CN110562496A - integrated satellite propulsion system - Google Patents
integrated satellite propulsion system Download PDFInfo
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- CN110562496A CN110562496A CN201910775574.9A CN201910775574A CN110562496A CN 110562496 A CN110562496 A CN 110562496A CN 201910775574 A CN201910775574 A CN 201910775574A CN 110562496 A CN110562496 A CN 110562496A
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- thruster
- integrated
- main body
- interface
- integrated main
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- 239000003380 propellant Substances 0.000 claims abstract description 54
- 238000003860 storage Methods 0.000 claims abstract description 31
- 238000001514 detection method Methods 0.000 claims abstract description 28
- 238000007599 discharging Methods 0.000 claims abstract description 9
- LVGUZGTVOIAKKC-UHFFFAOYSA-N 1,1,1,2-tetrafluoroethane Chemical group FCC(F)(F)F LVGUZGTVOIAKKC-UHFFFAOYSA-N 0.000 claims description 7
- 238000005096 rolling process Methods 0.000 claims description 6
- 238000009826 distribution Methods 0.000 claims description 3
- 238000009413 insulation Methods 0.000 claims description 3
- 230000010354 integration Effects 0.000 abstract description 8
- 239000007788 liquid Substances 0.000 description 7
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 6
- 239000000654 additive Substances 0.000 description 4
- 230000000996 additive effect Effects 0.000 description 4
- 238000013461 design Methods 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 229910021529 ammonia Inorganic materials 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 231100000252 nontoxic Toxicity 0.000 description 2
- 230000003000 nontoxic effect Effects 0.000 description 2
- 108091092878 Microsatellite Proteins 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000000110 cooling liquid Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000005486 microgravity Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 229920006395 saturated elastomer Polymers 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/401—Liquid propellant rocket engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention provides an integrated satellite propulsion system, which comprises: the device comprises an integrated main body structure (1), a charging and discharging valve (2), a thruster (3), a support structure (17) and a detection device (8); the integrated main body structure (1) is an annular structure; a support structure (17) is arranged on the integrated main body structure (1); a thruster interface is arranged on the support structure (17); the thruster (3) is arranged on the thruster interface; the interior of the integrated main body structure (1) is a cavity structure; a flow channel (14), a propellant storage cavity (15) and a propellant management structure (16) are arranged inside the integrated main body structure (1); the flow channel (14) can be communicated with the thruster (3), the detection device (8) and the propellant storage cavity (15). The invention meets the requirements of micro-nano satellites on miniaturization and integration of a propulsion system.
Description
Technical Field
The invention relates to the field of propulsion systems, in particular to an integrated satellite propulsion system, and particularly relates to a novel low-cost integrated liquefied gas micro propulsion system.
background
The propulsion system is a key system for the micro-nano satellite to perform tasks such as attitude control, accurate positioning, position maintenance, resistance compensation, orbit lifting, formation flying of the micro-satellite and the like. A small-sized satellite liquefied gas constant pressure propulsion system and method as disclosed in patent document CN106564623B, comprising a storage tank, wherein ammonia is stored in the storage tank in a gas-liquid two-phase form; a shell of the storage tank is provided with a temperature sensor, and an outlet pipe of the storage tank is provided with a high-pressure sensor for detecting the temperature and the pressure in the storage tank; the storage tank is provided with a heater for increasing the temperature of the storage tank and adjusting the pressure of the propellant in the storage tank; a filling valve is arranged at an outlet pipe of the storage tank and is used for filling ammonia propellant into the storage tank; the output pipeline of the storage tank is connected with a pressure reducing valve and is used for throttling and cooling liquid ammonia and stabilizing downstream pressure; the output pipeline of the pressure reducing valve is connected with an evaporator, and the evaporator is arranged on the storage tank and used for exchanging heat with high-temperature liquid ammonia in the storage tank to ensure that an inlet of the engine is a gaseous propellant; a low-pressure sensor is arranged on an output pipeline of the evaporator and used for detecting the pressure of an inlet of the engine; a cold air engine arranged on an output pipeline of the evaporator provides thrust and impulse required by the satellite, and the requirements of satellite attitude and orbit control functions are met.
However, the conventional propulsion system has the following problems:
1. each functional component of the propulsion system exists in an independent product form and is implemented in a pipeline connection mode, and the final assembly welding of the micro pipelines also needs a longer production period, so that the system space utilization efficiency is lower, the weight and volume control difficulty is high, and the development period is longer.
2. The micro-nano satellite has small volume and light weight, and the traditional propulsion system is difficult to meet the requirements of the micro-nano satellite on the miniaturization and integration of the propulsion system.
Disclosure of Invention
In view of the shortcomings in the prior art, it is an object of the present invention to provide an integrated satellite propulsion system.
According to the invention, an integrated satellite propulsion system is provided, comprising: the device comprises an integrated main body structure 1, an adding and discharging valve 2, a thruster 3, a support structure 17 and a detection device 8;
the integrated main body structure 1 is an annular structure;
The integrated main body structure 1 is provided with a support structure 17;
A thruster interface is arranged on the support structure 17;
The thruster 3 is arranged on the thruster interface;
the interior of the integrated main body structure 1 is a cavity structure;
the integrated main body structure 1 is internally provided with a flow channel 14, a propellant storage cavity 15 and a propellant management structure 16;
the flow channel 14 can be communicated with the thruster 3, the detection device 8 and the propellant storage cavity 15;
The propellant management structure 16 is capable of driving propellant into the flow channel 14;
The charging and discharging valve 2 is arranged on the integrated main body structure 1;
the detection device 8 is mounted on the integrated body structure 1.
preferably, the thruster interface includes: a pitching yawing thruster interface 4 and a rolling thruster interface 5; the pitch yaw thruster interface 4 and the rolling thruster interface 5 are respectively communicated with a flow channel 14 inside the integrated main body structure 1.
Preferably, the integrated main body structure 1, the bracket structure 17 and the thruster interface are integrally formed; and the thruster 3 is fixedly connected with the thruster interface.
Preferably, the integrated main body structure 1 is provided with an exhaust valve installation interface 12; the charging and discharging valve 2 is arranged on the integrated main body structure 1 through a charging and discharging valve mounting interface 12.
Preferably, the integrated main body structure 1 is provided with a detection device mounting interface 13, and the detection device 8 is arranged on the integrated main body structure 1 through the detection device mounting interface 13.
Preferably, the detection means 8 is capable of detecting the propellant pressure inside the propellant storage cavity 15.
preferably, the detection device 8 is capable of cutting off the dispensing channel between the propellant storage cavity 15 to the thruster 3.
Preferably, an expanded module mounting seat 9 and an expanded module orienting boss seat 10 are arranged on the inner side of the integrated main body structure 1; an expansion function module can be arranged on the expansion module mounting seat 9; the expansion module orienting boss base 10 can orient the expansion function module.
Preferably, the propellant is tetrafluoroethane.
preferably, the thruster 3 is connected with the thruster interface through a screw 6; and a heat insulation pad 7 is arranged between the thruster 3 and the thruster interface.
compared with the prior art, the invention has the following beneficial effects:
1. The whole structure of the system is annular, a propellant storage cavity is designed in the system, the wall of the annular integrated main body structure is thin, the strength is high, the annular inner side space can be used for installing the expanded functional module, the space utilization rate is effectively improved, and the system is high in integration level and light in weight.
2. The thruster interface and the support structure are integrally formed in the additive manufacturing process, so that the invalid structure and the weight of the whole system are greatly reduced, and meanwhile, the system is more flexible in configuration due to the adoption of the scheme of integral design and integral manufacturing.
3. The system is of an integrated module structure, and is integrated with a satellite through a flange structure, so that the integration convenience is good.
4. The runner design is integrated during the additive manufacturing design of the integrated main structure, so that the pipeless of the system is realized, and the assembly integration efficiency of the propulsion system is greatly improved.
5. The liquid propellant forms thrust at the jet flow of the throat part of the jet pipe of the thruster in a flash evaporation mode, the pressure of the system is maintained by the self saturation vapor pressure of the propellant, and a pressure adjusting device is not required to be configured, so that the system is simpler to configure on the basis of ensuring the stability of the thrust, and the weight is lighter.
6. the system adopts commercial low-pressure liquefied gas tetrafluoroethane as a propellant, the propellant is green and nontoxic, the acquisition and filling are convenient, the density specific impulse is relatively high, and the filling cost and the volume control advantage of the system are obvious.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
Fig. 1 is a schematic diagram of an overall structure of an integrated satellite propulsion system according to the present invention.
fig. 2 is a schematic structural diagram of an integrated main body of an integrated satellite propulsion system according to the present invention.
the figures show that:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
According to the invention, an integrated satellite propulsion system is provided, comprising: the device comprises an integrated main body structure 1, an adding and discharging valve 2, a thruster 3, a support structure 17 and a detection device 8; the integrated main body structure 1 is an annular structure; the integrated main body structure 1 is provided with a support structure 17; a thruster interface is arranged on the support structure 17; the thruster 3 is arranged on the thruster interface; the interior of the integrated main body structure 1 is a cavity structure; the integrated main body structure 1 is internally provided with a flow channel 14, a propellant storage cavity 15 and a propellant management structure 16; the flow channel 14 can be communicated with the thruster 3, the detection device 8 and the propellant storage cavity 15; the propellant management structure 16 is capable of driving propellant into the flow channel 14; the charging and discharging valve 2 is arranged on the integrated main body structure 1; the detection device 8 is mounted on the integrated main body structure 1; the thruster interface includes: a pitching yawing thruster interface 4 and a rolling thruster interface 5; the pitch yaw thruster interface 4 and the rolling thruster interface 5 are respectively communicated with a flow channel 14 inside the integrated main body structure 1. In a preferred embodiment, the integrated main body structure 1 is an annular-like structure, the propellant storage cavity 15 and the propellant distribution flow channel 14 are designed inside the integrated main body structure, and the thruster interface and the support structure 17 are integrally designed and formed in the additive manufacturing process of the integrated main body structure. The thruster 3, the additional exhaust valve 2 and the detection device 8 are connected into the system through the interfaces arranged at the annular end face of the integrated main body structure, the non-pipeline design of the system is realized, the system assembly integration efficiency is greatly improved, and the system space utilization rate and the integration level are effectively improved. In a preferred embodiment, the thruster 3 and the support structure 17 can be flexibly designed according to requirements, so that the configuration of different thrust quantities and directions can be realized. In a preferred embodiment, the propellant management structure 16 is a tab propellant management structure.
Further, the integrated main body structure 1, the support structure 17 and the thruster interface are integrally formed; the thruster 3 is fixedly connected with the thruster interface; the integrated main body structure 1 is provided with an exhaust valve installation interface 12; the exhaust adding valve 2 is arranged on the integrated main body structure 1 through an exhaust adding valve mounting interface 12; the integrated main body structure 1 is provided with a detection device mounting interface 13, and the detection device 8 is arranged on the integrated main body structure 1 through the detection device mounting interface 13; said detection means 8 being capable of detecting the propellant pressure inside the propellant storage cavity 15; said detection means 8 being able to cut off the dispensing passage between the propellant storage cavity 15 to the thruster 3; an expansion module mounting seat 9 and an expansion module directional boss seat 10 are arranged on the inner side of the integrated main body structure 1; an expansion function module can be arranged on the expansion module mounting seat 9; the expansion module orienting boss base 10 can orient the expansion function module. In a preferred embodiment, the integrated main body structure 1, the support structure 17 and the thruster interface are integrally formed by using an additive manufacturing technology. In a preferred embodiment, six symmetrical supports are arranged on the inner side of the integrated main body structure and used for installing the expansion function module so as to fully utilize the structural space, and boss structures for orientation are arranged on the two supports and used for orienting the installation of the expansion module; and 4 supports are provided with mounting threaded holes for mounting the expanded functional modules. The system is of an integrated module structure, and is integrated with the micro-nano satellite through the connecting flange 11, so that the integration convenience is good. In a preferred embodiment, the detection device 8 is adapted to cut off the dispensing channel between the propellant storage cavity 15 and the thruster 3 in a system-commissioned, stored state, and to detect the propellant pressure in the propellant storage cavity 15.
Still further, the propellant is tetrafluoroethane; the thruster 3 is connected with the thruster interface through a screw 6; and a heat insulation pad 7 is arranged between the thruster 3 and the thruster interface. In a preferred embodiment, the system adopts nontoxic and harmless commercial liquefied gas tetrafluoroethane as a propellant, and has the characteristics of high density specific impulse and low cost. Tetrafluoroethane stored in the internal cavity of the integrated main structure 1 is in a gas-liquid mixed state, propellant gas-liquid distribution state under microgravity condition is managed through the propellant management structure 16 in the integrated main structure 1, and liquid propellant is driven by vapor pressure of gaseous tetrafluoroethane to distribute propellant through the internal flow channel 14 in the integrated main structure 1. In a preferred embodiment, the liquid propellant enters the thruster 3 through the internal flow passage 14, flash jet flow is generated after passing through the spray pipe, only a small amount of propellant in the system is gasified to compensate volume change caused by consumption of the liquid propellant, and the system pressure is automatically maintained by the saturated vapor pressure of the propellant during the working process of the system without configuring a pressure regulating device.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
the foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. An integrated satellite propulsion system, comprising: the device comprises an integrated main body structure (1), a charging and discharging valve (2), a thruster (3), a support structure (17) and a detection device (8);
the integrated main body structure (1) is an annular structure;
A support structure (17) is arranged on the integrated main body structure (1);
A thruster interface is arranged on the support structure (17);
The thruster (3) is arranged on the thruster interface;
The interior of the integrated main body structure (1) is a cavity structure;
a flow channel (14), a propellant storage cavity (15) and a propellant management structure (16) are arranged inside the integrated main body structure (1);
The flow channel (14) can be communicated with the thruster (3), the detection device (8) and the propellant storage cavity (15);
The propellant management structure (16) being capable of driving propellant into the flow channel (14);
The charging and discharging valve (2) is arranged on the integrated main body structure (1);
the detection device (8) is mounted on the integrated main body structure (1).
2. The integrated satellite propulsion system of claim 1, wherein the thruster interface comprises: a pitching yawing thruster interface (4) and a rolling thruster interface (5); the pitching yawing thruster interface (4) and the rolling thruster interface (5) are respectively communicated with a flow channel (14) in the integrated main body structure (1).
3. Integrated satellite propulsion system according to claim 1, characterized in that the integrated main structure (1), the support structure (17) and the thruster interface are integrally formed; and the thruster (3) is fixedly connected with the thruster interface.
4. An integrated satellite propulsion system according to claim 1, characterized in that the integrated main body structure (1) is provided with a charge and discharge valve mounting interface (12); the exhaust adding valve (2) is arranged on the integrated main body structure (1) through an exhaust adding valve mounting interface (12).
5. Integrated satellite propulsion system according to claim 1, characterized in that the integrated main structure (1) is provided with a detection device mounting interface (13), the detection device (8) being provided on the integrated main structure (1) through the detection device mounting interface (13).
6. Integrated satellite propulsion system according to claim 1, characterized in that the detection means (8) are able to detect the propellant pressure inside the propellant storage cavity (15).
7. integrated satellite propulsion system according to claim 1, characterized in that the detection device (8) is able to cut off the distribution channel between the propellant storage cavity (15) to the thruster (3).
8. an integrated satellite propulsion system according to claim 1, characterized in that the inner side of the integrated main structure (1) is provided with an expansion module mounting seat (9) and an expansion module orientation boss seat (10); an expansion function module can be arranged on the expansion module mounting seat (9); the expansion module orientation boss seat (10) can orient the expansion function module.
9. The integrated satellite propulsion system of claim 1, wherein the propellant is tetrafluoroethane.
10. The integrated satellite propulsion system according to claim 1, characterized in that the thruster (3) is connected with the thruster interface by means of screws (6); and a heat insulation pad (7) is arranged between the thruster (3) and the thruster interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910775574.9A CN110562496B (en) | 2019-08-21 | 2019-08-21 | Integrated satellite propulsion system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910775574.9A CN110562496B (en) | 2019-08-21 | 2019-08-21 | Integrated satellite propulsion system |
Publications (2)
| Publication Number | Publication Date |
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| CN110562496A true CN110562496A (en) | 2019-12-13 |
| CN110562496B CN110562496B (en) | 2021-05-11 |
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| CN201910775574.9A Active CN110562496B (en) | 2019-08-21 | 2019-08-21 | Integrated satellite propulsion system |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101907041A (en) * | 2010-07-23 | 2010-12-08 | 北京航空航天大学 | Propane liquid gas micro propulsion device suitable for micro-nano satellite |
| CN202389602U (en) * | 2011-06-08 | 2012-08-22 | 航天东方红卫星有限公司 | Universal propelling module of small satellite |
| CN103930348A (en) * | 2011-09-20 | 2014-07-16 | 国家空间研究中心 | Propulsion bay |
| CN107352051A (en) * | 2017-07-13 | 2017-11-17 | 上海航天控制技术研究所 | Multidirectional thrust integrated form microthruster and its control method |
| CN107891999A (en) * | 2017-09-30 | 2018-04-10 | 北京控制工程研究所 | Single group member micromass culture modular device and its boosting method based on increases material manufacturing technology |
| CN108190048A (en) * | 2017-12-05 | 2018-06-22 | 北京控制工程研究所 | A kind of micromodule butane propulsion system structure and propulsion method |
-
2019
- 2019-08-21 CN CN201910775574.9A patent/CN110562496B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101907041A (en) * | 2010-07-23 | 2010-12-08 | 北京航空航天大学 | Propane liquid gas micro propulsion device suitable for micro-nano satellite |
| CN202389602U (en) * | 2011-06-08 | 2012-08-22 | 航天东方红卫星有限公司 | Universal propelling module of small satellite |
| CN103930348A (en) * | 2011-09-20 | 2014-07-16 | 国家空间研究中心 | Propulsion bay |
| CN107352051A (en) * | 2017-07-13 | 2017-11-17 | 上海航天控制技术研究所 | Multidirectional thrust integrated form microthruster and its control method |
| CN107891999A (en) * | 2017-09-30 | 2018-04-10 | 北京控制工程研究所 | Single group member micromass culture modular device and its boosting method based on increases material manufacturing technology |
| CN108190048A (en) * | 2017-12-05 | 2018-06-22 | 北京控制工程研究所 | A kind of micromodule butane propulsion system structure and propulsion method |
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| CN110562496B (en) | 2021-05-11 |
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