CN117622538A - Overload adjusting device for microgravity test - Google Patents
Overload adjusting device for microgravity test Download PDFInfo
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- CN117622538A CN117622538A CN202311602525.8A CN202311602525A CN117622538A CN 117622538 A CN117622538 A CN 117622538A CN 202311602525 A CN202311602525 A CN 202311602525A CN 117622538 A CN117622538 A CN 117622538A
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- 230000005486 microgravity Effects 0.000 title claims abstract description 61
- 238000012360 testing method Methods 0.000 title claims abstract description 39
- 239000007921 spray Substances 0.000 claims abstract description 59
- 230000009467 reduction Effects 0.000 claims abstract description 18
- 238000005507 spraying Methods 0.000 claims abstract description 9
- 238000000034 method Methods 0.000 abstract description 16
- 230000008569 process Effects 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 description 6
- 238000012986 modification Methods 0.000 description 5
- 230000004048 modification Effects 0.000 description 5
- 230000008859 change Effects 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 235000015842 Hesperis Nutrition 0.000 description 2
- 235000012633 Iberis amara Nutrition 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000004080 punching Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000006837 decompression Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
An embodiment of the present application provides an overload adjustment device for a microgravity test, including: a cabin falling platform mounting plate; the cold flow spray pipe is positioned below the cabin falling platform mounting plate and is provided with a cold flow spray pipe inlet, a secondary flow inlet and a cold flow spray pipe outlet, and the cold flow spray pipe is used for spraying high-pressure gas; the high-pressure gas cylinder group, the primary pressure reducing pipeline and the secondary pressure reducing pipeline are respectively arranged on the cabin falling platform mounting plate, one end of the primary pressure reducing pipeline is connected with the high-pressure gas cylinder group, and the other end of the primary pressure reducing pipeline is connected with the cold flow spray pipe inlet; one end of the secondary pressure reducing pipeline is connected with the primary pressure reducing pipeline for carrying out secondary pressure reduction on the gas, and the other end of the secondary pressure reducing pipeline is connected with the secondary inflow port. According to the method, the thrust and the direction are adjustable through a secondary cold flow method, and in the microgravity environment test process, the magnitude and the direction of the microgravity falling cabin microgravity are controlled through adjusting the thrust and the direction of the cold flow spray pipe, so that the controllable microgravity level is realized.
Description
Technical Field
The application relates to the technical field of space environment simulation tests, in particular to an overload adjusting device for a microgravity test.
Background
In order to solve the microgravity problem of carrier rockets and satellites, test means such as tower falling, pipe falling, airplane, balloon, sounding rocket, satellite recovery, suspension and the like are successively established in each country. Among ground test equipment, falling towers are one of the most effective microgravity research means. The microgravity falling tower has the advantages of repeatability number, high microgravity level, easy guarantee of initial conditions, convenient data acquisition, low cost, easy operation, small interference and the like, and the microgravity test device is an important device for developing application research of liquid management engineering in the microgravity environment in the aerospace field, meets the development needs of aerospace, and improves the capability and level necessary guarantee of liquid rockets and aerospace aircrafts in China. Especially when the rail needs long-time inertial flight and the engine is restarted for a plurality of times, the fluid form of the liquid propellant in the microgravity environment is critical to the engine starting. Therefore, the variable overload control capability is required to be realized in the microgravity test process, and the secondary starting, posture adjustment and separation process of the aircraft engine in the space environment can be truly simulated.
The cabin falling equipment in most foreign microgravity test facilities only has the function of obtaining higher residual microgravity level, and the few towers realize accurate adjustment of the microgravity level by adopting a linear motor thrust system and a booster. The device does not have the test capability of simulating the posture, the shaking and the like under the microgravity.
Disclosure of Invention
The embodiment of the application provides an overload adjusting device for a microgravity test, which is used for solving the problem that the existing microgravity test equipment does not have the fine tuning capability of simulating the gesture, shaking and the like under the microgravity.
In order to achieve the above purpose, the present application provides the following technical solutions:
an overload adjustment apparatus for microgravity testing, comprising:
a cabin falling platform mounting plate;
the cold flow spray pipe is positioned below the cabin falling platform mounting plate and is provided with a cold flow spray pipe inlet, a secondary flow inlet and a cold flow spray pipe outlet, and the cold flow spray pipe is used for spraying high-pressure gas;
the high-pressure gas cylinder group, the primary pressure reducing pipeline and the secondary pressure reducing pipeline are respectively arranged on the cabin falling platform mounting plate, one end of the primary pressure reducing pipeline is connected with the high-pressure gas cylinder group, and the other end of the primary pressure reducing pipeline is connected with the cold flow spray pipe inlet; one end of the secondary pressure reducing pipeline is connected with the primary pressure reducing pipeline and used for carrying out secondary pressure reduction on gas, and the other end of the secondary pressure reducing pipeline is connected with the secondary inflow port.
Optionally, the primary pressure reducing line includes:
the first pressure reducing valve, the first stop valve and the first electromagnetic switch valve are sequentially arranged, the first pressure reducing valve is connected with the high-pressure gas cylinder group and used for reducing pressure of high-pressure gas once, and the first electromagnetic switch valve is connected with the cold flow spray pipe inlet through a pipeline.
Optionally, the primary pressure reducing line further comprises:
and the first pressure sensor is positioned between the first pressure reducing valve and the first stop valve and is used for detecting the gas pressure of the high-pressure gas after primary pressure reduction.
Optionally, the secondary pressure relief line includes:
the second pressure reducing valve is connected with the first electromagnetic switch valve and used for carrying out secondary pressure reduction on high-pressure gas, and the second electromagnetic switch valve is connected with the secondary inflow port through a pipeline.
Optionally, the secondary pressure reducing line further comprises:
and the second pressure sensor is positioned between the second pressure reducing valve and the second electromagnetic switch valve and is used for detecting the gas pressure of the high-pressure gas after secondary pressure reduction.
Optionally, the method further comprises:
one end of the inflation pipeline is connected with the high-pressure gas cylinder group, the inflation pipeline is provided with an inflation inlet and a second stop valve, and the inflation inlet is connected with a gas source; the second stop valve is positioned between the high-pressure gas cylinder group and the charging port and is used for controlling the on-off of the charging pipeline.
Optionally, the inflation line further comprises:
and the third pressure sensor is positioned between the high-pressure gas cylinder group and the second stop valve and is used for measuring the gas pressure of the high-pressure gas cylinder group.
Optionally, the high-pressure gas cylinder group comprises at least two high-pressure gas cylinders which are arranged in parallel.
Optionally, the method further comprises:
the valve block is positioned on the cabin falling platform mounting plate and is provided with an air inlet cavity; the cold flow spray pipe penetrates through the wall thickness of the cabin falling platform mounting plate, is fixed with the bottom wall of the valve block and is communicated with the air inlet cavity, and the first electromagnetic switch valve is communicated with the air inlet cavity through a pipeline and supplies air for the inlet of the cold flow spray pipe.
Optionally, the method further comprises:
and the control assembly is respectively connected with the first pressure reducing valve, the first stop valve, the first electromagnetic switch valve, the first pressure sensor, the second pressure reducing valve, the second electromagnetic switch valve and the second pressure sensor.
An overload adjusting device for microgravity test that this application embodiment provided, include: a cabin falling platform mounting plate; the cold flow spray pipe is positioned below the cabin falling platform mounting plate and is provided with a cold flow spray pipe inlet, a secondary flow inlet and a cold flow spray pipe outlet, and the cold flow spray pipe is used for spraying high-pressure gas; the high-pressure gas cylinder group, the primary pressure reducing pipeline and the secondary pressure reducing pipeline are respectively arranged on the cabin falling platform mounting plate, one end of the primary pressure reducing pipeline is connected with the high-pressure gas cylinder group, and the other end of the primary pressure reducing pipeline is connected with the cold flow spray pipe inlet; one end of the secondary pressure reducing pipeline is connected with the primary pressure reducing pipeline for carrying out secondary pressure reduction on the gas, and the other end of the secondary pressure reducing pipeline is connected with the secondary inflow port.
Adopt the overload adjusting device for microgravity test that provides in this application embodiment, compare in prior art, have following technical effect:
the thrust force and the direction are adjustable through a secondary cold flow method, specifically, a cold flow spray pipe, a high-pressure gas cylinder group, a primary pressure reducing pipeline, a secondary pressure reducing pipeline and the like are arranged, the primary pressure reducing pipeline is used for carrying out primary pressure reduction on high-pressure gas and spraying the high-pressure gas along an inlet of the cold flow spray pipe, and the secondary pressure reducing pipeline is used for carrying out secondary pressure reduction on the high-pressure gas and spraying the high-pressure gas through a secondary inlet; by adopting the device, in the microgravity environment test process, the magnitude and the direction of the microgravity falling cabin microgravity can be controlled by adjusting the thrust magnitude and the direction of the cold flow spray pipe, so that the controllable microgravity level is realized.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiments of the application and together with the description serve to explain the application and do not constitute an undue limitation to the application. In the drawings:
fig. 1 is a schematic structural diagram of an overload adjustment device for microgravity test according to an embodiment of the present application;
FIG. 2 is a schematic diagram of an installation structure of a cold flow nozzle according to an embodiment of the present disclosure;
fig. 3 is a schematic structural diagram of a cold flow nozzle according to an embodiment of the present disclosure.
The figures are marked as follows:
the system comprises a cabin falling platform mounting plate 1, a first pressure reducing valve 2, a first high-pressure gas cylinder 3, a third pressure sensor 4, a first pressure sensor 5, a first stop valve 6, a first electromagnetic switch valve 7, a second stop valve 8, a second pressure reducing valve 9, a second pressure sensor 10, a second electromagnetic switch valve 11, a second high-pressure gas cylinder 12, an inflation inlet 13, a valve block 14 and a cold flow spray pipe 15;
a cold flow nozzle inlet 151, a secondary flow inlet 152, a cold flow nozzle outlet 153.
Detailed Description
The embodiment of the invention discloses an overload adjusting device for a microgravity test, which aims to solve the problem that the conventional microgravity test equipment does not have the capability of simulating fine adjustment of gestures, shaking and the like under the microgravity.
In order to make the technical solutions and advantages of the embodiments of the present application more apparent, the following detailed description of exemplary embodiments of the present application is given with reference to the accompanying drawings, and it is apparent that the described embodiments are only some of the embodiments of the present application and not exhaustive of all the embodiments. It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other.
Referring to fig. 1 to 3, fig. 1 is a schematic structural diagram of an overload adjusting device for microgravity test according to an embodiment of the present application; FIG. 2 is a schematic diagram of an installation structure of a cold flow nozzle according to an embodiment of the present disclosure; fig. 3 is a schematic structural diagram of a cold flow nozzle according to an embodiment of the present disclosure.
In a specific embodiment, the overload adjusting device for the microgravity test provided by the application comprises a cabin falling platform mounting plate 1, a cold flow spray pipe 15, a high-pressure gas cylinder group, a primary pressure reducing pipeline and a secondary pressure reducing pipeline; the cold flow spray pipe 15, the high-pressure gas cylinder group, the primary pressure reducing pipeline and the secondary pressure reducing pipeline are respectively arranged on the cabin-falling platform mounting plate 1, and are preferably detachably and fixedly connected so as to facilitate disassembly and assembly; the cold flow spray pipe 15 is designed into a device structure according to design requirements, the cold flow spray pipe 15 comprises a cold flow spray pipe inlet 151, a secondary flow inlet 152 and a cold flow spray pipe outlet 153, and the cold flow spray pipe 15 is used for spraying high-pressure gas; the high pressure gas cylinder group provides the pipeline with high pressure gas, and the high pressure gas cylinder group comprises at least two high pressure gas cylinders which are arranged in parallel, and preferably comprises a first high pressure gas cylinder 3 and a second high pressure gas cylinder 12. One end of the primary pressure reducing pipeline is connected with the high-pressure gas cylinder group, and the other end of the primary pressure reducing pipeline is connected with the cold flow spray pipe inlet 151; one end of the secondary pressure reducing pipe is connected to the primary pressure reducing pipe for secondarily reducing pressure of the gas, and the other end of the secondary pressure reducing pipe is connected to the secondary inflow port 152.
In general, during the drop cabin microgravity test, the pressure of the secondary inlet 152 is smaller than the gas pressure of the cold flow nozzle inlet 151 to change the thrust and direction of the cold flow nozzle 15.
Adopt the overload adjusting device for microgravity test that provides in this application embodiment, compare in prior art, have following technical effect:
the thrust and direction are adjustable through a secondary cold flow method, specifically, a cold flow spray pipe 15, a high-pressure gas cylinder group, a primary pressure reducing pipeline, a secondary pressure reducing pipeline and the like are arranged, the primary pressure reducing pipeline is used for carrying out primary pressure reduction on high-pressure gas and spraying the high-pressure gas along a cold flow spray pipe inlet 151, and the secondary pressure reducing pipeline is used for carrying out secondary pressure reduction on the high-pressure gas and spraying the high-pressure gas through a secondary inflow 152; by adopting the device, in the microgravity environment test process, the magnitude and the direction of the thrust of the cold flow spray pipe 15 are adjusted, so that the magnitude and the direction of microgravity falling cabin microgravity are controlled, and the controllable microgravity level is realized.
The high-pressure gas cylinder is made of carbon fiber composite materials and is a power source of high-pressure thrust. The stop valve controls the on-off of each air supply pipeline of the high-pressure air source, the pressure reducing valve adjusts the air supply pressure to the pressure required by the inlet 151 of the cold flow spray pipe, the pressure sensor is arranged at the air supply key point of the device, and the pressure sensor monitors the pressure of the air bottle and the pressure after the pressure reducing valve reduces the pressure. The cold flow nozzle 15 is mounted on the valve block 14, and the flow channel of the valve block 14 is in butt joint with the cold flow nozzle inlet 151 to send high-pressure gas into the cold flow nozzle 15. The controller sends a time sequence control signal, the quick-opening electromagnetic valve receives the control signal and is opened, high-pressure gas is quickly introduced into the cold flow spray pipe 15, the high-pressure gas is accelerated in the cold flow spray pipe 15, the gas flows out of a spray pipe outlet at supersonic speed to generate thrust, the thrust acts on the cabin-falling platform, and the cabin-falling microgravity level is changed. The response time of the quick-opening electromagnetic valve is in the order of ms, and the cold flow spray pipes 15 with different specifications can generate thrust with different magnitudes.
The cold flow spray pipe 15 is provided with a secondary flow inlet 152, a flow passage is reserved through the valve block 14, and the secondary flow inlet 152 is connected with the flow passage outlet of the valve block 14 through a hose. The secondary flow air supply branch is also provided with a stop valve, a pressure reducing valve, a pressure sensor and a quick electromagnetic valve. The pressure sensor sends the pressure signal after decompression to the controller for display, and the controller controls the fast solenoid valve of the secondary flow gas supply branch via time sequence control command to control the on-off of the secondary flow gas supply branch. By adjusting the pressure behind the secondary flow air supply branch relief valve, the primary flow of the high-pressure cold flow spray pipe 15 can be changed by the secondary jet flow.
Specifically, the primary pressure reducing line includes:
the first pressure reducing valve 2, the first stop valve 6 and the first electromagnetic switch valve 7 are sequentially arranged, the first pressure reducing valve 2 is connected with the high-pressure gas cylinder group and used for reducing pressure of high-pressure gas once, and the first electromagnetic switch valve 7 is connected with the cold flow spray pipe inlet 151 through a pipeline.
In this embodiment, the primary pressure reducing line further comprises a first pressure sensor 5, located between the first pressure reducing valve 2 and the first shut-off valve 6, for detecting the gas pressure of the high-pressure gas after the primary pressure reduction.
In another embodiment, the secondary pressure relief circuit includes:
the second pressure reducing valve 9 and the second electromagnetic switch valve 11, the second pressure reducing valve 9 is connected with the first electromagnetic switch valve 7 for carrying out secondary pressure reduction on the high-pressure gas, and the second electromagnetic switch valve 11 is connected with the secondary inlet 152 through a pipeline.
And a second pressure sensor 10, located between the second pressure reducing valve 9 and the second electromagnetic switch valve 11, for detecting the gas pressure of the high-pressure gas after the secondary pressure reduction.
Preferably, the method further comprises:
one end of the air charging pipeline is connected with the high-pressure air cylinder group, the air charging pipeline is provided with an air charging port 13 and a second stop valve 8, and the air charging port 13 is connected with an air source; the second stop valve 8 is positioned between the high-pressure gas cylinder group and the charging port 13 and is used for controlling the on-off of the charging pipeline;
and a third pressure sensor 4, which is positioned between the high-pressure gas cylinder group and the second stop valve 8, and is used for measuring the gas pressure of the high-pressure gas cylinder group.
The device further comprises:
the valve block 14 is positioned on the cabin falling platform mounting plate 1 and is provided with an air inlet cavity; the cold flow spray pipe 15 penetrates through the wall thickness of the cabin falling platform mounting plate 1, is fixed with the bottom wall of the valve block 14 and is communicated with the air inlet cavity, and the first electromagnetic switch valve 7 is communicated with the air inlet cavity through a pipeline to supply air for the cold flow spray pipe inlet 151.
The device further comprises a control assembly which is respectively connected with the first pressure reducing valve 2, the first stop valve 6, the first electromagnetic switch valve 7, the first pressure sensor 5, the second pressure reducing valve 9, the second electromagnetic switch valve 11 and the second pressure sensor 10.
In a specific embodiment, two high-pressure cylinders are installed in parallel via a pipeline, and a third pressure sensor 4 is arranged between the high-pressure cylinder group and the second stop valve 8 for measuring the gas pressure in the high-pressure cylinder group. The first pressure sensor 5 is arranged between the first pressure reducing valve 2 and the first stop valve 6 and is used for measuring the gas pressure of the high-pressure gas after one-time pressure reduction; the second pressure sensor 10 is arranged between the second pressure reducing valve 9 and the second electromagnetic switch valve 11 and is used for measuring the gas pressure after the secondary flow gas supply is reduced, the cold flow spray pipe 15 is arranged at the bottom of the valve block 14, and the first electromagnetic switch valve 7 is connected to the gas inlet cavity of the valve block 14 through a pipeline and is used for supplying gas to the cold flow spray pipe inlet 151; the second electromagnetic opening/closing valve 11 communicates with the secondary inflow port 152 via a hose, and supplies high-pressure gas thereto.
And opening the second stop valve 8, punching the high-pressure gas cylinder group through the charging port 13, monitoring the pressure of the current high-pressure gas cylinder group in real time by the third pressure sensor 4, and closing the second stop valve 8 after the pressure reaches the target pressure for charging, so as to finish gas cylinder punching.
And the first pressure reducing valve 2 and the second pressure reducing valve 9 are regulated, the first pressure sensor 5 and the second pressure sensor 10 monitor the pressure values of the two pressure reducing pipelines after the pressure is reduced, and after the two pressure values reach the regulating pressure, the regulation of the first pressure reducing valve 2 and the second pressure reducing valve 9 is stopped, so that the pressure regulation of the high-pressure pipeline is completed.
Lifting the cabin falling platform mounting plate 1 to a certain height, synchronously sending time sequence control signals to the first electromagnetic switch valve 7 and the second electromagnetic switch valve 11 by the control component when releasing the cabin falling platform, respectively conveying the depressurized high-pressure gas to the cold flow spray pipe inlet 151 and the secondary flow inlet 152, and releasing the gas flow through the cold flow spray pipe outlet 153 in a supersonic speed state after the high-pressure gas is subjected to main supplementary acceleration by the cold flow spray pipe 15, so as to generate a reaction force to fall to the cabin falling platform mounting plate 1 to change the microgravity level of the cabin falling platform mounting plate 1 in the free falling process, thereby realizing the overload changing function of the microgravity test. After the cabin falling platform is recovered, the first electromagnetic switch valve 7 and the second electromagnetic switch valve 11 are closed.
The device adopts a method based on cold flow thrust, generates thrust through the cold flow spray pipe 15, acts on the microgravity test falling cabin, changes the microgravity level in the microgravity test process of the falling cabin test platform, and can simulate different microgravity environments. The main flow direction of the cold flow spray pipe 15 is changed, so that the change of the cold flow thrust direction can be realized, and the attitude adjustment process of the microgravity environment of the on-orbit aircraft can be realized under the ground simulation microgravity environment.
While preferred embodiments of the present application have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. It is therefore intended that the following claims be interpreted as including the preferred embodiments and all such alterations and modifications as fall within the scope of the application.
It will be apparent to those skilled in the art that various modifications and variations can be made in the present application without departing from the spirit or scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims and the equivalents thereof, the present application is intended to cover such modifications and variations.
Claims (10)
1. An overload adjustment apparatus for microgravity testing, comprising:
a cabin falling platform mounting plate;
the cold flow spray pipe is positioned below the cabin falling platform mounting plate and is provided with a cold flow spray pipe inlet, a secondary flow inlet and a cold flow spray pipe outlet, and the cold flow spray pipe is used for spraying high-pressure gas;
the high-pressure gas cylinder group, the primary pressure reducing pipeline and the secondary pressure reducing pipeline are respectively arranged on the cabin falling platform mounting plate, one end of the primary pressure reducing pipeline is connected with the high-pressure gas cylinder group, and the other end of the primary pressure reducing pipeline is connected with the cold flow spray pipe inlet; one end of the secondary pressure reducing pipeline is connected with the primary pressure reducing pipeline and used for carrying out secondary pressure reduction on gas, and the other end of the secondary pressure reducing pipeline is connected with the secondary inflow port.
2. An overload adjustment device for microgravity testing according to claim 1, wherein the primary pressure relief line comprises:
the first pressure reducing valve, the first stop valve and the first electromagnetic switch valve are sequentially arranged, the first pressure reducing valve is connected with the high-pressure gas cylinder group and used for reducing pressure of high-pressure gas once, and the first electromagnetic switch valve is connected with the cold flow spray pipe inlet through a pipeline.
3. An overload adjustment apparatus for a microgravity test according to claim 2, wherein the primary pressure relief line further comprises:
and the first pressure sensor is positioned between the first pressure reducing valve and the first stop valve and is used for detecting the gas pressure of the high-pressure gas after primary pressure reduction.
4. An overload adjustment device for microgravity tests according to claim 3 wherein the secondary pressure relief circuit comprises:
the second pressure reducing valve is connected with the first electromagnetic switch valve and used for carrying out secondary pressure reduction on high-pressure gas, and the second electromagnetic switch valve is connected with the secondary inflow port through a pipeline.
5. The overload adjustment apparatus for microgravity test of claim 4, wherein the secondary pressure relief circuit further comprises:
and the second pressure sensor is positioned between the second pressure reducing valve and the second electromagnetic switch valve and is used for detecting the gas pressure of the high-pressure gas after secondary pressure reduction.
6. An overload adjustment apparatus for a microgravity test according to claim 1, further comprising:
one end of the inflation pipeline is connected with the high-pressure gas cylinder group, the inflation pipeline is provided with an inflation inlet and a second stop valve, and the inflation inlet is connected with a gas source; the second stop valve is positioned between the high-pressure gas cylinder group and the charging port and is used for controlling the on-off of the charging pipeline.
7. The overload adjustment apparatus for a microgravity test of claim 6, wherein the inflation line further comprises:
and the third pressure sensor is positioned between the high-pressure gas cylinder group and the second stop valve and is used for measuring the gas pressure of the high-pressure gas cylinder group.
8. An overload adjustment device for microgravity experiments according to claim 1 wherein the set of high pressure cylinders comprises at least two high pressure cylinders arranged in parallel.
9. An overload adjustment apparatus for a microgravity test according to claim 1, further comprising:
the valve block is positioned on the cabin falling platform mounting plate and is provided with an air inlet cavity; the cold flow spray pipe penetrates through the wall thickness of the cabin falling platform mounting plate, is fixed with the bottom wall of the valve block and is communicated with the air inlet cavity, and the first electromagnetic switch valve is communicated with the air inlet cavity through a pipeline and supplies air for the inlet of the cold flow spray pipe.
10. An overload adjustment apparatus for a microgravity test according to claim 1, further comprising:
and the control assembly is respectively connected with the first pressure reducing valve, the first stop valve, the first electromagnetic switch valve, the first pressure sensor, the second pressure reducing valve, the second electromagnetic switch valve and the second pressure sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311602525.8A CN117622538A (en) | 2023-11-28 | 2023-11-28 | Overload adjusting device for microgravity test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311602525.8A CN117622538A (en) | 2023-11-28 | 2023-11-28 | Overload adjusting device for microgravity test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117622538A true CN117622538A (en) | 2024-03-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311602525.8A Pending CN117622538A (en) | 2023-11-28 | 2023-11-28 | Overload adjusting device for microgravity test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117622538A (en) |
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- 2023-11-28 CN CN202311602525.8A patent/CN117622538A/en active Pending
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