CN110697082B - Attitude control power system - Google Patents
Attitude control power system Download PDFInfo
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- CN110697082B CN110697082B CN201910827043.XA CN201910827043A CN110697082B CN 110697082 B CN110697082 B CN 110697082B CN 201910827043 A CN201910827043 A CN 201910827043A CN 110697082 B CN110697082 B CN 110697082B
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- 238000003860 storage Methods 0.000 claims abstract description 119
- 239000003380 propellant Substances 0.000 claims abstract description 99
- 238000005520 cutting process Methods 0.000 claims abstract description 68
- 239000007788 liquid Substances 0.000 claims abstract description 56
- 238000010438 heat treatment Methods 0.000 claims abstract description 41
- 238000007789 sealing Methods 0.000 claims description 15
- 238000004880 explosion Methods 0.000 claims 2
- 238000013461 design Methods 0.000 abstract description 7
- 239000007789 gas Substances 0.000 description 58
- 239000007787 solid Substances 0.000 description 12
- 239000007858 starting material Substances 0.000 description 9
- 239000002245 particle Substances 0.000 description 6
- 239000002737 fuel gas Substances 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 230000006870 function Effects 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000004064 recycling Methods 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical compound C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 239000002760 rocket fuel Substances 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 230000008016 vaporization Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
- B64G1/245—Attitude control algorithms for spacecraft attitude control
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/401—Liquid propellant rocket engines
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- Engineering & Computer Science (AREA)
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Automation & Control Theory (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention discloses an attitude control power system which comprises a starting unit, a heating unit, a thruster unit and a storage unit, wherein the starting unit comprises a gas generation structure, a cutting structure, a propellant storage structure and a shell structure; the casing structure has medium passageway export, gas generation structure intercommunication casing structure's gas channel, the cutting structure is located casing structure's inside the gas channel, gas generation structure is used for producing high temperature gas, in order to promote cutting structure cutting propellant storage structure, so that the propellant flows out from the liquid medium passageway export, the heating unit is used for heating the propellant that flows out from the liquid medium passageway export, the propellant of heating gives on the one hand the thruster unit, for the thruster unit provides power, on the other hand flows in storage unit through the pipeline and stores, whole system has reasonable in design, safe and reliable.
Description
Technical Field
The invention relates to the field of liquid rocket fuel gas pressurization power systems, in particular to an attitude control power system.
Background
With the rapid development of the aerospace industry, various technologies related to rockets also realize the rapid advance. The functions of the attitude and orbit control power system comprise pitching yaw control, rolling control, orbit keeping, speed correction and the like. As an important component of the attitude control power system, the thruster is a function execution mechanism of the attitude control power system and provides initial starting pressure for a fuel gas pressurization system. At present, when the thruster is started, the thruster is often applied to a starter, and the starter adopts solid charge at present. When solid charge burns, a large amount of solid particles are generated, so that a valve of a power system is blocked, the working reliability of a gas pressurization power system is reduced, and the safe operation of a rocket is influenced.
Therefore, how to provide a reasonable-design, safe and reliable attitude control power system to solve the defect that a large amount of solid particles are generated during the operation of a solid starter to cause valve blockage, and the problem to be solved at present is to improve the operational reliability of a gas pressurization power system.
Disclosure of Invention
The invention aims to provide an attitude control power system which has the advantages of reasonable design, safety and reliability, capability of solving the defect that a large amount of solid particles are generated during the working of a solid starter to cause valve blockage, improvement on the working reliability of a gas pressurization power system and the like.
In order to achieve the purpose, the invention provides the following technical scheme: an attitude control power system comprises a starting unit, a heating unit, a thruster unit and a storage unit, wherein the starting unit, the heating unit, the thruster unit and the storage unit are connected through pipelines, an outlet pipeline of the starting unit is respectively connected with the heating unit and the storage unit, and an outlet pipeline of the heating unit is respectively connected with the thruster unit and the storage unit; the starting unit 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 at one side of the shell structure, the part for storing propellant is arranged in the shell structure in a matching way 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 so that the propellant flows out from the liquid medium channel outlet, the heating unit is used for heating the propellant flowing out from the liquid medium channel outlet, the propellant is gasified, and the gasified propellant is supplied to the thruster unit on the one hand to provide pre-pressure for the thruster unit, on the other hand, the water flows into the storage unit through the pipeline for storage so as to be recycled later.
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, propellant storage structure contains storage tank, spring, piston, sealing washer and liquid propellant, the spring, the piston, the sealing washer with liquid propellant is located inside the storage tank, the storage tank is seal structure, the spring both ends are connected respectively the storage tank with the piston, the piston other end is used for sealed liquid propellant, the sealing washer cover is established the piston surface, and with the storage tank internal surface is hugged closely each other, be equipped with the recess on the outward flange of piston, the recess be to storage tank central direction recessed structure, the sealing washer be located in the recess, and with the recess is hugged closely each other.
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.
Preferably, the heating unit comprises a propellant generating device for heating and gasifying the liquid propellant, the thruster unit provides kinetic energy for the liquid rocket, and the storage unit comprises a storage tank for storing the propellant.
Compared with the prior art, the invention has the beneficial effects that: an attitude control power system comprises a starting unit, a heating unit, a thruster unit and a storage unit, wherein the starting unit, the heating unit, the thruster unit and the storage unit are connected through pipelines, an outlet pipeline of the starting unit is respectively connected with the heating unit and the storage unit, and an outlet pipeline of the heating unit is respectively connected with the thruster unit and the storage unit; the starting unit 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 at one side of the shell structure, the part for storing propellant is arranged in the shell structure in a matching way 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 so that the propellant flows out from the liquid medium channel outlet, the heating unit is used for heating the propellant flowing out from the liquid medium channel outlet, the propellant is gasified, and the gasified propellant is supplied to the thruster unit on the one hand to provide pre-pressure for the thruster unit, on the other hand flows into the storage unit through the pipeline and stores for subsequent cycle use, and the system has reasonable in design, safe and reliable, and the starter uses liquid propellant as the starting source, can solve the solid starter during operation and produce the shortcoming that a large amount of solid particles cause the valve to block up, improves advantages such as the operational reliability of gas pressure boost driving system.
Drawings
FIG. 1 is a schematic structural diagram of an attitude control power system according to the present invention;
FIG. 1A is a schematic structural diagram of an initial state of an attitude control power system according to 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 a 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 a circular plate of the present invention;
FIG. 8 is a perspective view of the cone of the present invention.
Description of reference numerals:
1A Start Unit 2A heating Unit
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 spring 33 piston
331 groove 34 sealing ring
35 liquid propellant 4 shell structure
41 raised column on shell body 42
43 taper 431 big end
432 small end 44 lower protruding column
5 circular plate 6 stop valve
Detailed Description
For the purpose of promoting a clear understanding of the objects, aspects and advantages of the embodiments of the invention, reference will now be made to the drawings and detailed description, wherein there are shown in the drawings and described in detail, various modifications of the embodiments described herein, and other embodiments of the invention will be apparent to those skilled in the art.
The exemplary embodiments of the present invention and the description thereof are provided to explain the present invention and 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 sequence, nor are they used to limit the present 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, fig. 1A, fig. 2 and fig. 5, an attitude control power system includes a starting unit 1A, a heating unit 2A, a thruster unit 3A and a storage unit 4A, the starting unit 1A, the heating unit 2A, the thruster unit 3A and the storage unit 4A are connected through pipelines, wherein an outlet pipeline of the starting unit 1A is respectively connected with the heating unit 2A and the storage unit 4A, and an outlet pipeline of the heating unit 2A is respectively connected with the thruster unit 3A and the storage unit 4A; the starting unit 1A 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, and 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 so that the propellant flows out from the liquid medium channel outlet, the heating unit 2A is used for heating the propellant flowing out from the liquid medium channel outlet to gasify the propellant, the gasified propellant is supplied to the thruster unit 3A on one hand to provide pre-pressing for the thruster unit 3A on the other hand, and flows into the storage unit 4A through a pipeline to be stored on the other hand, for subsequent recycling.
Specifically, the method comprises the following steps: the attitude control power system comprises a starting unit 1A, a heating unit 2A, a thruster unit 3A and a storage unit 4A, wherein the starting unit 1A, the heating unit 2A, the thruster unit 3A and the storage unit 4A are connected through pipelines, and the starting unit 1A comprises a gas generation structure 1, a cutting structure 2, a propellant storage structure 3 and a shell structure 4. Wherein, the outlet pipeline of the starting unit 1A is respectively connected with the heating unit 2A and the storage unit 4A, and the outlet pipeline of the heating unit 2A is respectively connected with the thruster unit 3A and the storage unit 4A. 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 on one side of the shell structure 4, and 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 so that the propellant flows out from the liquid medium channel outlet, the heating unit 2A is used for heating the propellant flowing out from the liquid medium channel outlet to gasify the propellant, the gasified propellant is supplied to the thruster unit 3A on one hand to provide prepressing for the thruster unit 3A on the other hand, and flows into the storage unit 4A through a pipeline to be stored on the other hand, for subsequent recycling. The system 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, so as 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 232 (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. 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 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 spring 32, a piston 33, a sealing ring 34 and a liquid propellant 35. The spring 32, piston 33, sealing ring 34 and liquid propellant 35 are located inside the tank 31. The storage tank 31 is a sealed structure, two ends of the spring 32 are respectively connected with the storage tank 31 and the piston 33, and the other end of the piston 33 is used for sealing 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 tank 31 is cut open, the spring 32, which is in a compressed state, expands to urge the piston in a first direction, causing a rapid flow of liquid propellant to the 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.
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.
As shown in fig. 1 and 8, 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 stopped 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 axial section 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 away from the cutting structure 2. For example, the outer diameter of the cutting structure 2 far from the end of the electric detonator may be slightly smaller than the inner diameter of the large end of the cavity structure, and as the cutting structure 2 enters the vertebral body 43 from the large end and continues to move to the small end, the cutting structure 2 is limited by the vertebral body 43 with gradually decreasing inner dimension, so that the cutting structure 2 stops at the position where the flow guide part is communicated with the liquid medium outlet channel, it needs to be further explained that when the cutting structure 2 is limited by the conical body 43, the center lines of the storage tank 31 and the second flow guide channel 232 are exactly located on the same straight line, and the liquid propellant can conveniently flow out from the liquid medium outlet along the second flow guide channel 232.
In the present embodiment, as shown in fig. 1A, the heating unit 2A includes a propellant generating device for heating and vaporizing a liquid propellant, the thruster unit 3A supplies kinetic energy to the liquid rocket, and the storage unit 4A includes a tank for storing the propellant. It is to be noted that in order to avoid propellant in the starting unit 1A from directly entering the storage unit 4A, a shut-off valve 6 is provided in the line between the starting unit 1A and the storage unit 4A.
As shown in fig. 1A and fig. 1, 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 attitude control power system is electrified, and the electric detonator 11 fires. The high-pressure gas generated by the electric detonator 11 drives the cutting structure 2 to break and push the bottom of the storage tank 31, the spring 32 pushes the piston 33 to extrude the liquid propellant 34 in the storage tank 31 into the power system, at the moment, the stop valve 6 in the 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 propellant is decomposed into high-temperature fuel gas by the fuel gas generating device, and the high-temperature fuel gas is filled into the storage tank and the downstream dynamic thruster unit 3A to finish the starting pressurization of the power system. When the spring liquid starter is used, the initial pressurizing gas of the gas pressurizing 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 foregoing is merely 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 principle of the present invention should fall within the protection scope of the present invention.
Claims (9)
1. An attitude control power system is characterized in that: the device comprises a starting unit, a heating unit, a thruster unit and a storage unit; the starting unit, the heating unit, the thruster unit and the storage unit are connected through pipelines, wherein an outlet pipeline of the starting unit is respectively connected with the heating unit and the storage unit, and an outlet pipeline of the heating unit is respectively connected with the thruster unit and the storage unit; the starting unit 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, a part for storing propellant is arranged in the shell structure in a matching way with the cutting structure, and 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 so that the propellant flows out from the liquid medium channel outlet; the heating unit is used for heating the propellant flowing out of the liquid medium channel outlet so as to gasify the propellant, the gasified propellant provides pre-pressure for the thruster unit on one hand, and flows into the storage unit through a pipeline to be stored on the other hand, so that the propellant can be recycled later; 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.
2. The attitude control power system according to 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 attitude control power system according to claim 1, 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.
4. The attitude control power system according to claim 3, wherein: the aperture of the channel hole is larger than that of the first flow guide channel.
5. The attitude control power system according to claim 3, 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.
6. The attitude control power system according to claim 1, wherein: propellant storage structure contains storage tank, spring, piston, sealing washer and liquid propellant, the spring, the piston, the sealing washer with liquid propellant is located inside the storage tank, the storage tank is seal structure, the spring both ends are connected respectively the storage tank with the piston, the piston other end is used for sealed liquid propellant, the sealing washer cover is established the piston surface, and with the storage tank internal surface is hugged closely each other, be equipped with the recess on the outward flange of piston, the recess be to the recessed structure of storage tank central direction, the sealing washer is located in the recess, and with the recess is hugged closely each other.
7. The attitude control power system according to claim 6, characterized in that: the storage tank comprises a first storage tank and a second storage tank, the first storage tank and the second storage tank are of cylindrical structures in appearance, 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.
8. The attitude control power system according to 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.
9. The attitude control power system according to claim 1, wherein: the heating unit comprises a propellant generating device used for heating and gasifying the liquid propellant, the thruster unit provides kinetic energy for the liquid rocket, and the storage unit comprises a storage tank used for storing the propellant.
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| CN110697082B true CN110697082B (en) | 2021-04-16 |
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| GB1513760A (en) * | 1975-12-18 | 1978-06-07 | Adachi K | Fluid flow control valve for a liquid fuel rocket and a liquid fuel rocket including such a valve |
| US6113032A (en) * | 1998-02-25 | 2000-09-05 | Kistler Aerospace Corporation | Delivering liquid propellant in a reusable booster stage |
| CN101445160A (en) * | 2008-12-23 | 2009-06-03 | 中国科学院广州能源研究所 | Micro liquid fuel propulsion system used in micro-nano satellite |
| CN101865321B (en) * | 2010-07-08 | 2012-01-11 | 中国航天科技集团公司第六研究院第十一研究所 | Diaphragm cutting type electric explosion valve |
| CN202500675U (en) * | 2011-12-30 | 2012-10-24 | 中国航天科技集团公司第六研究院第十一研究所 | High-pressure-resistant starting box based on non-metallic capsule |
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| CN105422317A (en) * | 2015-12-09 | 2016-03-23 | 西安航天动力研究所 | Starting box type multi-time starting system for engine and starting method |
| RU2671449C2 (en) * | 2016-12-28 | 2018-10-31 | Акционерное общество "НПО Энергомаш имени академика В.П. Глушко" | Ampoule with starting fuel for ignition of fuel components of liquid fuel rocket engine |
| CN107218850B (en) * | 2017-06-09 | 2018-09-18 | 北京空间飞行器总体设计部 | A kind of piston type explosion acting device encapsulating method |
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