CN108928505B - Satellite active section exhaust method controlled by satellite and rocket falling plug signal - Google Patents
Satellite active section exhaust method controlled by satellite and rocket falling plug signal Download PDFInfo
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- CN108928505B CN108928505B CN201810684012.9A CN201810684012A CN108928505B CN 108928505 B CN108928505 B CN 108928505B CN 201810684012 A CN201810684012 A CN 201810684012A CN 108928505 B CN108928505 B CN 108928505B
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- 238000000034 method Methods 0.000 title claims abstract description 17
- 230000008859 change Effects 0.000 claims abstract description 9
- 230000003993 interaction Effects 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 4
- 238000000926 separation method Methods 0.000 description 3
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 2
- MHAJPDPJQMAIIY-UHFFFAOYSA-N Hydrogen peroxide Chemical compound OO MHAJPDPJQMAIIY-UHFFFAOYSA-N 0.000 description 2
- 230000033001 locomotion Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000003321 amplification Effects 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
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- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Stored Programmes (AREA)
Abstract
The invention provides a satellite active section exhaust method controlled by satellite and rocket falling plug signals, which comprises the following steps: the method adopts a main and standby redundant control circuit, and finishes the on-off task of a drop signal line through the working state change of a satellite and rocket drop plug/socket; after the satellite and rocket falling plug/socket falls off, the falling signal line is in a disconnected state; the change of the level of the shedding signal is collected by a satellite integrated electronic computer, and a control signal is output after corresponding operation and processing, so that the control task of the exhaust valve of the propulsion system is completed. The invention reduces the data interaction between the ground station and the satellite in the active section, reduces the influence of other actions in the active section on the pipeline exhaust, enhances the self-management capability of the satellite, and ensures that the satellite can smoothly complete the pipeline exhaust work of a propulsion system in the active section.
Description
Technical Field
The invention relates to an exhaust method for a satellite active section, in particular to an exhaust method for a satellite active section, which is controlled by a satellite arrow falling plug signal.
Background
Thousands of satellites with various purposes are launched in succession in countries around the world, and the on-board propulsion system of the satellites correspondingly develops various propulsion technologies such as single-component hydrazine, double-mode and electric propulsion and the like from cold air and hydrogen peroxide. The performance of the system directly influences the control precision, the service life and the reliability of the satellite. An exhaust valve is arranged above each storage tank of the propulsion system and used for extruding gas in a propulsion pipeline, so that the equal amount of the propellant filled into each group of storage tanks is ensured, good atomization and mixing can be realized, the combustion efficiency is improved, and stable thrust performance is obtained. At present, an exhaust valve receives a control signal sent by a control system after separation of a satellite and an arrow, and drives an electromagnetic valve of a thruster or a self-locking valve to complete an exhaust process after power amplification, or receives a ground remote control instruction to complete a control function of the self-locking valve. However, since the motions such as damping, initial bias elimination, posture adjustment and the like need to be completed after the separation of the satellite and the arrow, in order to avoid the influence of the exhaust of the pipeline of the propulsion system on the motions, the pipeline exhaust task of the propulsion system can be completed at the satellite launching active section before the separation of the satellite and the arrow.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a satellite active section exhaust method controlled by satellite and rocket falling plug signals, which realizes the extrusion of gas in a pipeline line of a propulsion system.
According to one aspect of the invention, a satellite active section exhaust method controlled by satellite rocket falling plug signals is provided, and is characterized by comprising the following steps: the method adopts a main and standby redundant control circuit, and finishes the on-off task of a drop signal line through the working state change of a satellite and rocket drop plug/socket; after the satellite and rocket falling plug/socket falls off, the falling signal line is in a disconnected state; the change of the level of the shedding signal is collected by a satellite integrated electronic computer, and a control signal is output after corresponding operation and processing, so that the control task of the exhaust valve of the propulsion system is completed.
Preferably, the on-off task is specifically represented by that before the star-arrow falling plug/socket falls off, the falling signal line is in a conducting state.
Compared with the prior art, the invention has the following beneficial effects: the invention reduces the data interaction between the ground station and the satellite in the active section, reduces the influence of other actions in the active section on the pipeline exhaust, enhances the self-management capability of the satellite, and ensures that the satellite can smoothly complete the pipeline exhaust work of a propulsion system in the active section.
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 the exhaust method of the active section of the satellite controlled by the star-arrow falling plug signal according to the present invention.
Fig. 2 is a timing chart of control by a satellite drop plug drop signal.
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 variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, the method for exhausting gas in the active section of the satellite controlled by the satellite and rocket falling plug signal of the invention comprises the following steps: the method adopts a main and standby redundant control circuit, and finishes the on-off task of the drop signal line through the working state change of the satellite and rocket drop plug/socket, wherein the on-off task is specifically represented as that before the satellite and rocket drop plug/socket drops, the drop signal line 2 is in a conducting state; after the star arrow falling plug 1/socket falls off, the falling signal line is in a disconnected state; the change of the level of the shedding signal is collected by the satellite integrated electronic computer 3, and a control signal is output after corresponding operation and processing, so that the control task of the exhaust valve of the propulsion system is completed.
As shown in fig. 2, the rocket launching time is set to be T0, the drop plug drops at the rocket launching time T0-delta T1, after the satellite integrated electronic computer detects the change of the drop signal, an exhaust instruction is automatically sent at the rocket launching time T0+ delta T2 to drive the exhaust valve of the thruster to extrude gas, and the process continues to the time T0+ delta T3 to complete the pipeline exhaust task of the propulsion system.
The invention reduces the data interaction between the ground station and the satellite in the active section, reduces the influence of other actions in the active section on the pipeline exhaust, enhances the self-management capability of the satellite, and ensures that the satellite can smoothly complete the pipeline exhaust work of a propulsion system in the active section.
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 and 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.
Claims (2)
1. A satellite active section exhaust method controlled by satellite and rocket falling plug signals is characterized by comprising the following steps: the method adopts a main and standby redundant control circuit, and finishes the on-off task of a drop signal line through the working state change of a satellite and rocket drop plug/socket; after the satellite and rocket falling plug/socket falls off, the falling signal line is in a disconnected state; the change of the level of the shedding signal is collected by a satellite integrated electronic computer, and a control signal is output after corresponding operation and processing, so that the control task of the exhaust valve of the propulsion system is completed.
2. The method for exhausting the active section of the satellite controlled by the satellite and rocket dropping plug signal according to claim 1, wherein the on-off task is specifically represented by that before the satellite and rocket dropping plug/socket drops, a dropping signal line is in a conducting state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810684012.9A CN108928505B (en) | 2018-06-28 | 2018-06-28 | Satellite active section exhaust method controlled by satellite and rocket falling plug signal |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201810684012.9A CN108928505B (en) | 2018-06-28 | 2018-06-28 | Satellite active section exhaust method controlled by satellite and rocket falling plug signal |
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| Publication Number | Publication Date |
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| CN108928505A CN108928505A (en) | 2018-12-04 |
| CN108928505B true CN108928505B (en) | 2021-04-27 |
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| CN201810684012.9A Active CN108928505B (en) | 2018-06-28 | 2018-06-28 | Satellite active section exhaust method controlled by satellite and rocket falling plug signal |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113636111B (en) * | 2021-08-24 | 2023-08-18 | 上海卫星工程研究所 | Spacecraft electromechanical separation signal mixed use system, method and medium |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104390528A (en) * | 2014-09-17 | 2015-03-04 | 中国航天科技集团公司第四研究院第四十一研究所 | Rocket time sequence controller and control method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4428814B2 (en) * | 2000-05-18 | 2010-03-10 | Ｎｅｃエンジニアリング株式会社 | Ordnance control circuit |
| US8256203B1 (en) * | 2007-01-26 | 2012-09-04 | The University Of Alabama In Huntsville | Rocket based combined cycle propulsion unit having external rocket thrusters |
| CN201325678Y (en) * | 2008-12-20 | 2009-10-14 | 中国航天科技集团公司第五研究院第五一八研究所 | Entire satellite packing chest environment controller |
| CN101907041B (en) * | 2010-07-23 | 2013-04-03 | 北京航空航天大学 | Propane liquid gas micro propulsion device suitable for micro-nano satellite |
| CN102588740B (en) * | 2012-02-17 | 2013-11-27 | 北京航空航天大学 | High-pressure and high-purity nitrogen distribution device for plume test platform and application method for device |
| CN104358663B (en) * | 2014-09-19 | 2017-03-22 | 浙江大学 | Liquid ammonia propulsion system for pico-satellite or nano-satellite |
| CN105428862B (en) * | 2015-11-06 | 2018-11-09 | 杭州航天电子技术有限公司 | A kind of low magnetic umbilical connector for satellite |
| CN107792405A (en) * | 2017-09-25 | 2018-03-13 | 上海卫星工程研究所 | To the non-contact double super satellite platforms of principal and subordinate of day inertial orientation |
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104390528A (en) * | 2014-09-17 | 2015-03-04 | 中国航天科技集团公司第四研究院第四十一研究所 | Rocket time sequence controller and control method |
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| CN108928505A (en) | 2018-12-04 |
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