CN113002808A - Rocket blowing centralized gas supply system - Google Patents
Rocket blowing centralized gas supply system Download PDFInfo
- Publication number
- CN113002808A CN113002808A CN202110178075.9A CN202110178075A CN113002808A CN 113002808 A CN113002808 A CN 113002808A CN 202110178075 A CN202110178075 A CN 202110178075A CN 113002808 A CN113002808 A CN 113002808A
- Authority
- CN
- China
- Prior art keywords
- rocket
- blowing
- arrow
- orifice plate
- supply system
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000007664 blowing Methods 0.000 title claims abstract description 25
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 24
- 230000006837 decompression Effects 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 25
- 238000012423 maintenance Methods 0.000 description 3
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 229910001873 dinitrogen Inorganic materials 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G5/00—Ground equipment for vehicles, e.g. starting towers, fuelling arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D1/00—Pipe-line systems
- F17D1/02—Pipe-line systems for gases or vapours
- F17D1/04—Pipe-line systems for gases or vapours for distribution of gas
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D1/00—Pipe-line systems
- F17D1/20—Arrangements or systems of devices for influencing or altering dynamic characteristics of the systems, e.g. for damping pulsations caused by opening or closing of valves
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D3/00—Arrangements for supervising or controlling working operations
- F17D3/01—Arrangements for supervising or controlling working operations for controlling, signalling, or supervising the conveyance of a product
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Pressure Circuits (AREA)
Abstract
The invention provides a rocket blowing centralized gas supply system, which comprises: the device comprises an air source, a pressure reducer, a manual switch, a normally open electromagnetic valve, a ground orifice plate, an arrow pipeline joint and a plurality of arrow upper orifice plates; the invention relates to a pipeline throttling device, which comprises a pressure reducer, a gas source outlet, a pressure reducer outlet, a normally-closed electromagnetic valve, a ground throttling orifice plate, an arrow pipeline joint and a plurality of arrow upper throttling orifice plates.
Description
Technical Field
The invention relates to a rocket blowing centralized gas supply system.
Background
Fig. 2 is a schematic diagram of a conventional rocket blowing gas supply system. When a traditional air supply system is designed, each blowing air supply can be decompressed to design pressure through a decompressor in a two-stage or three-stage decompression mode and then supplied to an arrow body. Under the design guidance, the ground air supply system is complex and large, the number of pipelines for connecting the arrow body and the ground is large, and the use and maintenance cost is high. The use of novel carrier rocket and low temperature liquid oxygen kerosene engine, liquid oxygen liquid hydrogen engine all need a large amount of blowdown gas to maintain the guarantee, and ground gas supply system is more and more huge, and is more and more complicated, need consume a large amount of time and manpower and materials in the rocket launch test process and be used for the maintenance and the detection of ground gas supply equipment.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the rocket blowing centralized gas supply system is provided, the ground gas supply system is simplified, the number of rocket ground connecting pipelines is reduced, ground equipment is optimized, and the use and maintenance work of the pipelines is optimized.
The technical scheme adopted by the invention is as follows: a rocket blowing centralized gas supply system, comprising: the device comprises an air source, a pressure reducer, a manual switch, a normally open electromagnetic valve, a ground orifice plate, an arrow pipeline joint and a plurality of arrow upper orifice plates;
the air source outlet is connected with the pressure reducer inlet, the pressure reducer outlet is connected with the normally open type electromagnetic valve inlet through a manual switch, the normally open type electromagnetic valve outlet is connected with the ground throttling orifice plate, the ground throttling orifice plate is connected with the arrow pipeline joint, and the arrow pipeline joint is connected with the throttling orifice plates on a plurality of arrows respectively.
The pressure reducer is a constant pressure reducer, and is used for reducing the pressure of a changed gas source and stabilizing the pressure in a set range, and controlling the pressure to be about 23-25 MPa.
The normally-closed electromagnetic valve is connected with the air supply passage when being electrified and disconnected when being powered off, and is used for controlling the on-off of the blowing air passage.
After the pressure reducer reduces the pressure of the gas output by the gas source, the gas is subjected to first throttling and pressure reduction through the ground throttling orifice plate, enters the rocket body, and is subjected to second throttling and pressure reduction through the corresponding rocket upper throttling orifice plate according to the gas supply requirement, and then the part required to be blown is blown.
Compared with the prior art, the invention has the advantages that:
the invention is applied to the carrier rocket launching preparation phase in the aerospace field to carry out the gas blowing and removing guarantee on products such as engines, valves and the like, and is particularly suitable for low-temperature liquid rockets with larger gas blowing and removing requirements. Compared with the prior art, each blowing-off air supply needs to be separately matched with a manual switch, a pressure reducer and an electromagnetic valve, and the ground air distribution table is relatively complex, while the number of the arrow pipe pipelines butted by adopting the invention can be reduced from 3 routes to 1 route, so that the inserting and pulling connectors on the arrow can be optimized, and the ground air supply and distribution pipelines can be reduced.
Drawings
FIG. 1 is a rocket blowing centralized gas supply system provided by the present invention;
wherein, 1-gas source, 2-pressure reducer, 3-manual switch, 4-normal-way electromagnetic valve, 5-ground orifice plate, 6-arrow pipeline joint, 7-first arrow upper orifice plate, 8-second arrow upper orifice plate, 9-third arrow upper orifice plate
Fig. 2 shows a conventional rocket blowing gas supply system.
Detailed Description
To better illustrate the present invention, a preferred embodiment will be described in detail with reference to the accompanying drawings.
Example (b):
fig. 1 is a schematic diagram of a rocket blowing centralized gas supply system provided by the invention.
A rocket blowing centralized gas supply system, comprising: the device comprises an air source 1, a pressure reducer 2, a manual switch 3, a normally-closed electromagnetic valve 4, a ground orifice plate 5, an arrow pipeline joint 6, a first arrow-mounted orifice plate 7, a second arrow-mounted orifice plate 8 and a third arrow-mounted orifice plate 9;
1 export of air supply and 2 access connections of pressure reducer, 2 exports of pressure reducer pass through hand switch 3 and 4 access connections of normal general formula solenoid valve, 4 exports of normal general formula solenoid valve are connected with ground orifice plate 5, ground orifice plate 5 again with arrow pipe joint 6 access connection, arrow pipe joint 6 respectively with throttle plate 7 on the first arrow, throttle plate 8 on the second arrow, throttle plate 9 is connected on the third arrow, constitute 3 air feed branches.
The normal-way electromagnetic valve 4 is connected with the air supply passage when being powered on and disconnected when being powered off, and is suitable for on-off control of the short-time blowing air passage.
The pressure of the air source 1 is 35-45 MPa, the pressure reducer 2 is a constant pressure reducer, and the pressure of the air source is reduced and stabilized within the range of 23-25 MPa through the pressure reducer 2.
The drift diameter of the ground orifice plate 5 is 1.6mm, the drift diameter of the orifice plate 7 on the first arrow is 3.4mm, the drift diameter of the orifice plate 8 on the second arrow is 1.0mm, and the drift diameter of the orifice plate 9 on the third arrow is 1.0 mm.
After the rocket is launched, an operator of the gas distribution table opens the manual switch 3 to blow off 3 positions on the rocket, the pressure of the butt joint surface of the rocket can be guaranteed to be stable within the range of 2-3 MPa, and the pressure requirement of the engine and the valve for blowing off gas is met.
When the engine is not required to be blown off after ignition, the normal-way electromagnetic valve 4 is electrified to cut off the gas supply path, and the nitrogen gas blowing on the arrow is stopped. Because blowing generally needs long-time air supply, the normal-way electromagnetic valve does not need to be electrified for a long time, and the working reliability of the electromagnetic valve is ensured.
The ground pipeline is internally provided with a throttling orifice plate for primary throttling and pressure reduction, the throttling orifice plate enters the rear branch of the rocket body, each air supply branch is provided with a throttling orifice plate for secondary throttling and pressure reduction, and the pressure and the flow of the air can be stabilized after pressure reduction by a pressure reducer and twice orifice plate throttling and pressure reduction. The number of supply branches may be determined according to the need to blow off gas, and only three supply branches are described in this embodiment.
Parts of the invention not described in detail are known to the person skilled in the art.
Claims (5)
1. A rocket blowing centralized gas supply system is characterized by comprising: the device comprises a gas source (1), a pressure reducer (2), a manual switch (3), a normally-open electromagnetic valve (4), a ground orifice plate (5), an arrow pipeline joint (6) and a plurality of arrow upper orifice plates;
the outlet of the air source (1) is connected with the inlet of the pressure reducer (2), the outlet of the pressure reducer (2) is connected with the inlet of the normally open type electromagnetic valve (4) through the manual switch (3), the outlet of the normally open type electromagnetic valve (4) is connected with the ground orifice plate (5), the ground orifice plate (5) is connected with the arrow pipeline joint (6), and the arrow pipeline joint (6) is connected with the arrow pipeline joint (6) respectively.
2. A rocket blowing centralized gas supply system according to claim 1, wherein the pressure of the gas source (1) is 35-45 MPa.
3. A rocket blowing centralized gas supply system according to claim 1 or 2, wherein the pressure reducer (2) is a constant pressure reducer, and the pressure of the variable gas source (1) is reduced and stabilized within a set range, and is controlled to be about 23-25 MPa.
4. A rocket blowing centralized air supply system according to claim 3, wherein the normally-open solenoid valve (4) is switched on the air supply passage when powered on, and is switched off when powered off for on-off control of the blowing air passage.
5. A rocket blowing-off centralized gas supply system according to claim 4, wherein the pressure reducer (2) decompresses the gas output by the gas source (1), performs first throttling decompression through the ground throttling orifice plate (5), enters the rocket body, performs second throttling decompression through the corresponding rocket upper throttling orifice plate according to the gas supply requirement, and blows off the part needing blowing off.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110178075.9A CN113002808A (en) | 2021-02-07 | 2021-02-07 | Rocket blowing centralized gas supply system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110178075.9A CN113002808A (en) | 2021-02-07 | 2021-02-07 | Rocket blowing centralized gas supply system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113002808A true CN113002808A (en) | 2021-06-22 |
Family
ID=76384328
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110178075.9A Pending CN113002808A (en) | 2021-02-07 | 2021-02-07 | Rocket blowing centralized gas supply system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113002808A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101652192A (en) * | 2007-04-04 | 2010-02-17 | 杜尔艾科克林有限公司 | Method for supplying a cleaning medium, and method and cleaning device for cleaning a workpiece |
| EP2192209A2 (en) * | 2008-11-17 | 2010-06-02 | Alstom Technology Ltd | Device for cleaning oxidized or corroded components in the presence of a halogenous gas mixture |
| CN104913201A (en) * | 2015-04-29 | 2015-09-16 | 北京航天发射技术研究所 | Pressure reducer air supply loop adopting redundant design and control method |
| CN105604738A (en) * | 2015-12-30 | 2016-05-25 | 西安航天动力试验技术研究所 | Liquid oxygen/kerosene engine test gas supply system |
| CN105665374A (en) * | 2016-01-06 | 2016-06-15 | 北京航天发射技术研究所 | Engine blowdown gas circuit |
| CN107587954A (en) * | 2017-09-05 | 2018-01-16 | 北京航空航天大学 | Gas oxygen kerosene Rocket Engines pressurizing transmission system and small rocket motor propellant-feed system |
| CN111677600A (en) * | 2020-06-08 | 2020-09-18 | 西安航天动力研究所 | Method for accurately controlling blowing pressure of floating ring of multi-start rocket engine |
| CN111810320A (en) * | 2020-07-22 | 2020-10-23 | 北京星际荣耀空间科技有限公司 | Control and blowing system, liquid rocket engine and rocket |
-
2021
- 2021-02-07 CN CN202110178075.9A patent/CN113002808A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101652192A (en) * | 2007-04-04 | 2010-02-17 | 杜尔艾科克林有限公司 | Method for supplying a cleaning medium, and method and cleaning device for cleaning a workpiece |
| EP2192209A2 (en) * | 2008-11-17 | 2010-06-02 | Alstom Technology Ltd | Device for cleaning oxidized or corroded components in the presence of a halogenous gas mixture |
| CN104913201A (en) * | 2015-04-29 | 2015-09-16 | 北京航天发射技术研究所 | Pressure reducer air supply loop adopting redundant design and control method |
| CN105604738A (en) * | 2015-12-30 | 2016-05-25 | 西安航天动力试验技术研究所 | Liquid oxygen/kerosene engine test gas supply system |
| CN105665374A (en) * | 2016-01-06 | 2016-06-15 | 北京航天发射技术研究所 | Engine blowdown gas circuit |
| CN107587954A (en) * | 2017-09-05 | 2018-01-16 | 北京航空航天大学 | Gas oxygen kerosene Rocket Engines pressurizing transmission system and small rocket motor propellant-feed system |
| CN111677600A (en) * | 2020-06-08 | 2020-09-18 | 西安航天动力研究所 | Method for accurately controlling blowing pressure of floating ring of multi-start rocket engine |
| CN111810320A (en) * | 2020-07-22 | 2020-10-23 | 北京星际荣耀空间科技有限公司 | Control and blowing system, liquid rocket engine and rocket |
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210622 |