone is located shell main part one end, and keeps away from electric detonator structure one side.

The utility model also provides a position accuse driving system contains above liquid starter structure.

Compared with the prior art, the beneficial effects of the utility model are that: a liquid starter structure comprises a gas generating structure, a cutting structure, a propellant storage structure and a shell structure; the shell structure is provided with a gas channel and a liquid medium channel outlet, the gas generation structure is communicated with the gas channel of the shell structure, the cutting structure is positioned in the gas channel of the shell structure, the propellant storage structure is fixedly arranged at one side of the shell structure, the part for storing propellant is arranged in the shell structure in a manner of being matched with the cutting structure, the gas generation structure is used for generating high-temperature gas to push the cutting structure to cut the propellant storage structure positioned in the shell structure, a piston is arranged at the inner side of the propellant storage structure, the propellant storage structure is used for storing propellant at one side of the piston, a first magnet and a second magnet are oppositely arranged at the other side of the piston, and the first magnet and the second magnet which are arranged in the propellant storage structure repel each other after being electrified, the structure has the advantages of reasonable design, safety and reliability, the starter takes the liquid propellant as a starting source, the defect that a large amount of solid particles are generated during the working of a solid starter to cause valve blockage can be overcome, and the working reliability of a gas pressurization power system is improved.

Drawings

Fig. 1 is a schematic structural diagram of the initial state of the liquid starter structure of the present invention;

FIG. 2 is a front view of the cutting structure of the present invention;

FIG. 3 is a top view of the cutting structure of the present invention;

FIG. 4 is a perspective view of the cutting structure of the present invention;

FIG. 5 is an enlarged view of the propellant storage structure of the present invention;

FIG. 6 is a front view of the piston of the present invention;

FIG. 7 is a top view of the circular plate of the present invention;

FIG. 8 is a schematic diagram of a boosting system of a gas boosting power system.

Description of reference numerals:

1 gas generating structure 11 electric detonator

2 cutting structure 21 body part

211 sink plane 22 cutting section

221 channel hole 23 flow guide part

231 first flow guide channel 232 second flow guide channel

3 propellant storage structure 31 tank

311 first reservoir 312 second reservoir

32 first magnet 33 piston

331 groove 34 sealing ring

35 liquid propellant 36 second magnet

4 casing structure 41 casing main body

42 upper convex column 43 cone

44 lower protruding column 5 round plate

Detailed Description

To make the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the spirit of the present invention will be described in detail with reference to the accompanying drawings, and any person skilled in the art can change or modify the techniques taught by the present invention without departing from the spirit and scope of the present invention after understanding the embodiments of the present invention.

The exemplary embodiments and descriptions of the present invention are provided to explain the present invention, but not to limit the present invention. Additionally, the same or similar numbered elements/components used in the drawings and the embodiments are used to represent the same or similar parts.

As used herein, the terms "first," "second," …, etc. do not denote any order or sequential importance, nor are they used to limit the invention, but rather are used to distinguish one element from another or from another element or operation described in the same technical language.

With respect to directional terminology used herein, for example: up, down, left, right, front or rear, etc., are simply directions with reference to the drawings. Accordingly, the directional terminology used is intended to be illustrative and is not intended to be limiting of the present teachings.

As used herein, the terms "comprising," "including," "having," "containing," and the like are open-ended terms that mean including, but not limited to.

As used herein, "and/or" includes any and all combinations of the described items.

As used herein, the terms "substantially", "about" and the like are used to modify any slight variation in quantity or error that does not alter the nature of the variation. Generally, the range of slight variations or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. It should be understood by those skilled in the art that the aforementioned values can be adjusted according to actual needs, and are not limited thereto.

Certain words used to describe the present application are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art in describing the present application.

The technical scheme provides: as shown in fig. 1, 2 and 5, a liquid initiator structure comprises a gas generating structure 1, a cutting structure 2, a propellant storage structure 3 and a housing structure 4. The shell structure 4 is provided with a gas channel and a liquid medium channel outlet, the gas generating structure 1 is communicated with the gas channel of the shell structure 4, the cutting structure 2 is positioned inside the gas channel of the shell structure 4, the propellant storage structure 3 is fixedly arranged at one side of the shell structure 4, a part for storing propellant is arranged in the shell structure 4 in a matching way with the cutting structure 2, the gas generating structure 1 is used for generating high-temperature gas to push the cutting structure 2 to cut the propellant storage structure 3 positioned in the shell structure 4, a piston is arranged at the inner side of the propellant storage structure 3, the propellant storage structure 3 is used for storing propellant at one side of the piston 33, a first magnet 32 and a second magnet 36 are oppositely arranged at the other side of the piston 33, and the first magnet 32 and the second magnet 36 arranged in the propellant storage structure 3 are mutually repelled (namely the opposite surfaces of the two have the same polarity) after being electrified, the pushing piston 33 presses the propellant stored in the propellant storage structure 3 so that the propellant flows out from the liquid medium passage outlet.

Specifically, the method comprises the following steps: the liquid starter structure consists of a gas generating structure 1, a cutting structure 2, a propellant storage structure 3 and a casing structure 4. The housing structure 4 has a gas passage and a liquid medium passage outlet, and the gas generating structure is in communication with the gas passage of the housing structure 4. Wherein the gas generated by the gas generating structure moves along the gas channel and the liquid propellant stored in the storage structure 3 flows out from the outlet of the liquid medium channel. The cutting structure 2 is located inside the gas passage of the housing structure 4 and the cutting structure 2 sealingly engages the inside of the gas passage so that gas generated by the gas generating structure may push the cutting structure 2 in motion. Propellant storage structure 3 is fixed to be set up in one side of shell structure 4, and the part that is used for storing propellant sets up with cutting structure 2 cooperation in shell structure 4, and gas generation structure 1 is used for producing high temperature gas to promote cutting structure 2 to cut propellant storage structure 3 that is located shell structure 4. The propellant storage structure 3 is provided with a piston inside (the outer diameter edge of the piston sealingly abuts against the inner wall of the storage structure) to confine the propellant to one side of the propellant storage structure 3. The propellant storage structure 3 is used to store propellant on one side of the piston 33 and is provided with a first magnet 32 and a second magnet 36 arranged opposite each other on the other side of the piston 33. Upon energization, the first magnet 32 and the second magnet 36 provided in the propellant storage structure 3 repel each other, pushing the piston 33 to squeeze the propellant so that the propellant flows out from the liquid medium passage outlet. The structure has the advantages of reasonable design, safety and reliability, the starter takes the liquid propellant as the starting source, the defect that a large amount of solid particles are generated during the working of the solid starter to cause valve blockage can be overcome, and the working reliability of the gas pressurization power system is improved.

The utility model discloses a first magnet and second magnet can be the electro-magnet, and after the circular telegram, the two polarity is the same. Or one of the magnets is an electromagnet, the other is a permanent magnet, and the electromagnet is mutually repelled with the permanent magnet after being electrified.

As shown in fig. 1, in order to enable the gas generating structure 1 to generate high temperature quickly, the gas generating structure 1 is designed as an electric squib 11, and the electric squib 11 is communicated with a gas passage at one end of the housing structure 4 in order to facilitate the generated high-temperature gas to flow into the housing structure 4 smoothly.

It is worth mentioning that, as shown in fig. 2, 3 and 4, the cutting structure 2 includes a main body portion 21, a cutting portion 22 and a flow guide portion 23. The propellant storage structure 3 comprises a storage tank 31, the cutting part 22 abuts against the bottom of the storage tank 31, and when the gas generating structure 1 generates high-pressure gas, the cutting part 22 is pushed to move so as to cut the bottom of the storage tank 31, so that the propellant stored in the storage tank 31 enters the liquid medium channel outlet through the diversion part 23.

Specifically, in the present embodiment, the cutting portion 22 includes a channel hole 221 with two ends communicating with each other, in order to facilitate the propellant liquid to flow into the flow guiding portion 23, the flow guiding portion 23 includes a first flow guiding channel 231 and a second flow guiding channel 231 (the first direction is the top view direction of fig. 1) which are opened along the first direction and are arranged at intervals along the moving direction of the cutting structure 2, and the channel hole 221 is located on the first flow guiding channel 231, and the central lines of the two channels are located on the same straight line. That is, the first guide channel 231 includes the channel hole 221 having the larger diameter and the channel hole communicating with the channel hole 221 and having the smaller diameter, so that a boss is formed at the middle of the first guide channel 231, in which case the channel hole 221 of the first guide channel 231 serves to cut the bottom of the tank in addition to the guide function. In order to facilitate cutting of the tank 31 and outflow of the liquid propellant 35, the bottom end of the tank 31 is positioned in the passage hole 221 and is in close contact with the inner wall of the passage hole 221, in which case when the gas generating structure generates gas, the cutting structure 2 is pushed along the gas passage so that the inner wall of the passage hole 221 applies pressure to the bottom of the tank to peel off the bottom thereof and the propellant flows into the liquid medium passage outlet. Note that, in order to effectively support the bottom of the reservoir 31 for cutting, the hole diameter of the passage hole 221 is designed to be larger than the hole diameter of the first guide passage 231 so that the bottom of the reservoir 31 can be supported by the boss. I.e. the aperture of the passage hole 221 is larger than the aperture of the first flow guiding passage 231 at the side of the passage hole 221 facing away from the propellant storage structure 3.

In addition, in order to reduce the weight of cutting structure 2, make things convenient for liquid propellant 35 to flow into main part 21, can be the circular structure with main part 21 both ends appearance design, and the middle part is close to storage tank 31 both sides and is equipped with the plane 211 that sinks, sinks two water conservancy diversion passageways mutually perpendicular of plane 211 and water conservancy diversion portion 23, and the design of the plane 211 that sinks can avoid liquid propellant 35 to prolong the main part 21 surface and flow out, guarantees that shell structure 4 is inside clean and tidy.

In particular, as shown in figures 5, 6 and 7, the propellant storage structure 3 comprises a tank 31, a gasket 34 and a liquid propellant 35. For example, an electromagnet, a permanent magnet, a piston 33, a packing 34 and a liquid propellant 35 are located inside the tank 31. The storage tank 31 is a sealing structure, the electromagnet and the permanent magnet are arranged on one side of the piston in a facing mode, the other side, away from the permanent magnet, of the electromagnet is tightly attached to the inner surface of the upper end of the storage tank, one side, away from the permanent magnet, of the permanent magnet is tightly attached to the piston, and therefore the piston is pushed to move through repulsive force generated between the electrified electromagnet and the permanent magnet. The propellant storage structure 3 is used for storing liquid propellant 35 at the other side of the piston 33, and the sealing ring 34 is sleeved on the outer surface of the piston 33 and is tightly attached to the inner surface of the storage tank 31. The outer edge of the piston 33 is provided with a groove 331, the groove 331 is concave toward the center of the tank 31, and the sealing ring 34 is located in the groove 331 and closely attached to the groove 331. For example, one end of the first magnet 32 is connected to the inside of the tank 31, one end of the second magnet 36 is closely attached to one side of the piston 33, and the other end is spaced apart from and faces the other end of the first magnet 32, and the other end of the piston 33 is used to seal the liquid propellant 35. The sealing ring 34 is sleeved on the outer surface of the piston 33 and is tightly attached to the inner surface of the storage tank 31.

When the bottom of the storage tank 31 is cut, a repulsive force is generated between the energized electromagnet and the permanent magnet to push the piston to move, so that the liquid propellant is squeezed to rapidly flow out of the storage tank 31. In addition, in order to ensure that the sealing ring 34 is tightly connected with the piston 33, a groove 331 is provided on the outer edge of the piston 33, the groove 331 is recessed toward the center of the tank 31, and the sealing ring 34 is located in the groove 331 and is tightly adhered to the groove 331.

In this embodiment, the electromagnet is located above the permanent magnet (in the up-down direction in the figure), and in practical applications, the electromagnet may also be located below the permanent magnet, so as to generate a repulsive force between the energized electromagnet and the permanent magnet to push the piston to move in the first direction, so that the liquid propellant flows out of the storage tank 31 quickly, and the specific process steps are not described one by one here.

It is further noted that, for example, in order to facilitate cutting, tank 31 is composed of first tank 311 and second tank 312, first tank 311 has a larger diameter than second tank 312, and first tank 311 is connected to second tank 312 through circular plate 5 having a through hole. In order to ensure the tightness of the storage tank 31 and avoid the liquid leakage of the liquid propellant 35 in the storage tank 31, the first storage tank 311, the second storage tank 312 and the circular plate 5 are integrally formed. In order to increase the volume and facilitate the installation, the first tank 311 and the second tank 312 are designed to have a cylindrical shape.

It is noted that the housing structure 4, as shown in fig. 1 and 5, includes a housing main body 41, an upper projection column 42, a cone 43 and a lower projection column 44. Upper protruding column 42 and lower protruding column 44 are located the both sides of shell main part 41, and both central lines are located same straight line, and in order to make shell structure 4 be connected more closely with propellant storage structure 3, be equipped with the internal thread in the inboard of upper protruding column 42, propellant storage structure 3 is equipped with the external screw thread, and propellant storage structure 3 is fixed in shell structure 4 through its external screw thread screw in internal thread. The lower raised columns 44 form the liquid medium passage outlets. The cone 43 is positioned at one end of the shell body 41 and is far away from one side of the electric detonator 11 structure, and the cone 43 is used for limiting the cutting structure 2.

When the cutting gas generating structure 1 generates high temperature gas, so as to push the cutting structure 2 to move along the gas passage and cut the second tank 312 located inside the housing structure 4, one end of the cutting structure 2 is in contact with one end of the cone 43 and is limited by the cone 43 during the movement of the cutting structure 2. Since the diameter of the cone 43 is gradually reduced toward the end away from the electric detonator 11, the cutting structure 2 can be effectively limited from moving toward the cone 43. In order to reduce the weight of the cone 43, the interior of the cone 43 may be designed into a cavity structure, the shape of the cavity structure is similar to an isosceles trapezoid, and the large end side is located on the side close to the cutting structure 2, and the small end is located on the side far from the cutting structure 2. It should be further noted that when the cutting structure 2 is limited by the cone 43, the central lines of the storage tank 31 and the second guiding channel 323 are exactly located on the same straight line, so that the liquid propellant can flow out from the outlet of the liquid medium channel along the second guiding channel 323 conveniently.

As shown in fig. 1 and 8, the working principle is as follows: when the gas pressurization power system needs to be started to work, firstly, the electric blasting tube 11 on the liquid starter structure is electrified, and the electric blasting tube 11 fires. The high-pressure gas generated by the electric detonator drives the cutting structure 2 to break and push the bottom of the storage tank 31. When energized, the first magnet 32 and the second magnet 36 disposed in the propellant storage structure 3 repel each other, and the second magnet 36 pushes the piston 33 to squeeze the liquid propellant 34 in the tank 31 into the power system (for example, the energization time may be when the cutting structure has just cut the bottom of the tank, or when the cutting structure moves to a limit position, for example, a travel switch may be disposed in the path of the movement of the cutting structure, and the contact of the cutting structure with the travel switch may send an electrical signal to the electromagnet to energize the electromagnet). At the moment, a stop valve in a pressurization system of the gas pressurization power system is in a closed state, and the propellant is extruded into the gas generating device downstream. The fuel gas generating device decomposes the propellant into high-temperature fuel gas which is filled into the storage tank and a downstream power execution system to finish the starting and pressurization of the power system. Because the initial pressurized gas of the fuel gas pressurization power system is the fuel gas generated by decomposing the liquid propellant when the first magnet liquid starter is used, no solid particle residue exists in the starting process of the power system, and the working reliability of the power system is improved.

The above embodiments may be combined with each other and have corresponding effects.

The foregoing is only an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principles of the present invention should fall within the protection scope of the present invention.

Claims

1. A liquid actuator structure, characterized by: comprises a gas generating structure, a cutting structure, a propellant storage structure and a shell structure; the shell structure is provided with a gas channel and a liquid medium channel outlet, the gas generation structure is communicated with the gas channel of the shell structure, the cutting structure is positioned in the gas channel of the shell structure, the propellant storage structure is fixedly arranged at one side of the shell structure, the part for storing propellant is arranged in the shell structure in a manner of being matched with the cutting structure, the gas generation structure is used for generating high-temperature gas to push the cutting structure to cut the propellant storage structure positioned in the shell structure, a piston is arranged at the inner side of the propellant storage structure, the propellant storage structure is used for storing propellant at one side of the piston, a first magnet and a second magnet are oppositely arranged at the other side of the piston, and the first magnet and the second magnet which are arranged in the propellant storage structure repel each other after being electrified, pushing the piston to squeeze the propellant stored in the propellant storage structure so that the propellant rapidly flows out from the liquid medium passage outlet.

2. The liquid actuator structure of claim 1, wherein: the gas generating structure is an electric explosion tube, and one end of the shell structure is communicated with the gas channel through the electric explosion tube.

3. The liquid actuator structure of claim 1, wherein: the cutting structure comprises a main body part, a cutting part and a flow guide part, the propellant storage structure comprises a storage tank, the cutting part is abutted to the bottom of the storage tank, and when the gas generation structure generates high-pressure gas, the cutting part is pushed to move so as to cut the bottom of the storage tank, so that the propellant stored in the storage tank enters the liquid medium channel outlet through the flow guide part.

4. A liquid actuator construction according to claim 3, wherein: the cutting part comprises a channel hole, the flow guide part comprises a first flow guide channel and a second flow guide channel which are arranged along a first direction at intervals in the movement direction of the cutting structure, the first flow guide channel comprises the channel hole, the central lines of the first flow guide channel and the second flow guide channel are positioned on the same straight line, and one end of the bottom of the storage tank is positioned in the channel hole and is tightly attached to the inner wall of the channel hole.

5. The liquid actuator structure of claim 4, wherein: the aperture of the passage hole is larger than that of the first flow guide passage on the side of the passage hole far away from the storage structure.

6. The liquid actuator structure of claim 4, wherein: the appearance of main part both ends is circular structure, and the middle part is close to the storage tank both sides are equipped with the plane of sinking, the plane of sinking with first direction mutually perpendicular.

7. The liquid actuator structure of claim 1, wherein: the propellant storage structure further comprises a storage tank, a sealing ring and liquid propellant, the first magnet and the second magnet are respectively an electromagnet and a permanent magnet, the electromagnet, the permanent magnet, the piston, the sealing ring and the liquid propellant are located inside the storage tank, the storage tank is a sealing structure, the first magnet and the permanent magnet are arranged on one side of the piston in a facing mode, the other side, far away from the permanent magnet, of the electromagnet is tightly attached to the inner surface of the upper end of the storage tank, one side, far away from the electromagnet, of the permanent magnet is tightly attached to the piston, and therefore the piston is pushed to move by the repulsion force generated between the electromagnet and the permanent magnet which are electrified; the propellant storage structure is used for storing liquid propellant on the other side of the piston, and the sealing ring is sleeved on the outer surface of the piston and is tightly attached to the inner surface of the storage tank; the outer edge of the piston is provided with a groove, the groove is of a structure which is concave towards the center direction of the storage tank, and the sealing ring is located in the groove and is tightly attached to the groove.

8. The liquid actuator structure of claim 7, wherein: the storage tank comprises a first storage tank and a second storage tank, the first storage tank and the second storage tank are in cylindrical structures, the diameter of the first storage tank is larger than that of the second storage tank, and the first storage tank is connected with the second storage tank through a circular plate with a through hole.

9. The liquid actuator structure of claim 2, wherein: the shell structure contains shell main part, goes up protruding post, cone and protruding post down, it is located to go up protruding post and protruding post down the both sides of shell main part, and both central lines are located same straight line, the inboard of going up protruding post is equipped with the internal thread, propellant storage structure is equipped with the external screw thread, propellant storage structure is through its external screw thread screw in the internal thread is fixed in shell structure, protruding post forms down the liquid medium passageway export, the cone is used for right the cutting structure carries on spacingly, the cone is located shell main part one end, and keeps away from electric detonator structure one side.

10. An attitude control power system comprising a liquid actuator structure according to any one of claims 1 to 9.