CN117341994B - Cold air pushing system and cold air pushing method - Google Patents
Cold air pushing system and cold air pushing method Download PDFInfo
- Publication number
- CN117341994B CN117341994B CN202311349662.5A CN202311349662A CN117341994B CN 117341994 B CN117341994 B CN 117341994B CN 202311349662 A CN202311349662 A CN 202311349662A CN 117341994 B CN117341994 B CN 117341994B
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- 238000000034 method Methods 0.000 title claims abstract description 13
- 238000004880 explosion Methods 0.000 claims abstract description 20
- 229910001220 stainless steel Inorganic materials 0.000 claims description 7
- 239000010935 stainless steel Substances 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 3
- 230000001502 supplementing effect Effects 0.000 abstract description 13
- 238000000926 separation method Methods 0.000 abstract description 4
- 238000003466 welding Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000006978 adaptation Effects 0.000 description 2
- 238000005474 detonation Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000002955 isolation Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000001052 transient effect Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 230000035699 permeability Effects 0.000 description 1
Classifications
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention relates to the technical field of rocket separation, in particular to a cold air pushing system and a cold air pushing method. The system is installed in a rocket bay, the system comprising: the four pushing devices are uniformly distributed in the circumferential direction of the rocket cabin section, the gas cylinders are connected with the pushing devices, the gas charging valves, the high-pressure explosion valves and the pressure sensors through pipelines, and a plurality of multi-way pipes are arranged on the pipelines. The invention utilizes the plurality of pushing devices uniformly distributed in the circumferential direction of the rocket cabin section, so that the gas in the pipeline has the same air supplementing quantity when the pushing devices work at the moment of working, and the pushing devices do not work to generate thrust deviation due to different air supplementing quantities in the pipeline.
Description
Technical Field
The invention relates to the technical field of rocket separation, in particular to a cold air pushing system and a cold air pushing method.
Background
The carrier rocket needs to be separated among stages in the flight process, and a cold air thrust system is adopted in the stage section of the rocket in order to ensure the reliable separation of the stages. The cold air pushing system charges the air cylinder through controlling the air stored in the high-pressure air cylinder through the valve, and the air cylinder utilizes the expansion work of the air to generate pushing force so as to separate the front sub-stage from the rear sub-stage. The existing cold air pushing system is unreasonable in layout, so that the air supplementing quantity in the pipeline is different, and further the air cylinder works to generate thrust deviation, so that the separation effect is affected.
Disclosure of Invention
The invention aims to provide a cold air pushing system and a cold air pushing method, so as to solve the problem that the existing cold air pushing system generates thrust deviation.
In order to solve the technical problems, the technical scheme of the invention is as follows:
a cold air thrust system mounted in a rocket pod segment, comprising: the rocket cabin comprises a plurality of pushing devices, a gas cylinder, an inflation valve, a high-pressure explosion valve and a pressure sensor, wherein the pushing devices are uniformly distributed in the circumferential direction of the rocket cabin section, the gas cylinder is connected with the pushing devices, the inflation valve, the high-pressure explosion valve and the pressure sensor through pipelines, and a plurality of multi-way pipelines are arranged on the pipelines.
Further, the pushing device comprises a first pushing cylinder, a second pushing cylinder, a third pushing cylinder and a fourth pushing cylinder, the tee joint is arranged on the pipelines between the first pushing cylinder and the second pushing cylinder and between the third pushing cylinder and the fourth pushing cylinder.
Further, a plurality of the thrust devices are spaced 90 degrees apart from each other.
Further, the multiple passes include five passes, which are located on the pipeline between the three passes.
Further, a ground test port is arranged on the five-way pipe.
Further, the multi-way valve comprises a four-way valve, and the inflation valve, the gas cylinder and the pressure sensor are all connected with the four-way valve through pipelines.
Further, the high-pressure explosion valve is positioned on a pipeline between the four-way valve and the five-way valve.
Further, a pressure sensor is connected to the five-way valve.
Further, the pipeline is made of stainless steel.
According to another aspect of the present invention, there is provided a cold air thrust method, employing the cold air thrust system as set forth in any one of the above, comprising:
inflating the gas cylinder by using the inflation valve;
the high-pressure explosion valve is detonated and opened;
the gas is conveyed to a plurality of pushing devices through the pipeline;
and the plurality of pushing devices expand to do work to generate thrust, so that the rocket is separated.
The scheme of the invention at least comprises the following beneficial effects:
according to the scheme, the plurality of pushing devices uniformly distributed in the circumferential direction of the rocket cabin section are utilized, so that the gas in the pipeline has the same gas supplementing amount when the pushing devices work at the moment of working, and the pushing devices do not work to generate thrust deviation due to different gas supplementing amounts in the pipeline.
Drawings
FIG. 1 is a schematic diagram of a cold air push flushing system in accordance with an embodiment of the present invention;
fig. 2 is a step diagram of a cold air pushing method according to an embodiment of the present invention.
Reference numerals illustrate: 1-gas cylinder, 2-inflation valve, 3-high pressure explosion valve, 4-pressure sensor, 5-pipeline, 51-five-way outlet pipeline, 52-three-way outlet pipeline, 61-first thrust cylinder, 62-second thrust cylinder, 63-third thrust cylinder, 64-fourth thrust cylinder, 71-three-way, 72-five-way, 721-ground test port and 73-four-way.
Detailed Description
Exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present invention are shown in the drawings, it should be understood that the present invention may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
As shown in fig. 1, an embodiment of the present invention proposes a cool air thrust system installed in a rocket bay (not shown in fig. 1), comprising: the rocket cabin comprises a plurality of pushing devices, a gas cylinder 1, an inflation valve 2, a high-pressure explosion valve 3 and a pressure sensor 4, wherein the pushing devices are uniformly distributed in the circumferential direction of the rocket cabin section, the gas cylinder 1 is connected with the pushing devices, the inflation valve 2, the high-pressure explosion valve 3 and the pressure sensor 4 through a pipeline 5, and a plurality of multi-way pipes are arranged on the pipeline 5.
According to the cool air pushing system provided by the embodiment of the invention, the plurality of pushing devices uniformly distributed in the circumferential direction of the rocket cabin section are utilized, so that the gas in the pipeline has the same air supplementing quantity when the pushing devices work at the moment of working, and the pushing devices do not work to generate thrust deviation due to different air supplementing quantities in the pipeline.
In an alternative embodiment of the present invention, as shown in fig. 1, there are four pushing devices, which are respectively a first pushing cylinder 61, a second pushing cylinder 62, a third pushing cylinder 63 and a fourth pushing cylinder 64, and the four pushing cylinders are uniformly distributed along the circumferential direction of the rocket cabin section and are mutually spaced by 90 °. The device can ensure that the gas in the pipeline has the same air supplementing quantity in the working transient gas expansion working process of the pushing cylinder, so that the pushing force generated by the pushing cylinder in working is the same in magnitude, and the pushing deviation is reduced. In the specific implementation, the pushing devices can also be tables, which are mutually separated by 120 degrees, or more pushing devices are uniformly distributed along the circumferential direction of the rocket cabin section.
As shown in fig. 1, in the embodiment, the multi-way valve includes a three-way valve 71, and the three-way valve 71 is disposed on the pipeline 5 between the first pushing cylinder 61 and the second pushing cylinder 62, and between the third pushing cylinder 63 and the fourth pushing cylinder 64.
The tee joint has three access & exit, can realize two pushing away towards cylinder and gas cylinder and together with, make things convenient for the gas to pass through the pipeline evenly and get into a plurality of pushing away towards cylinder of many pipelines, not only be favorable to simplifying the system structure, can also guarantee that a plurality of pushing away towards cylinder during operation produces pushing away the impulsive force size the same, reduces the thrust deviation, can also reduce pipeline welding seam and interface.
In an alternative embodiment of the invention, as shown in fig. 1, the multiple pass includes a five pass 72, the five pass 72 being located on the line 5 between the three-way valves. The five-way pipe 72 is provided with a ground test port 721.
Five inlets and outlets are formed in the five-way pipe, two pipelines leading to the pushing cylinder, one pipeline leading to the gas cylinder, one pressure sensor are respectively connected, a ground test port is formed in the other inlet and outlet, and the ground test port is used for a connection port of the ground pipeline in the air tightness test after assembly. The five-way connection is beneficial to simplifying the system structure and reducing the welding seams and interfaces of the pipelines.
In an alternative embodiment of the present invention, as shown in fig. 1, the manifold includes a four-way 73, and the inflation valve 2, the gas cylinder 1, and the pressure sensor 4 are all connected to the four-way 73 through a pipe 5.
The four-way valve is provided with four inlets and outlets which are respectively connected with the gas cylinder, the pressure sensor, the inflation valve and the five-way valve, and a plurality of pipelines and devices are connected through the four-way valve, so that the system structure is simplified, and the pipeline welding seams and interfaces are reduced.
In an alternative embodiment of the invention, as shown in fig. 1, the high pressure explosion valve 3 is located on the line 5 between the four-way 73 and the five-way 72.
The high-pressure explosion valve is used for realizing physical isolation between high-pressure gas in the gas cylinder and the downstream thrust cylinder when the system does not work, and is beneficial to improving the safety and reliability of the system.
In an alternative embodiment of the present invention, as shown in fig. 1, the five-way switch 72 is connected to the pressure sensor 4.
The system is provided with two pressure sensors, one is arranged at one inlet and outlet of the four-way valve, the system pressure before detonation of the high-pressure explosion valve is monitored, and if the pressure at the gas cylinder is lower than the rated working pressure before the rocket takes off, corresponding air supplementing is carried out; and the inlet and outlet is arranged on the five-way valve, and the system pressure after the detonation of the high-pressure explosion valve is monitored.
In an alternative embodiment of the present invention, the material of the pipe 5 is stainless steel.
The stainless steel has the advantages of corrosion resistance, good permeability resistance, no color change, long service life, low temperature resistance, fire resistance, heat resistance, high temperature resistance, good impact resistance and the like, and the pipeline made of the stainless steel can not only prolong the service life of the system, but also improve the safety and the reliability of the system.
Referring to fig. 1, a specific embodiment of a cold air thrust system according to an embodiment of the present invention is:
according to the requirements of tasks and structural mass centers, four pushing air cylinders are adopted in the inter-stage section and are uniformly distributed along the circumferential direction of the rocket cabin section, and the mutual intervals are 90 degrees. For convenience of description of the layout of the piping 5, the upper right side of fig. 1 is defined as the I-th quadrant, the upper left side is defined as the II-th quadrant, the lower left side is defined as the III-th quadrant, and the lower right side is defined as the IV-th quadrant. The pipelines between the first pushing cylinder 61 and the second pushing cylinder 62, and between the third pushing cylinder 63 and the fourth pushing cylinder 64 are all connected by a tee 71, and the pipeline connected by two inlets and outlets of the tee 71 can be used as a tee outlet pipeline 52. A pipe line is also connected between the two tee-joints 71, and a five-way pipe 72 is provided on the pipe line, so that the pipe line can be used as a five-way outlet pipe line 51. One of the inlets and outlets of the five-way pipe 72 is connected with a pressure sensor 4, and one of the inlets and outlets is set as a ground test port 721 which is used for connecting a ground pipeline in the air tightness test after assembly. The five-way valve 72 is also provided with an inlet and an outlet which are connected with the charging valve 2 through a pipeline, and the section of pipeline is also provided with a high-pressure explosion valve 3, wherein the high-pressure explosion valve 3 is used for realizing the physical isolation between the high-pressure gas in the gas cylinder 1 and four downstream pushing cylinders when the system does not work. The four-way valve 73 is arranged on a pipeline of the charging valve 2 connected with the gas cylinder 1, and the charging valve 2 is used for charging the gas cylinder 1. The inlet and outlet of the four-way valve 73 are respectively connected with the charging valve 2, the gas cylinder 1, the high-pressure explosion valve 3 and the pressure sensor 4. Two pressure sensors 4 are used to monitor the system pressure.
Wherein, five-way 72 is set in quadrant I, two five-way outlet pipes 51 are symmetrically arranged relative to the reference plane of quadrant I-III, and gas is conveyed to tee joint 71 positioned in quadrant II and quadrant III through five-way outlet pipes 51; four three-way outlet pipes 52 are arranged in pairs opposite to the reference planes of the quadrants II-IV respectively. The tee 71 of quadrants II and III delivers gas to the four thrust cylinders through tee outlet line 52.
The material of the various pipes in this embodiment is stainless steel, and the brand of the pipes may be 1Cr18Ni9Ti (austenitic heat-resistant stainless steel).
In order to ensure that the gas in the pipeline has the same air supplementing amount in the working transient gas expansion working process of the air cylinders, the air supplementing amount of the four air cylinders is ensured to be the same through the symmetrical layout of the system pipeline, and the pushing force generated in working is the same. Through setting up a plurality of multitooms, reduce pipeline welding seam and interface, simplify system structure and reduce the realization degree of difficulty.
As shown in fig. 2, an embodiment of the present invention provides a cold air pushing method, which adopts the cold air pushing system according to any one of the above embodiments, and includes the following steps:
s1, receiving a control instruction;
s2, controlling the inflation valve 2 to inflate the gas cylinder 1 according to the control instruction; so that the high-pressure explosion valve 3 is detonated and opened; the gas is delivered to a plurality of pushing devices through the pipeline 5; and the plurality of pushing devices expand to do work to generate thrust, so that the rocket is separated.
In particular, in S2, the gas is delivered through the five-way outlet line 51 to the tee 71 located in quadrant II and quadrant III; the tee 71 of the second quadrant and the third quadrant delivers the gas to 4 pushing cylinders through the tee outlet pipeline 52; each thrust cylinder expands to do work to generate thrust, so that the rocket is separated.
According to the cool air pushing method, the plurality of pushing devices which are uniformly distributed in the circumferential direction of the rocket cabin section are utilized, so that the gas in the pipeline has the same air supplementing quantity when the pushing devices work at the moment of working, and the pushing devices do not work to generate thrust deviation due to different air supplementing quantities in the pipeline.
While the foregoing is directed to the preferred embodiments of the present invention, it will be appreciated by those skilled in the art that various modifications and adaptations can be made without departing from the principles of the present invention, and such modifications and adaptations are intended to be comprehended within the scope of the present invention.
Claims (3)
1. A cold air thrust system installed in a rocket pod segment, comprising: the rocket cabin comprises a plurality of pushing devices, a gas cylinder (1), an inflation valve (2), a high-pressure explosion valve (3) and a pressure sensor (4), wherein the pushing devices are uniformly distributed in the circumferential direction of the rocket cabin section, the gas cylinder (1) is connected with the pushing devices, the inflation valve (2), the high-pressure explosion valve (3) and the pressure sensor (4) through a pipeline (5), and a plurality of multi-way pipelines are arranged on the pipeline (5);
the pushing device comprises a first pushing cylinder (61), a second pushing cylinder (62), a third pushing cylinder (63) and a fourth pushing cylinder (64), the multipass comprises a tee joint (71), and the tee joint (71) is arranged on a pipeline (5) between the first pushing cylinder (61) and the second pushing cylinder (62) and between the third pushing cylinder (63) and the fourth pushing cylinder (64);
the pushing devices are mutually spaced by 90 degrees;
the multi-way valve comprises five-way valves (72), and the five-way valves (72) are positioned on a pipeline (5) between the three-way valves;
a ground test port (721) is arranged on the five-way pipe (72);
the multi-way valve comprises a four-way valve (73), and the charging valve (2), the gas cylinder (1) and the pressure sensor (4) are all connected with the four-way valve (73) through a pipeline (5);
the high-pressure explosion valve (3) is positioned on a pipeline (5) between the four-way valve (73) and the five-way valve (72);
the five-way valve (72) is connected with a pressure sensor (4).
2. Cold air thrust system according to claim 1, characterized in that the material of the pipe (5) is stainless steel.
3. A cold air thrust method employing the cold air thrust system of any one of claims 1-2, comprising:
receiving a control instruction;
according to the control instruction, the inflation valve (2) is controlled to inflate the gas cylinder (1); so that the high-pressure explosion valve (3) is detonated and opened; the gas is conveyed to a plurality of pushing devices through the pipeline (5); and the plurality of pushing devices expand to do work to generate thrust, so that the rocket is separated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311349662.5A CN117341994B (en) | 2023-10-18 | 2023-10-18 | Cold air pushing system and cold air pushing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311349662.5A CN117341994B (en) | 2023-10-18 | 2023-10-18 | Cold air pushing system and cold air pushing method |
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| Publication Number | Publication Date |
|---|---|
| CN117341994A CN117341994A (en) | 2024-01-05 |
| CN117341994B true CN117341994B (en) | 2024-03-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311349662.5A Active CN117341994B (en) | 2023-10-18 | 2023-10-18 | Cold air pushing system and cold air pushing method |
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| Country | Link |
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| CN (1) | CN117341994B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05256197A (en) * | 1992-03-11 | 1993-10-05 | Nissan Motor Co Ltd | Rocket thrust direction control device |
| US6968673B1 (en) * | 2003-11-14 | 2005-11-29 | Knight Andrew F | Cool gas generator and ultra-safe rocket engine |
| DE102010063452A1 (en) * | 2010-12-17 | 2012-06-21 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Cooled system, which is exposed to hot gas flow, comprises wall and a cooling device integrated at least partially in the wall, which is made of a porous material in a partial region and is cooled by transpiration and/or effusion cooling |
| CN104895698A (en) * | 2015-05-19 | 2015-09-09 | 西北工业大学 | Boosting structure of large-pipe-diameter pulse detonation rocket engine and control method thereof |
| CN108869100A (en) * | 2018-07-03 | 2018-11-23 | 北京航空航天大学 | Separation pushes away solid-liquid rocket and rocket auxiliary braking system with counter |
| CN110816901A (en) * | 2019-12-19 | 2020-02-21 | 北京中科宇航探索技术有限公司 | Rocket cabin section separation system and rocket |
| CN111361764A (en) * | 2020-04-16 | 2020-07-03 | 北京宇航推进科技有限公司 | Integrated gas circuit combined system |
| CN111605740A (en) * | 2020-04-28 | 2020-09-01 | 北京控制工程研究所 | Anode structure of electric arc thruster |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100390397C (en) * | 2005-04-30 | 2008-05-28 | 张鸿元 | Air compression aeroengine |
-
2023
- 2023-10-18 CN CN202311349662.5A patent/CN117341994B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05256197A (en) * | 1992-03-11 | 1993-10-05 | Nissan Motor Co Ltd | Rocket thrust direction control device |
| US6968673B1 (en) * | 2003-11-14 | 2005-11-29 | Knight Andrew F | Cool gas generator and ultra-safe rocket engine |
| DE102010063452A1 (en) * | 2010-12-17 | 2012-06-21 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Cooled system, which is exposed to hot gas flow, comprises wall and a cooling device integrated at least partially in the wall, which is made of a porous material in a partial region and is cooled by transpiration and/or effusion cooling |
| CN104895698A (en) * | 2015-05-19 | 2015-09-09 | 西北工业大学 | Boosting structure of large-pipe-diameter pulse detonation rocket engine and control method thereof |
| CN108869100A (en) * | 2018-07-03 | 2018-11-23 | 北京航空航天大学 | Separation pushes away solid-liquid rocket and rocket auxiliary braking system with counter |
| CN110816901A (en) * | 2019-12-19 | 2020-02-21 | 北京中科宇航探索技术有限公司 | Rocket cabin section separation system and rocket |
| CN111361764A (en) * | 2020-04-16 | 2020-07-03 | 北京宇航推进科技有限公司 | Integrated gas circuit combined system |
| CN111605740A (en) * | 2020-04-28 | 2020-09-01 | 北京控制工程研究所 | Anode structure of electric arc thruster |
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| Publication number | Publication date |
|---|---|
| CN117341994A (en) | 2024-01-05 |
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