CN211058922U - Liquid starter equipment and appearance accuse driving system - Google Patents
Liquid starter equipment and appearance accuse driving system Download PDFInfo
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- CN211058922U CN211058922U CN201921452055.0U CN201921452055U CN211058922U CN 211058922 U CN211058922 U CN 211058922U CN 201921452055 U CN201921452055 U CN 201921452055U CN 211058922 U CN211058922 U CN 211058922U
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Abstract
The utility model discloses a liquid starter device 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 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, the piston both sides are equipped with propellant respectively and are used for storing compressed gas's compression chamber, cutting structure cutting behind the propellant storage structure, set up to be in compressed gas inflation in the compression chamber promotes the storage and is in piston extrusion propellant, so that the propellant is followed liquid medium channel outlet flows, compares with prior art, has reasonable in design, improves the reliability of system.
Description
Technical Field
The utility model relates to a liquid rocket gas pressure boost driving system field, in particular to liquid starter equipment 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 equipment and appearance accuse driving system, starter device reasonable in design, 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 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 initiator device comprising a gas generating structure, a cutting structure, a propellant storage structure and a housing 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 inside the gas channel of the shell structure, the propellant storage structure is fixedly arranged on 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 on the inner side of the propellant storage structure, the propellant storage structure is used for storing propellant on one side of the piston, a compression chamber for storing compressed gas is arranged on the other side of the piston, and after the cutting structure cuts the part for storing propellant of the propellant storage structure, compressed gas disposed within the compression chamber expands, pushing the piston to squeeze propellant so that it rapidly exits 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 tank, a gasket and a liquid propellant, the compression chamber, the piston, the gasket and the liquid propellant being located inside the tank, the tank being a sealed structure, the compression chamber being located inside the tank on one side of the piston; the tank is on the other side of the piston for storing liquid propellant; 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 equipment.
Compared with the prior art, the beneficial effects of the utility model are that: a liquid initiator device comprising a gas generating structure, a cutting structure, a propellant storage structure and a housing 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 inside the gas channel of the shell structure, the propellant storage structure is fixedly arranged on 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 on the inner side of the propellant storage structure, the propellant storage structure is used for storing propellant on one side of the piston, a compression chamber for storing compressed gas is arranged on the other side of the piston, and after the cutting structure cuts the part for storing propellant of the propellant storage structure, the compressed gas arranged in the compression chamber expands to push the piston to extrude the propellant, so that the propellant can flow out from the outlet of the liquid medium channel quickly.
Drawings
Fig. 1 is a schematic structural diagram of the initial state of the liquid starter device 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 compression chamber 33 piston
331 groove 34 sealing ring
35 liquid propellant 36 round plate
4 casing structure 41 casing main body
42 upper convex column 43 cone
44 lower protruding column
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.
As shown in fig. 1, 2 and 5, the present solution provides a liquid initiator device comprising a gas generating structure 1, a cutting structure 2, a propellant storage structure 3 and a housing structure 4. Shell structure 4 has gas passage and liquid medium passageway export, gas generating structure 1 communicates shell structure 4's gas passage, cutting structure 2 is located inside shell structure 4's the gas passage, 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, gas generating structure 1 is used for producing high temperature gas, store structure 3 with the propellant that promotes cutting structure 2 cutting to be located shell structure 4. The propellant storage structure 3 is provided with a piston inside, the propellant storage structure 3 being provided with a compression chamber 32 for storing compressed gas on one side of the piston 33 and on the other side of the piston 33. After the cutting structure 2 cuts the propellant-storing part of the propellant storage structure 3, the compressed gas provided in the compression chamber 32 expands, pushing the piston 33 to squeeze the propellant so that the propellant flows out rapidly from the liquid medium passage outlet.
Specifically, the method comprises the following steps: the liquid starter device consists of a gas generating structure 1, a cutting structure 2, a propellant storage structure 3 and a housing 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. The propellant storage structure 3 is fixedly arranged on one side of the housing structure 4, and the part for storing propellant is arranged in the housing structure 4 in cooperation with the cutting structure 2. The gas generating structure 1 is used to generate a high temperature gas to push the cutting structure 2 to cut the propellant storage structure 3 located within the housing structure 4. The propellant storage structure 3 is provided with a piston inside, the propellant storage structure 3 being provided with a compression chamber 32 for storing compressed gas on one side of the piston 33 and on the other side of the piston 33. After the cutting structure 2 cuts the propellant-storing part of the propellant storage structure 3, the compressed gas stored in the compression chamber 32 expands, pushing the piston 33 to squeeze the propellant so that the propellant flows out rapidly 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.
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 passage 231 includes the passage hole 221 having a larger diameter and the passage hole communicating with the passage hole 221 and having a smaller diameter, thereby forming a boss at the middle of the first guide passage 231. In this case, the first flow-guiding channel 231, in addition to its flow-guiding function, has its channel hole 221 also for cutting the bottom of the tank. 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. The passage hole 221 has a larger diameter than the first flow-guiding passage 231 on the side of the passage hole 221 facing away from the propellant storage structure 3.
In addition, in order to reduce the weight of the cutting structure 2 and facilitate the liquid propellant 35 to flow into the main body 21, the shapes of the two ends of the main body 21 may be designed to be circular structures, and the middle part of the main body is provided with sinking planes 211 near the two sides of the storage tank 31, and the sinking planes 211 are perpendicular to the two flow guide channels of the flow guide part 23. The design of the sinking plane 211 prevents the liquid propellant 35 from flowing out along the surface of the main body 21, thereby ensuring a neat interior of the housing structure 4.
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. The compression chamber, the piston, the sealing washer with liquid propellant is located inside the storage tank, the storage tank is seal structure, the compression chamber is located in the storage tank one side of the piston. The tank is on the other side of the piston for storing liquid propellant. 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. The compression chamber 32 is formed by the tank 31 on the upper side of the piston 33 (in the up-down orientation as shown in fig. 5) and the piston 33, the other end of the piston 33 being 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. 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.
Further, as shown in fig. 5 and 7, for example, in order to facilitate cutting, the tank 31 is composed of a first tank 311 and a second tank 312, the first tank 311 has a diameter larger than that of the second tank 312, and the first tank 311 is connected to the second tank 312 through a circular plate 36 having a through hole. In order to ensure the tightness of the tank 31 and avoid liquid leakage of the liquid propellant 35 in the tank 31, the first tank 311, the second tank 312 and the circular plate 36 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. The upper and lower protrusion columns 42 and 44 are located at both sides of the case main body 41, and their center lines are located on the same straight line. In order to make the connection of the housing structure 4 with the propellant storage structure 3 more tight, an internal thread is provided on the inner side of the upper protruding stud 42, the propellant storage structure 3 is provided with an external thread, and the propellant storage structure 3 is fixed to the housing structure 4 by screwing the external thread into the 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 gas generating structure 1 is cut, high temperature gas is generated to push the cutting structure 2 to move along the gas passage and cut the second tank 312 located inside the housing structure 4. During the movement of the cutting structure 2, one end of the cutting structure 2 is in contact with one end of the cone 43 and is limited by the cone 43. 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 stopped by the cone 43 (i.e. when the cutting structure is moved to its extreme position), the center lines of the storage tank 31 and the second diversion channel 323 are exactly aligned, so that the liquid propellant flows out from the liquid medium channel outlet along the second diversion channel 323.
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 detonator 11 on the liquid starter device is electrified, and the electric detonator 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, the compressed gas arranged in the compression chamber 32 expands, the piston 33 is pushed to squeeze the liquid propellant 34, so that the liquid propellant 34 rapidly flows out from the liquid medium channel outlet, and the liquid propellant 34 in the storage tank 31 is squeezed into a power system. 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. When the compression chamber liquid starter is used, the initial pressurized gas of the gas pressurization power system is the gas generated by decomposing the liquid propellant, so that no solid particle residue exists in the starting process of the power system, and the working reliability of the power system is improved.
The utility model also provides a position accuse driving system contains above liquid starter equipment.
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 (10)
1. A liquid actuator device, 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 inside the gas channel of the shell structure, the propellant storage structure is fixedly arranged on 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 on the inner side of the propellant storage structure, the propellant storage structure is used for storing propellant on one side of the piston, a compression chamber for storing compressed gas is arranged on the other side of the piston, and after the cutting structure cuts the part for storing propellant of the propellant storage structure, compressed gas disposed within the compression chamber expands, pushing the piston to squeeze propellant so that it rapidly exits the liquid medium passage outlet.
2. The liquid activator device 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 activator device 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. The liquid activator device of 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 activator device 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 activator device 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 activator device of claim 1, wherein: the propellant storage structure further comprises a storage tank, a sealing ring and liquid propellant, wherein the compression chamber, the piston, the sealing ring and the liquid propellant are positioned inside the storage tank, the storage tank is a sealing structure, and the compression chamber is positioned on one side of the piston in the storage tank; the tank is on the other side of the piston for storing liquid propellant; the sealing ring is sleeved on the outer surface of the piston and is tightly attached to the inner surface of the storage box; 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 activator apparatus 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 activator device 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 apparatus as claimed in any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921452055.0U CN211058922U (en) | 2019-09-03 | 2019-09-03 | Liquid starter equipment and appearance accuse driving system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921452055.0U CN211058922U (en) | 2019-09-03 | 2019-09-03 | Liquid starter equipment and appearance accuse driving system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211058922U true CN211058922U (en) | 2020-07-21 |
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ID=71591233
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921452055.0U Active CN211058922U (en) | 2019-09-03 | 2019-09-03 | Liquid starter equipment and appearance accuse driving system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211058922U (en) |
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2019
- 2019-09-03 CN CN201921452055.0U patent/CN211058922U/en active Active
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