CN113375943A - Posture and orbit control engine high-modulus post-test quick blowing system and method - Google Patents
Posture and orbit control engine high-modulus post-test quick blowing system and method Download PDFInfo
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- CN113375943A CN113375943A CN202110586897.0A CN202110586897A CN113375943A CN 113375943 A CN113375943 A CN 113375943A CN 202110586897 A CN202110586897 A CN 202110586897A CN 113375943 A CN113375943 A CN 113375943A
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- 238000007664 blowing Methods 0.000 title claims abstract description 139
- 238000000034 method Methods 0.000 title claims abstract description 47
- 238000012360 testing method Methods 0.000 title claims abstract description 46
- 238000011084 recovery Methods 0.000 claims abstract description 106
- 239000003380 propellant Substances 0.000 claims abstract description 102
- 238000004064 recycling Methods 0.000 claims abstract description 10
- 239000002737 fuel gas Substances 0.000 abstract description 8
- 239000000126 substance Substances 0.000 abstract description 3
- 231100000331 toxic Toxicity 0.000 abstract description 3
- 230000002588 toxic effect Effects 0.000 abstract description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 6
- 239000007789 gas Substances 0.000 description 6
- 238000002347 injection Methods 0.000 description 6
- 239000007924 injection Substances 0.000 description 6
- 239000012535 impurity Substances 0.000 description 5
- 238000007599 discharging Methods 0.000 description 4
- 238000004088 simulation Methods 0.000 description 4
- 229910052757 nitrogen Inorganic materials 0.000 description 3
- 238000005086 pumping Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000002457 bidirectional effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000000779 smoke Substances 0.000 description 1
- 238000013022 venting Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B5/00—Cleaning by methods involving the use of air flow or gas flow
- B08B5/02—Cleaning by the force of jets, e.g. blowing-out cavities
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- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The invention provides a posture-orbit control engine high-modulus after-quick blowing system and a posture-orbit control engine high-modulus after-quick blowing method, which solve the problems of unclean blowing and more toxic and harmful substances in fuel gas in the blowing process of the existing engine blowing system. The rapid blowing and supplying system after the attitude and orbit control engine high-modulus test comprises a propellant blowing unit, a propellant supplying unit and a propellant recycling unit; the propellant blowing unit comprises a blowing container, a blowing pipeline, a first one-way valve, a pneumatic blowing valve and a first one-way filter; the propellant supply unit comprises a pneumatic supply valve, a supply line, a second one-way filter and a product valve; the propellant recovery unit comprises a recovery pipeline, a two-way filter, a pneumatic recovery valve, a second one-way valve and a recovery container.
Description
Technical Field
The invention relates to the field of attitude control power system tests, in particular to a system and a method for quickly blowing off an attitude and orbit control engine after a high-modulus test.
Background
The attitude and orbit control engine mostly adopts a mode of supplying propellant by an extrusion method, and thrust performance and working reliability under a vacuum environment need to be obtained in a development stage. A vacuum environment of the working process of the engine is built through a high-altitude simulation test system, and the engine thermal ignition test is carried out, so that the method is an important development means. Meanwhile, after the test is finished, the structure or the state of the product is very important for designers. However, after the ignition of the engine is finished, the inlet pipeline of the engine is filled with the propellant, and in this state, a designer or a producer cannot check the internal structure of the product, and the residual propellant in the product must be blown off to ensure the degradability of the product after the test.
During the attitude and orbit control engine test, the engine needs to be placed in a vacuum chamber, and a high-altitude simulation test system is used for suction to maintain the vacuum pressure environment of the vacuum chamber. Generally, a high-altitude simulation test system consumes a large amount of energy cost for timely discharging fuel gas generated by an engine and maintaining cabin pressure when the engine works. Therefore, the working time of the high-altitude simulation test system is required to be reduced to the greatest extent under the condition of meeting the starting working condition, and the product blowing work is required to be carried out quickly after the ignition of the engine is finished.
Meanwhile, after the test is finished, the engine is blown off under the condition that the propellant is filled in front of the engine valve, so that the condition that the mixing ratio of the engine in the combustion process is seriously deviated from the designed value often exists, and unnecessary damage to the engine is easily caused. Because the internal state of the engine cannot be checked in real time, whether the internal state appears in the test process or the post-test blowing process appears is difficult to judge, and a designer causes interference on the performance judgment of the engine.
Therefore, after the test is finished, the propellant in the inlet pipeline of the engine is firstly emptied to reduce the residual propellant amount as much as possible, and then the inert gas nitrogen is introduced to blow off the product. Since the propellant supply system mainly considers the function of the supply capacity, the rapid recovery processing of the propellant and the automation capacity design of the engine blow-off system are insufficient. After the engine test is finished, firstly, an operator goes to the foreground to evacuate the inlet pipeline propellant, and then nitrogen is introduced to blow off, in the process, the time for entering, operating and evacuating personnel is long, and the injection system is required not to stop, on one hand, the injection system needs to be injected to reserve enough spare capacity, and on the other hand, certain safety risk exists in the field operation of the personnel. The current normal processing flow is shown in fig. 1, and this mode has the following defects: 1) after the vacuum chamber is opened, blowing is carried out in the atmospheric environment, and part of the engine still remains and cannot be blown cleanly; 2) the propellant is not sufficiently combusted in the blowing process, toxic and harmful substances in the fuel gas are more and are scattered in the vacuum chamber, and although certain measures are taken, the fuel gas is difficult to treat cleanly, certain damage is caused to the physical health of test post-treatment personnel, and the mode does not meet the requirements of environmental protection and occupational health management.
Disclosure of Invention
The invention aims to solve the problems that the existing engine blowing system can not quickly discharge a propellant and can not quickly blow the engine, and further solve the problems that the blowing is not clean under atmospheric conditions and more toxic and harmful substances exist in the blowing process.
In order to achieve the above purpose, the technical scheme of the invention is as follows:
a method for quickly blowing off a posture and orbit control engine after a high-modulus test is disclosed, which is based on the realization of a propellant discharge blowing-off system quickly realized by the posture and orbit control engine high-modulus test, and the realization of the propellant discharge blowing-off system quickly realized by the posture and orbit control engine high-modulus test comprises a propellant blowing-off unit, a propellant supply unit and a propellant recovery unit; the propellant blowing unit comprises a blowing container, a blowing pipeline, a first one-way valve, a pneumatic blowing valve and a first one-way filter; the inlet of the blowing pipeline is connected with the blowing container, the outlet of the blowing pipeline is connected with the propellant supply unit, the first one-way valve, the pneumatic blowing valve and the first one-way filter are all arranged on the blowing pipeline, and the inlet and outlet directions of the first one-way valve and the first one-way filter are consistent with the inlet and outlet directions of the blowing pipeline; the propellant supply unit comprises a pneumatic supply valve, a supply line, a second one-way filter and a product valve; one end of the supply pipeline is respectively connected with the blowing pipeline and the external propellant pipeline, and the other end of the supply pipeline is connected with the attitude and orbit control engine; the pneumatic supply valve is arranged on a supply pipeline positioned outside the vacuum chamber; the second one-way filter and the product valve are arranged on a supply pipeline positioned in the vacuum chamber; the propellant recovery unit comprises a recovery pipeline, a two-way filter, a pneumatic recovery valve, a second one-way valve and a recovery container; the inlet of the recovery pipeline is connected with a supply pipeline arranged between the second one-way filter and the product valve, the outlet of the recovery pipeline is connected with a recovery container, the two-way filter is arranged on the recovery pipeline positioned in the vacuum cabin, the pneumatic recovery valve and the second one-way valve are arranged on the recovery pipeline positioned outside the vacuum cabin, and the inlet and outlet directions of the second one-way valve are consistent with the inlet and outlet directions of the recovery pipeline;
the method comprises the following steps:
step one, in the ignition process of the attitude and orbit control engine, a pneumatic supply valve is kept normally open, a pneumatic blow-off valve is closed, a pneumatic recovery valve is closed, the deflation systems of a blow-off container and a recovery container are kept closed, and a propellant enters the attitude and orbit control engine through a propellant supply unit;
step two, after the ignition of the attitude and orbit control engine is finished, closing the pneumatic supply valve, opening an air discharge system of a recovery container, and releasing the pressure of the propellant in a supply pipeline in front of a product valve by the pneumatic recovery valve; pressurizing the blowing container while releasing pressure, opening the pneumatic blowing valve when the pressure reaches a set value, and extruding residual propellant in the supply pipeline to the recovery container by using the pressure in the blowing container;
step three, opening a pneumatic blow-off valve for a certain time, closing the pneumatic blow-off valve for a certain time, blowing off the propellant in the supply pipeline, and closing a pneumatic recovery valve after blowing off the propellant for N times (3-5 times) intermittently;
and step four, maintaining the pressure of the blowing container, opening a product valve, blowing the attitude and orbit control engine until the nozzle of the attitude and orbit control engine has no obvious gas representation or the room pressure has no great change, closing the product valve, and finishing the blowing operation.
Further, in the second step, the pressure of the blowing container is increased to 1MPa while the pressure is released.
And step three, opening the pneumatic blow-off valve for 10s, then closing the pneumatic blow-off valve for 5s, and intermittently blowing off for three times, and then closing the pneumatic recovery valve.
Meanwhile, the invention also provides a posture and orbit control engine high-modulus post-test quick blowing system which comprises a propellant blowing unit, a propellant supply unit and a propellant recovery unit; the propellant blowing unit comprises a blowing container, a blowing pipeline, a first one-way valve, a pneumatic blowing valve and a first one-way filter; the inlet of the blowing pipeline is connected with the blowing container, the outlet of the blowing pipeline is connected with the propellant supply unit, the first one-way valve, the pneumatic blowing valve and the first one-way filter are all arranged on the blowing pipeline, and the inlet and outlet directions of the first one-way valve and the first one-way filter are consistent with the inlet and outlet directions of the blowing pipeline; the propellant supply unit comprises a pneumatic supply valve, a supply line, a second one-way filter and a product valve; one end of the supply pipeline is respectively connected with the blowing pipeline and the external propellant pipeline, and the other end of the supply pipeline is connected with the attitude and orbit control engine; the pneumatic supply valve is arranged on a supply pipeline positioned outside the vacuum chamber; the second one-way filter and the product valve are arranged on a supply pipeline positioned in the vacuum chamber; the propellant recovery unit comprises a recovery pipeline, a two-way filter, a pneumatic recovery valve, a second one-way valve and a recovery container; the inlet of the recovery pipeline is connected with a supply pipeline arranged between the second one-way filter and the product valve, the outlet of the recovery pipeline is connected with the recovery container, the two-way filter is arranged on the recovery pipeline positioned in the vacuum cabin, the pneumatic recovery valve and the second one-way valve are arranged on the recovery pipeline positioned outside the vacuum cabin, and the inlet and outlet directions of the second one-way valve are consistent with the inlet and outlet directions of the recovery pipeline.
Further, a manual blowing supply valve is arranged at an outlet of the blowing container, and a normally closed first process hand valve is also arranged on the blowing pipeline; and a manual recovery supply valve is arranged at an inlet of the recovery container, and a normally closed second process hand valve is also arranged on the recovery pipeline.
Furthermore, the top end of the blowing container is also provided with a pressurizing device, an air discharging device and a safety device, and the top end of the recovery container is also provided with a pressurizing device, an air discharging device and a safety device.
Furthermore, a pressure sensor is arranged on the supply pipeline in the vacuum cabin body.
Compared with the prior art, the invention has the following technical effects:
1. the method and the system of the invention are provided with the pneumatic blow-off valve at the position close to the propellant supply pipeline, thereby realizing the remote and rapid gas supply blow-off capability, and are provided with the pneumatic recovery valve at the position close to the propellant supply pipeline, thereby realizing the remote and rapid propellant recovery capability. The propellant blows off the unit and sets up the filter before pneumatic blow off valve, can effectively prevent to blow off impurity entering in the container and blow off the valve to avoid external impurity etc. to lead to risks such as valve jamming. Meanwhile, the one-way valve is arranged in the propellant blowing unit and is close to the propellant supply pipeline interface as much as possible, so that the corrosion of the propellant on a system valve and the influence of the propellant gas content when the propellant is supplied by the pipeline accommodating cavity at the position can be effectively prevented.
2. The propellant recovery unit is provided with the bidirectional filter at the interface in the cabin, so that impurities in the recovery system can be prevented from entering the propellant pipeline under the unexpected condition, the excess materials can be prevented from entering the propellant, the impurities in the propellant after the test can be prevented from entering the recovery system, and the cleanness of the recovery pipeline is ensured. Meanwhile, the recovery pipeline is provided with the one-way valve, so that the one-way flow of the propellant is ensured, and impurities or gas in the recovery system can be effectively prevented from accidentally entering the propellant supply pipeline during test preparation.
3. The process valve on the blowing pipeline in the propellant blowing unit is arranged on the lower wall surface of the pipeline, and has the capacity of discharging accumulated liquid in the pipeline after long-time use.
4. In the method and the system, the corrosion-resistant pneumatic valve capable of being remotely controlled is utilized, so that personnel can quickly discharge the propellant and the blowing capacity of the engine after the attitude and orbit control engine high-modulus test is finished without entering the site.
Drawings
FIG. 1 is a flow chart of a prior art post-test engine process;
FIG. 2 is a flow chart of the engine test post-treatment process of the method of the present invention;
FIG. 3 is a schematic diagram of a post-high-modulus quick blow-down system for a posture control engine according to the present invention.
Reference numerals: 1-blowing container, 2-manual blowing supply valve, 3-first process hand valve, 4-first one-way filter, 5-pneumatic blowing valve, 6-first one-way valve, 7-pneumatic supply valve, 8-supply pipeline, 9-second one-way filter, 10-two-way filter, 11-pneumatic recovery valve, 12-second one-way valve, 13-recovery container, 14-blowing pipeline, 15-product valve, 16-recovery pipeline, 17-manual recovery supply valve, 18-second process hand valve and 19-pressure sensor.
Detailed Description
The invention is described in further detail below with reference to the figures and specific embodiments.
According to the flow shown in fig. 1, to realize safe discharge of fuel gas in the blowing process, one is to independently treat the fuel gas, and the other is to blow the fuel gas in a vacuum environment by utilizing the characteristic of vacuumizing of an injection system, and suck and treat the fuel gas. The first mode needs an independent system, is complex in mode and high in cost, and solves the problems of gas collection, treatment and the like. The second mode effectively utilizes the existing conditions, and only needs to realize the quick treatment and pressurization work of the inlet propellant and the short working time of the injection system after the engine test is finished. Through long-term test observation, the inlet pipeline propellant is blown off the engine after evacuation treatment, and the condition that the engine structure is damaged due to the blowing-off process does not occur. In a vacuum environment, the engine blowing and vacuum pumping effects are performed, and the removal of residual propellant in a combustion chamber of the engine is facilitated. Thus, a new process flow is shown in FIG. 2. After the engine test is finished, the injection system continues pumping, the pipeline propellant is remotely treated by using the program control valve, nitrogen is introduced to control the time, the engine is quickly blown, and the injection system stops vacuumizing after blowing. Therefore, an automatic system for supplying and recovering the propellant needs to be built, and the rapid treatment of the inlet propellant and the blowing-off of the engine can be realized.
The invention provides a posture-orbit-control engine high-modulus post-test rapid blowing system and a posture-orbit-control engine high-modulus post-test rapid blowing method.
As shown in fig. 3, the posture control engine high-modulus after-rapid blowing system of the invention comprises a propellant blowing unit, a propellant supply unit and a propellant recovery unit. The propellant blowing unit and the propellant recovery unit are based on the rear part of the pneumatic primary valve of the propellant supply system.
The propellant blowing unit comprises a blowing container 1, a blowing pipeline 14, a first one-way valve 6, a pneumatic blowing valve 5 and a first one-way filter 4; the inlet of the blowing pipeline 14 is connected with the blowing container 1, the outlet of the blowing pipeline is connected with the propellant supply unit, the first one-way valve 6, the pneumatic blowing valve 5 and the first one-way filter 4 are all arranged on the blowing pipeline 14, and the inlet and outlet directions of the first one-way valve 6 and the first one-way filter 4 are consistent with the inlet and outlet directions of the blowing pipeline 14.
The propellant supply unit of the present invention comprises a pneumatic supply valve 7, a supply line 8, a second one-way filter 9, a pressure sensor 19 and a product valve 15; one end of the supply pipeline 8 is respectively connected with the blowing pipeline 14 and the external propellant pipeline, and the other end is connected with the attitude and orbit control engine; the pneumatic supply valve 7 is arranged on a supply line 8 located outside the vacuum chamber; a second one-way filter 9, a pressure sensor 19 and a product valve 15 are arranged on the supply line 8 in the vacuum chamber.
The propellant recovery unit of the invention comprises a recovery pipeline 16, a two-way filter 10, a pneumatic recovery valve 11, a second one-way valve 12 and a recovery container 13; an inlet of the recovery pipeline 16 is connected with the supply pipeline 8 arranged between the second one-way filter 9 and the product valve 15, an outlet of the recovery pipeline is connected with the recovery container 13, the two-way filter 10 is arranged on the recovery pipeline 16 positioned in the vacuum chamber, the pneumatic recovery valve 11 and the second one-way valve 12 are arranged on the recovery pipeline 16 positioned outside the vacuum chamber, and the inlet and outlet directions of the second one-way valve 12 are consistent with the inlet and outlet directions of the recovery pipeline 16.
The outlet of the blowing container 1 is provided with a manual blowing supply valve 2, and a normally closed process hand valve is also arranged on the blowing pipeline 14. The top end of the blow-off container 1 is also provided with conventional pressurising, venting and safety accessories. A manual recycling supply valve 17 is arranged at the inlet of the recycling container 13, and a normally closed process hand valve is also arranged on the recycling pipeline 16. The top end of the recovery vessel 13 is also provided with conventional pressurization, deflation and safety accessories.
Based on the attitude and orbit control engine high-modulus test rapid blowing supply system, the invention provides a attitude and orbit control engine high-modulus test rapid blowing method, which comprises the following steps:
in the process of ignition of the attitude and orbit control engine, the pneumatic supply valve 7 is kept normally open, the pneumatic blow-off valve 5 is closed, the pneumatic recovery valve 11 is closed, the process hand valve is closed, the manual blow-off supply valve 2 and the manual recovery control valve are kept normally open, the deflation systems of the blow-off container 1 and the recovery container 13 are kept closed, and the propellant enters the attitude and orbit control engine through the propellant supply unit;
after the attitude and orbit control engine is ignited, the pneumatic supply valve 7 is closed, and the air discharge system of the recovery container 13 and the pneumatic recovery valve 11 are opened to discharge the pressure of the propellant in the supply pipeline 8 in front of the product valve 15; pressurizing 1MPa (or required pressure) in the blowing container 1 while releasing the pressure in the pipeline, opening the pneumatic blowing valve 5 when the pressure in the pipeline is lower than 1MPa (or required pressure), and extruding residual propellant in the supply pipeline 8 to the recovery container 13 by utilizing the pressure in the blowing container 1;
the pneumatic blow-off valve 5 is opened for 10s and closed for 5s, the propellant in the supply pipeline 8 is blown off, and the pneumatic recovery valve 11 is closed after intermittent blowing off is carried out for three times;
maintaining the pressure of the blowing container 1, opening the product valve 15, blowing the attitude and orbit control engine until no obvious gas representation (white smoke) exists at the nozzle of the attitude and orbit control engine or the room pressure does not change greatly, closing the product valve 15, finishing the blowing work, stopping the vacuum-pumping system, and performing other treatment works.
Claims (10)
1. A posture and orbit control engine high-modulus after-test quick blowing method is characterized in that the method is realized based on a posture and orbit control engine high-modulus after-test quick blowing system, and the posture and orbit control engine high-modulus after-test quick blowing system comprises a propellant blowing unit, a propellant supply unit and a propellant recovery unit;
the propellant blowing unit comprises a blowing container (1), a blowing pipeline (14), a first one-way valve (6), a pneumatic blowing valve (5) and a first one-way filter (4); the inlet of the blowing-off pipeline (14) is connected with the blowing-off container (1), the outlet of the blowing-off pipeline is connected with the propellant supply unit, the first one-way valve (6), the pneumatic blowing-off valve (5) and the first one-way filter (4) are all arranged on the blowing-off pipeline (14), and the inlet and outlet directions of the first one-way valve (6) and the first one-way filter (4) are consistent with the inlet and outlet directions of the blowing-off pipeline (14);
the propellant supply unit comprises a pneumatic supply valve (7), a supply line (8), a second one-way filter (9) and a product valve (15); one end of the supply pipeline (8) is respectively connected with the blowing pipeline (14) and the external propellant pipeline, and the other end of the supply pipeline is connected with the attitude and orbit control engine; the pneumatic supply valve (7) is arranged on a supply pipeline (8) positioned outside the vacuum chamber; the second one-way filter (9) and the product valve (15) are arranged on a supply line (8) located in the vacuum chamber;
the propellant recovery unit comprises a recovery pipeline (16), a two-way filter (10), a pneumatic recovery valve (11), a second one-way valve (12) and a recovery container (13); the inlet of the recovery pipeline (16) is connected with a supply pipeline (8) arranged between a second one-way filter (9) and a product valve (15), the outlet of the recovery pipeline is connected with a recovery container (13), the two-way filter (10) is arranged on the recovery pipeline (16) positioned in the vacuum cabin, the pneumatic recovery valve (11) and the second one-way valve (12) are arranged on the recovery pipeline (16) positioned outside the vacuum cabin, and the inlet and outlet directions of the second one-way valve (12) are consistent with the inlet and outlet directions of the recovery pipeline (16);
the method for quickly blowing off the attitude and orbit control engine after high-modulus test comprises the following steps:
step one, in the ignition process of the attitude and orbit control engine, a pneumatic supply valve (7) is kept normally open, a pneumatic blow-off valve (5) is closed, a pneumatic recovery valve (11) is closed, the deflation systems of a blow-off container (1) and a recovery container (13) are kept closed, and a propellant enters the attitude and orbit control engine through a propellant supply unit;
step two, after the ignition of the attitude and orbit control engine is finished, closing the pneumatic supply valve (7), opening an air discharge system of the recovery container (13), and releasing the pressure of the propellant in the supply pipeline (8) in front of the product valve (15) by the pneumatic recovery valve (11); pressurizing the blowing container (1) while releasing pressure, opening the pneumatic blowing valve (5) after the pressure reaches a set value, and extruding residual propellant in the supply pipeline (8) to the recovery container (13) by utilizing the pressure in the blowing container (1);
step three, opening the pneumatic blow-off valve (5) for a certain time, closing the pneumatic blow-off valve for a certain time, blowing off the propellant in the supply pipeline (8), and closing the pneumatic recovery valve (11) after blowing off the propellant intermittently for N times;
and step four, maintaining the pressure of the blowing container (1), opening the product valve (15), blowing the attitude and orbit control engine until the nozzle of the attitude and orbit control engine has no obvious gas representation or the chamber pressure has no great change, closing the product valve (15), and finishing the blowing operation.
2. The attitude and orbit control engine fast blowing method after high modulus test according to claim 1, characterized in that: a manual blowing supply valve (2) is arranged at an outlet of the blowing container (1), and a normally closed first process hand valve (3) is also arranged on the blowing pipeline (14); a manual recycling supply valve (17) is arranged at an inlet of the recycling container (13), and a normally closed second process hand valve (18) is further arranged on the recycling pipeline (16).
3. The attitude and orbit control engine fast blowing method after high modulus test according to claim 2, characterized in that: the top end of the blowing container (1) is also provided with a pressurizing device and a safety device, and the top end of the recovery container (13) is also provided with a pressurizing device and a safety device.
4. The attitude and orbit control engine fast blowing method after high modulus test according to claim 1, 2 or 3, characterized in that: and a pressure sensor (19) is also arranged on the supply pipeline (8) positioned in the vacuum cabin body.
5. The attitude and orbit control engine fast blowing method after high modulus test according to claim 4, characterized in that: and in the second step, the pressure of the blowing container is increased to 1MPa while the pressure is released.
6. The attitude and orbit control engine fast blowing method after high modulus test according to claim 5, characterized in that: and step three, opening the pneumatic blow-off valve for 10s, then closing the pneumatic blow-off valve for 5s, and intermittently blowing off for three times, and then closing the pneumatic recovery valve.
7. A posture and orbit control engine high-modulus after-test quick blowing system is characterized in that: comprises a propellant blowing unit, a propellant supply unit and a propellant recovery unit;
the propellant blowing unit comprises a blowing container (1), a blowing pipeline (14), a first one-way valve (6), a pneumatic blowing valve (5) and a first one-way filter (4); the inlet of the blowing-off pipeline (14) is connected with the blowing-off container (1), the outlet of the blowing-off pipeline is connected with the propellant supply unit, the first one-way valve (6), the pneumatic blowing-off valve (5) and the first one-way filter (4) are all arranged on the blowing-off pipeline (14), and the inlet and outlet directions of the first one-way valve (6) and the first one-way filter (4) are consistent with the inlet and outlet directions of the blowing-off pipeline (14);
the propellant supply unit comprises a pneumatic supply valve (7), a supply line (8), a second one-way filter (9) and a product valve (15); one end of the supply pipeline (8) is respectively connected with the blowing pipeline (14) and the external propellant pipeline, and the other end of the supply pipeline is connected with the attitude and orbit control engine; the pneumatic supply valve (7) is arranged on a supply pipeline (8) positioned outside the vacuum chamber; the second one-way filter (9) and the product valve (15) are arranged on a supply line (8) located in the vacuum chamber;
the propellant recovery unit comprises a recovery pipeline (16), a two-way filter (10), a pneumatic recovery valve (11), a second one-way valve (12) and a recovery container (13); the inlet of the recovery pipeline (16) is connected with a supply pipeline (8) arranged between the second one-way filter (9) and the product valve (15), the outlet of the recovery pipeline is connected with a recovery container (13), the two-way filter (10) is arranged on the recovery pipeline (16) positioned in the vacuum cabin, the pneumatic recovery valve (11) and the second one-way valve (12) are arranged on the recovery pipeline (16) positioned outside the vacuum cabin, and the inlet and outlet directions of the second one-way valve (12) are consistent with the inlet and outlet directions of the recovery pipeline (16).
8. The attitude and orbit control engine high modulus post rapid blow-off system of claim 7, wherein: a manual blowing supply valve (2) is arranged at an outlet of the blowing container (1), and a normally closed first process hand valve (3) is also arranged on the blowing pipeline (14); a manual recycling supply valve (17) is arranged at an inlet of the recycling container (13), and a normally closed second process hand valve (18) is further arranged on the recycling pipeline (16).
9. The attitude and orbit control engine high modulus post rapid blow-off system of claim 8, further comprising: the top end of the blowing container (1) is also provided with a pressurizing device and a safety device, and the top end of the recovery container (13) is also provided with a pressurizing device and a safety device.
10. An attitude and orbit control engine high mode post-test quick blow-off system according to claim 7, 8 or 9, characterized in that: and a pressure sensor (19) is also arranged on the supply pipeline (8) positioned in the vacuum cabin body.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110586897.0A CN113375943B (en) | 2021-05-27 | 2021-05-27 | Quick blowing method for attitude and orbit control engine after high-mode test |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110586897.0A CN113375943B (en) | 2021-05-27 | 2021-05-27 | Quick blowing method for attitude and orbit control engine after high-mode test |
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| CN113375943A true CN113375943A (en) | 2021-09-10 |
| CN113375943B CN113375943B (en) | 2024-01-12 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114251192A (en) * | 2021-11-05 | 2022-03-29 | 航天科工火箭技术有限公司 | Liquid oxygen methane rocket land after-treatment method |
| CN115638986A (en) * | 2022-12-23 | 2023-01-24 | 北京航天试验技术研究所 | Rocket engine high-altitude simulation test device and hydrogen leakage treatment method thereof |
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| CN114251192A (en) * | 2021-11-05 | 2022-03-29 | 航天科工火箭技术有限公司 | Liquid oxygen methane rocket land after-treatment method |
| CN114251192B (en) * | 2021-11-05 | 2023-03-24 | 航天科工火箭技术有限公司 | Liquid oxygen methane rocket land after-treatment method |
| CN115638986A (en) * | 2022-12-23 | 2023-01-24 | 北京航天试验技术研究所 | Rocket engine high-altitude simulation test device and hydrogen leakage treatment method thereof |
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| CN113375943B (en) | 2024-01-12 |
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