CN108804836B - Propelling pipeline thermal control design method suitable for Mars detection - Google Patents
Propelling pipeline thermal control design method suitable for Mars detection Download PDFInfo
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- CN108804836B CN108804836B CN201810615381.2A CN201810615381A CN108804836B CN 108804836 B CN108804836 B CN 108804836B CN 201810615381 A CN201810615381 A CN 201810615381A CN 108804836 B CN108804836 B CN 108804836B
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- 238000013461 design Methods 0.000 title claims abstract description 41
- 238000000034 method Methods 0.000 title claims abstract description 24
- 238000001514 detection method Methods 0.000 title claims abstract description 12
- 238000010438 heat treatment Methods 0.000 claims abstract description 30
- 239000000446 fuel Substances 0.000 claims abstract description 19
- 239000007800 oxidant agent Substances 0.000 claims abstract description 19
- 230000001590 oxidative effect Effects 0.000 claims abstract description 19
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 18
- 238000005286 illumination Methods 0.000 claims abstract description 11
- 238000005192 partition Methods 0.000 claims abstract description 6
- 239000000523 sample Substances 0.000 claims abstract description 4
- 239000007788 liquid Substances 0.000 claims description 4
- 230000008569 process Effects 0.000 abstract description 8
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000000638 solvent extraction Methods 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 241000282414 Homo sapiens Species 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
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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
Abstract
The invention provides a propulsion pipeline thermal control design method suitable for Mars detection, which is characterized in that heating belts of a fuel agent pipeline and an oxidant pipeline are separately designed and controlled according to different temperature control requirements of an oxidant and a fuel agent of a propulsion pipeline, pipelines with different pipe diameters are separately designed to meet the same temperature control requirement, the fuel agent pipeline and the oxidant pipeline inside and outside a cabin are separately designed and controlled according to different temperature environments inside and outside the cabin of a detector, the pipelines outside the cabin are designed in a partition mode according to the characteristics of illumination and non-illumination, and different threshold values are set. The invention solves the technical problems that the Mars probe is suitable for the complex pipeline layout temperature control requirement of the Mars probe and the complex and severe thermal environment experienced in the Mars process under the limited resources and the temperature of the propelling pipeline is controlled in a proper range, and has the advantages of accurate control and energy saving.
Description
Technical Field
The invention relates to the field of spacecraft thermal control, in particular to a propulsion pipeline thermal control design method suitable for Mars detection.
Background
With the development of aerospace technology, the breadth and depth of deep space exploration performed by human beings are continuously increased, and compared with a near-earth space spacecraft, a deep space detector is subjected to complicated and variable severe thermal environment tests in the operation process, and higher requirements are provided for the design of a thermal control subsystem, particularly for the adaptability of the thermal control design of a propulsion system pipeline.
Compared with the earth satellite, the propelling pipeline of the Mars detector has the characteristics of complexity and severe thermal environment: firstly, the detector flies to experience multiple orbital transfer and deep space maneuver in the mars process, and the temperature control requirement on the propulsion pipeline is high when the detector is orbital transfer and the deep space maneuver, and the high requirement is provided for the thermal control design of the propulsion pipeline. And secondly, the process that the detector flies to mars is subjected to complex and variable and severe thermal environment, a near field section is adapted to strong external heat flow, a near fire capturing section is adapted to low external heat flow, a fire surrounding section is adapted to important processes such as fire shadow entering and exiting, long-time fire shadow, attitude adjustment, rail lifting and rail lowering and the like, the external heat flow of the detector is complex in change, higher requirements are provided for the thermal control design of a propulsion pipeline of the detector, and the temperature control requirements of a propulsion system are required to be met under the condition of limited resources.
Therefore, the propulsion pipeline thermal control design method suitable for spark detection is provided aiming at the characteristic that the spark detector has high requirements on the propulsion pipeline thermal control design.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a propulsion pipeline thermal control design method suitable for Mars detection, solves the technical problems that a Mars detector is required to adapt to the complex pipeline layout temperature control requirement of the Mars detector under limited resources and the complex and severe thermal environment experienced in the Mars process, and is required to control the temperature of a propulsion pipeline within a proper range, and has the advantages of precise control and energy conservation.
The technical scheme adopted by the invention is as follows:
a propulsion pipeline thermal control design method suitable for Mars detection comprises the following steps: the method comprises the following steps:
based on different temperature control requirements of an oxidant and a fuel agent of a propulsion pipeline, thermal control heating zones of the propulsion fuel agent pipeline and the oxidant pipeline are respectively and independently designed and respectively controlled;
based on different temperature environments inside and outside the detector cabin, a fuel agent pipeline and an oxidant pipeline inside and outside the detector cabin are independently designed and controlled, and a heating zone of the pipeline outside the detector cabin is designed and controlled in a partitioning mode.
Furthermore, aiming at the independent design of an oxidant pipeline and a fuel agent pipeline, due to the fact that the pipelines of the propulsion system are different in pipe diameter, the heating power designs of different pipe diameters are different in order to guarantee the same temperature requirement, the heating power designs of the pipelines of the same pipe diameter are controlled in a coupling mode as much as possible in the principle of thermal control design of the pipelines of the same pipe diameter, the heating uniformity is guaranteed, and the heating zones of the pipelines of different pipe diameters are designed in a separated thermal mode.
Further, according to different illumination conditions of the detector on the track, the heating zone of the propelling liquid pipeline is divided into four areas of + Y and-Y and + Z and-Z for respectively controlling during thermal control design, and the propelling gas pipeline is divided into two areas of + X and-X for respectively controlling.
Further, in four areas of + Y-Y area and + Z-Z area, the-Z area belongs to an illumination area, the detector can be irradiated by sunlight when in orbit, the + Z area belongs to a non-illumination area, and the detector cannot be irradiated by the sunlight when in orbit.
Further, a heating zone threshold value of the propulsion pipeline thermal control design is set in a partition mode, and the partition threshold value is set as follows.
| Attitude of the probe | + Y region | -Y region | + Z zone | -Z region |
| + X days | (10℃,20℃) | (10℃,20℃) | (10℃,20℃) | (10℃,20℃) |
| + Z pairs of fire | (15℃,25℃) | (10℃,20℃) | (15℃,25℃) | (10℃,20℃) |
| -Z days of the day | (10℃,20℃) | (15℃,25℃) | (10℃,20℃) | (15℃,25℃) |
Aiming at the fact that the propelling pipeline thermal control design of the Mars detector needs to ensure the temperature control requirement of the complex pipeline layout under the limited resources and still needs to control the temperature of the propelling pipeline within a proper range under the complex and severe thermal environment experienced in the process of going to Mars, the propelling pipeline thermal control design method suitable for Mars detection provided by the invention has the following advantages:
(1) according to the thermal control design method of the propulsion pipeline, the heating zone is designed and controlled in a partitioning mode according to the thermal environment characteristics of the flight process of the detector, the heating zone is divided into an illumination area and a non-illumination area, different threshold values are designed, the threshold values are adjustable, the propulsion pipeline can adapt to different external thermal environments, and the detector control system can perform overall planning and accurate control conveniently;
(2) the propulsion pipeline thermal control design method separately designs heating belts of pipelines inside and outside the cabin according to the layout characteristics of the detector, separately designs and controls a fuel agent pipeline and an oxidant pipeline, achieves control according to requirements, can meet the propulsion temperature control requirements of the detector, and can save energy.
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 illustration of the split design of the fuel and oxidant lines of the present invention;
FIG. 2 is a schematic diagram of the separate design of the inboard and outboard piping of the present invention;
fig. 3 is a schematic view of the sectional design of the propelling liquid pipeline heating belt.
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.
The invention provides a propulsion pipeline thermal control design method suitable for Mars detection, which mainly comprises the following steps: the heating zones of the fuel agent pipeline and the oxidant pipeline of the propulsion system are separately designed and controlled, and the fuel agent pipeline and the oxidant pipeline outside the cabin are separately designed and controlled and are separately designed and controlled outside the cabin.
In this embodiment, the heating zones of the propellant fuel agent pipeline and the oxidant pipeline are separately designed, as shown in fig. 1, during the thermal control design, the heating zones with different powers are designed for the oxidant pipeline 1 and the fuel agent pipeline 2 outside the cabin, so as to achieve the purpose of independent control of the two. And the power is unanimous when the pipeline thermal control heating zone of same pipe diameter designs, ensures that the heating is even, and different pipelines need the separate thermal design. The fuel agent pipeline and the oxidant pipeline inside and outside the cabin are separately designed and controlled as shown in fig. 2, on one hand, during the thermal control design, the heating zone of the cabin pipeline 3 and the heating zone of the cabin pipeline 4 which are positioned in the satellite cabin body 5 are respectively designed, and different heating powers are set, so that the same temperature control requirement is met. On the other hand, in the thermal control design, the heating zone of the propelling liquid pipeline is divided into four areas of + Y and-Y and + Z and-Z for respectively controlling, as shown in fig. 3, the propelling gas pipeline is divided into two areas of + X and-X for respectively controlling, and a heating threshold value is set according to the temperature control requirement, so that the thermal control design of the propelling pipeline can meet the design requirement.
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 (4)
1. A propulsion pipeline thermal control design method suitable for Mars detection is characterized in that heating belts of a fuel agent pipeline and an oxidant pipeline are separately designed and controlled according to different temperature control requirements of an oxidant and a fuel agent of a propulsion pipeline, pipelines with different pipe diameters are separately designed to meet the same temperature control requirement, the fuel agent pipeline and the oxidant pipeline inside and outside a cabin are separately designed and controlled according to different temperature environments inside and outside the cabin of a detector, the pipelines outside the cabin are designed in a partition mode according to the characteristics of illumination and non-illumination, and different threshold values are set;
the fuel agent pipeline and the oxidant pipeline inside and outside the cabin are separately designed and controlled, a propelling liquid pipeline heating zone is divided into four areas of + Y area, a-Y area and + Z area and-Z area for respectively controlling during thermal control design, the propelling gas pipeline is divided into two areas of + X area and-X area for respectively controlling, the-Z area belongs to an illumination area, the detector can be irradiated by sunlight during on-track, the + Z area belongs to a non-illumination area, and the detector cannot be irradiated by sunlight during on-track;
the threshold value of a heating zone of the propulsion pipeline thermal control design is set in a partition mode, and the threshold value of the partition mode is set as follows:
。
2. A propulsion line thermal control design method suitable for Mars detection as claimed in claim 1, wherein the oxidant line and the fuel agent line heating zone are separately designed, the power of the same diameter of the line is designed to be the same, and the power of different diameters of the line is designed to be different.
3. The propelling pipeline thermal control design method suitable for Mars detection as claimed in claim 1, wherein the extravehicular pipeline is controlled in a partitioned mode, and the power design values of the heating zones in different regions are different.
4. The method as claimed in claim 1, wherein the control of the heating zone of the propulsion pipeline is controlled by a detector control system, and the threshold value of the heating zone of the propulsion pipeline is adjustable.
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| CN115367151B (en) * | 2022-10-20 | 2023-03-21 | 哈尔滨工大卫星技术有限公司 | Active thermal control device and method for spacecraft |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103792966A (en) * | 2014-01-27 | 2014-05-14 | 西安航天动力试验技术研究所 | Engine hot environment test propellant constant temperature supplying system |
| CN107719704A (en) * | 2017-09-22 | 2018-02-23 | 北京空间飞行器总体设计部 | A kind of spacecraft propulsion agent pipeline entirety thermal controls apparatus |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103792966A (en) * | 2014-01-27 | 2014-05-14 | 西安航天动力试验技术研究所 | Engine hot environment test propellant constant temperature supplying system |
| CN107719704A (en) * | 2017-09-22 | 2018-02-23 | 北京空间飞行器总体设计部 | A kind of spacecraft propulsion agent pipeline entirety thermal controls apparatus |
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