CN215719136U - Self-generating pressurization system for impurity gas-resistant low-temperature rocket - Google Patents
Self-generating pressurization system for impurity gas-resistant low-temperature rocket Download PDFInfo
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- CN215719136U CN215719136U CN202121787377.8U CN202121787377U CN215719136U CN 215719136 U CN215719136 U CN 215719136U CN 202121787377 U CN202121787377 U CN 202121787377U CN 215719136 U CN215719136 U CN 215719136U
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- pressure
- liquid oxygen
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- exhaust electromagnetic
- oxygen tank
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- 239000012535 impurity Substances 0.000 title claims abstract description 27
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 58
- 239000007789 gas Substances 0.000 claims description 37
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 12
- 229910052760 oxygen Inorganic materials 0.000 claims description 12
- 239000001301 oxygen Substances 0.000 claims description 12
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 claims description 8
- 239000011148 porous material Substances 0.000 claims description 8
- 239000003350 kerosene Substances 0.000 claims description 5
- 229910002092 carbon dioxide Inorganic materials 0.000 claims description 4
- 239000001569 carbon dioxide Substances 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract description 3
- 230000002411 adverse Effects 0.000 abstract description 2
- 239000007787 solid Substances 0.000 description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 230000008030 elimination Effects 0.000 description 2
- 238000003379 elimination reaction Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
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Abstract
According to the self-generating pressurization system for the impurity gas-resistant low-temperature rocket, the adverse effect of the impurity gas on the system is avoided, the single point of the system action is eliminated, and the reliable work of the system is realized by closed-loop control, arrangement of the action unit on a pressurization pipeline, series connection of the exhaust electromagnetic valves, parallel connection of the electric control safety valves and the like.
Description
Technical Field
The utility model relates to a self-generating pressurization system suitable for a low-temperature rocket liquid oxygen tank, in particular to a self-generating pressurization system containing impurity gas.
Background
The YF-100 series engine is a high-pressure afterburning circulating liquid oxygen kerosene engine, has the advantages of high performance, adjustability, small size, light weight and the like, and is widely applied to CZ-5, CZ-7 and other low-temperature rockets of the new generation in China. The self-generation pressurization scheme adopted by the low-temperature rocket boosting-stage liquid oxygen box and the core first-stage liquid oxygen box has the advantages of simple system, good economy, convenience in use and maintenance, elimination of a pressurization gas cylinder installation cabin section and the like, and becomes a development trend. However, the autogenous pressurized gas (oxygen) provided by the high-pressure afterburning circulating liquid oxygen kerosene engine contains gas impurities such as carbon dioxide, water vapor and the like, after the pressurized gas enters the liquid oxygen tank, the impurity gas can be frosted and solidified at low temperature to form solid surplus objects, and the valve leakage and even the function failure can be caused when the surplus objects enter valve products such as a safety valve and the like. Therefore, there is an urgent need for a self-generating pressurization system for a low-temperature rocket, which is resistant to impurity gases.
SUMMERY OF THE UTILITY MODEL
The technical problem to be solved by the utility model is as follows: overcomes the defects of the prior art and provides a self-generating pressurization system for a low-temperature rocket resistant to impurity gases.
The technical solution of the utility model is as follows:
an impurity gas resistant self-generating pressurization system for a low-temperature rocket comprises a liquid oxygen tank, a pressurization pipe, three pressure sensors, a comprehensive controller, an electric control safety valve, two exhaust electromagnetic valves and a pressure drop pore plate;
the input end of the pressure increasing pipe is used for inputting oxygen, the output end of the pressure increasing pipe is provided with an energy dissipater, and the output end of the pressure increasing pipe and the installed energy dissipater are input into the liquid oxygen tank;
the pressure increasing pipe is provided with two branches, the two branches are respectively a first branch and a second branch, the first branch is provided with two exhaust electromagnetic valves side by side, a pressure dropping hole plate is arranged on the pressure increasing pipe and at the upstream position of the first branch, and the second branch is provided with an electric control safety valve; a pressure-holding pressure-dropping pore plate is arranged on a pressure increasing pipeline between the downstream of the exhaust electromagnetic valve and the electric control safety valve, so that the working pressure of the electromagnetic valve can meet the use requirement;
the pressure sensor is arranged on the liquid oxygen tank and used for measuring the gas pressure in the liquid oxygen tank;
the integrated controller is used for controlling the electric control safety valve and the two exhaust electromagnetic valves to be opened and closed, and when the pressure sensor measures that the gas pressure in the liquid oxygen tank is greater than a set value, the exhaust electromagnetic valves are opened to reduce the pressure;
an autogenous pressurization method for a low-temperature rocket resistant to impurity gases comprises the following steps: inputting oxygen into the liquid oxygen box through the input end of the pressurization pipe, transmitting the pressure of an air pillow of the liquid oxygen box to the integrated controller through three pressure sensors arranged on the liquid oxygen box, controlling the pressure in the liquid oxygen box in a design pressure band by the integrated controller through controlling the opening and closing of an exhaust electromagnetic valve in a voting mode of 'two out of three', controlling the pressure in the liquid oxygen box in the design pressure band when the pressure in the liquid oxygen box cannot be controlled in the design pressure band through controlling the opening and closing of the exhaust electromagnetic valve, namely when a fault working condition occurs, the pressure of the liquid oxygen box exceeds the upper limit of the design pressure band, and controlling the pressure in the liquid oxygen box in a safe pressure range through opening and closing an electric control safety valve by the integrated controller;
the oxygen input through the input end of the booster pipe is self-generated booster gas from a liquid oxygen kerosene engine, contains a small amount of gas impurities such as carbon dioxide, water vapor and the like, and has the temperature of more than 350K;
oxygen enters the liquid oxygen tank through the booster pipe and the energy dissipater to be pressurized;
the exhaust electromagnetic valve, the electric control safety valve and other action units are all installed on the autogenous pressurizing pipeline, contact high-temperature autogenous pressurizing gas and do not contact solid impurities in the air pillow of the liquid oxygen tank, and therefore reliable operation of the system is guaranteed.
Advantageous effects
According to the self-generating pressurization system containing the impurity gas, which is suitable for the low-temperature rocket liquid oxygen tank, the adverse effect of the impurity gas on the system is avoided, the single point of the system action is eliminated, and the reliable work of the system is realized by closed-loop control, arrangement of the action single machine on a pressurization pipeline, series connection of the exhaust electromagnetic valves, parallel connection of the electric control safety valves and the like.
Drawings
FIG. 1 is a schematic diagram of the system of the present invention;
1-a pressure increasing pipe; 2-a pressure sensor; 3-a comprehensive controller; 4-exhaust electromagnetism; 5-an electric control safety valve 6-an energy dissipater; 7-liquid oxygen box; 8-pressure drop pore plate.
Detailed Description
The utility model is further illustrated by the following figures and examples.
As shown in fig. 1, the autogenous pressurization system for the impurity gas resistant low-temperature rocket comprises a liquid oxygen tank, a pressurization pipe, three pressure sensors, a comprehensive controller, an electric control safety valve, two exhaust electromagnetic valves and a pressure drop pore plate;
the input end of the pressure increasing pipe is used for inputting oxygen, the output end of the pressure increasing pipe is provided with an energy dissipater, and the output end of the pressure increasing pipe and the installed energy dissipater are input into the liquid oxygen tank;
the pressure increasing pipe is provided with two branches, the two branches are respectively a first branch and a second branch, the first branch is provided with two exhaust electromagnetic valves side by side, a pressure dropping hole plate is arranged on the pressure increasing pipe and at the upstream position of the first branch, and the second branch is provided with an electric control safety valve; a pressure-holding pressure-dropping pore plate is arranged on a pressure increasing pipeline between the downstream of the exhaust electromagnetic valve and the electric control safety valve, so that the working pressure of the electromagnetic valve can meet the use requirement;
the pressure sensor is arranged on the liquid oxygen tank and used for measuring the gas pressure in the liquid oxygen tank;
the integrated controller is used for controlling the electric control safety valve and the two exhaust electromagnetic valves to be opened and closed, and when the pressure sensor measures that the gas pressure in the liquid oxygen tank is greater than a set value, the exhaust electromagnetic valves are opened to reduce the pressure;
an autogenous pressurization method for a low-temperature rocket resistant to impurity gases comprises the following steps: inputting oxygen into the liquid oxygen box through the input end of the pressurization pipe, transmitting the pressure of an air pillow of the liquid oxygen box to the integrated controller through three pressure sensors arranged on the liquid oxygen box, controlling the pressure in the liquid oxygen box in a design pressure band by the integrated controller through controlling the opening and closing of an exhaust electromagnetic valve in a voting mode of 'two out of three', controlling the pressure in the liquid oxygen box in the design pressure band when the pressure in the liquid oxygen box cannot be controlled in the design pressure band through controlling the opening and closing of the exhaust electromagnetic valve, namely when a fault working condition occurs, the pressure of the liquid oxygen box exceeds the upper limit of the design pressure band, and controlling the pressure in the liquid oxygen box in a safe pressure range through opening and closing an electric control safety valve by the integrated controller;
the oxygen input through the input end of the booster pipe is self-generated booster gas from a liquid oxygen kerosene engine, contains a small amount of gas impurities such as carbon dioxide, water vapor and the like, and has the temperature of more than 350K;
oxygen enters the liquid oxygen tank through the booster pipe and the energy dissipater to be pressurized;
the exhaust electromagnetic valve, the electric control safety valve and other action units are all installed on the autogenous pressurizing pipeline, contact high-temperature autogenous pressurizing gas and do not contact solid impurities in the air pillow of the liquid oxygen tank, and therefore reliable operation of the system is guaranteed.
Examples
As shown in fig. 1, an autogenous pressurization system for a low-temperature rocket resistant to impurity gases mainly comprises: the device comprises a pressure increasing pipe 1, a pressure sensor 2, an integrated controller 3, an exhaust electromagnet 4, an electric control safety valve 5, an energy dissipater 6, a liquid oxygen tank 7 and a pressure dropping pore plate 8;
the exhaust solenoid valve 4 and the electric control safety valve 5 are arranged on the pressure increasing pipe 1, the exhaust solenoid valve 4 eliminates a single-point fault mode which cannot be opened through a series connection elimination single-point fault mode and through combination with the electric control safety valve 5, and meanwhile, solid impurities in an air pillow of the liquid oxygen box are prevented from being contacted, and reliable work of the system is guaranteed.
Three pressure sensors 2 are arranged on the liquid oxygen tank 7, the pressure of an air pillow of the liquid oxygen tank 7 is fed back to the integrated controller 3, the integrated controller 3 controls the opening and closing of the exhaust electromagnetic valve 4 to control the pressure of the liquid oxygen tank within a design range through a voting mode of 'two out of three', and controls the opening and closing of the electric control safety valve 5 to control the pressure of the liquid oxygen tank within a safe pressure range, so that the closed-loop control of the pressure of the liquid oxygen tank is realized.
Claims (6)
1. The utility model provides a low temperature rocket of resistant impure gas is with autogenous turbocharging system which characterized in that: the system comprises a liquid oxygen tank, a pressure increasing pipe, a pressure sensor, a comprehensive controller, an electric control safety valve, an exhaust electromagnetic valve and a pressure drop pore plate;
the input end of the pressure increasing pipe is used for inputting oxygen, the output end of the pressure increasing pipe is provided with an energy dissipater, and the output end of the pressure increasing pipe and the installed energy dissipater are input into the liquid oxygen tank;
the pressure increasing pipe is provided with two branches which are respectively a first branch and a second branch, the first branch is provided with an exhaust electromagnetic valve, and the second branch is provided with an electric control safety valve; arranging a pressure drop pore plate on a pressure increasing pipeline between the first branch and the second branch;
the pressure sensor is arranged on the liquid oxygen tank and used for measuring the gas pressure in the liquid oxygen tank;
the integrated controller is used for controlling the electric control safety valve and the switch of the exhaust electromagnetic valve, and when the pressure sensor measures that the gas pressure in the liquid oxygen tank is greater than a set value, the exhaust electromagnetic valve is opened for pressure reduction;
when the pressure in the liquid oxygen box can not be controlled within a designed pressure band by controlling the opening and closing of the exhaust electromagnetic valve, the integrated controller controls the pressure in the liquid oxygen box within a safe pressure range by opening and closing the electric control safety valve.
2. An autogenous pressurization system for a low temperature rocket resistant to impurity gases, as claimed in claim 1, wherein:
the number of the pressure sensors is three.
3. An autogenous pressurization system for a low temperature rocket resistant to impurity gases, as claimed in claim 2, wherein:
the three pressure sensors arranged on the liquid oxygen tank transmit the pressure of the air pillow of the liquid oxygen tank to the integrated controller, and the integrated controller controls the pressure in the liquid oxygen tank in a design pressure band by controlling the opening and closing of the exhaust electromagnetic valve in a voting mode of 'two out of three'.
4. An autogenous pressurization system for a low temperature rocket resistant to impurity gases, as claimed in claim 1, wherein:
the number of the exhaust electromagnetic valves is two.
5. An autogenous pressurization system for a low temperature rocket resistant to impurity gases, as claimed in claim 4, wherein:
the two exhaust electromagnetic valves are arranged on the first branch in parallel.
6. An autogenous pressurization system for a low temperature rocket resistant to impurity gases, as claimed in claim 1, wherein: oxygen is input into the liquid oxygen box through the input end of the booster pipe, the oxygen input through the input end of the booster pipe is self-generated booster gas from the liquid oxygen kerosene engine, the self-generated booster gas contains carbon dioxide and vapor gas impurities, and the temperature is above 350K.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121787377.8U CN215719136U (en) | 2021-08-02 | 2021-08-02 | Self-generating pressurization system for impurity gas-resistant low-temperature rocket |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121787377.8U CN215719136U (en) | 2021-08-02 | 2021-08-02 | Self-generating pressurization system for impurity gas-resistant low-temperature rocket |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116046377A (en) * | 2022-12-30 | 2023-05-02 | 北京天兵科技有限公司 | Rocket oxygen safety valve opening and closing performance test system and test method |
| CN116296421A (en) * | 2022-12-30 | 2023-06-23 | 北京天兵科技有限公司 | Rocket oxygen tank power system test run pressure increasing and supplementing device and method |
-
2021
- 2021-08-02 CN CN202121787377.8U patent/CN215719136U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116046377A (en) * | 2022-12-30 | 2023-05-02 | 北京天兵科技有限公司 | Rocket oxygen safety valve opening and closing performance test system and test method |
| CN116296421A (en) * | 2022-12-30 | 2023-06-23 | 北京天兵科技有限公司 | Rocket oxygen tank power system test run pressure increasing and supplementing device and method |
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