Research on the thermal design of the propulsion pipeline on the Tianwen-1 Mars Orbiter
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摘要:针对火星探测器空间环境特点和热控设计难点，提出了一种适用于火星环绕器的推进管路热控设计方法，通过采用优化的加热功率、合适的多层层数和适宜的加热器分区实现地火空间复杂外热流下的管路控温。将该方法在“天问一号”火星环绕器推进管路设计中进行分析与验证，对影响热控设计的因素如舱内外环境温度变化、管路是否有工质、是否受太阳照射、包覆多层层数以及加热功率等进行了分析。研究表明，该方法具有高度环境适应性，在环绕器飞行全过程及变轨条件下均能适应。未来需重点关注管路加热功率的设计和舱外多层包覆层数的影响，舱外管路受阳光照射影响大，设计时应尽量避免阳光照射。以上研究结果可为后续深空探测推进管路热控设计提供一定的参考。Abstract:The article proposed a method which can solve the problem of the thermal design of the pipe that was suitable for the Characteristics of space environment of the Mars Probe. By adopting optimized heating power, suitable number of layers and suitable heater zone to realized the control of the pipeline under the complex external heat flow. Taking “Tianwen-1”Mars Orbiter as an example, the scheme was analyzed and verified by the on-orbit data. It also analyzed the influencing factors such as the changes of the ambient temperature, whether the propulsion pipeline had working fluid, whether it was exposed to the sun, the number of the coating layers and the heating power. Researches showed that it was suitable for all environments during the flight and track adjustment of the MARS Orbiter. It is impotent to focus on the number of the coating layers and the heating power in the future. It has great impact on the pipeline when it is exposed to the sun. The above research is applied to the thermal design of the Mars exploration in the future.
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Key words:
- Mars/
- propulsion pipeline/
- thermal control/
- influcing factor
Highlights● The thermal control method for the propulsion pipeline of the Mars Orbiter is proposed. ● The analysis shows that solar radiation has a great influence on the external pipeline. ● The number of layers has great influence on the external pipeline. -
图 2探测器舱内管路热控包覆状态与舱外管路热控包覆状态
Fig. 2The thermal control multilayer coating state of the detector in the cabin and out of the cabin
图 4探测器管路试验温度与在轨温度比较
Fig. 4The comparison of the test and on-orbit temperature of the pipe
图 7舱外管路热控包覆10层与舱外管路热控包覆20层
Fig. 7The thermal control multilayer coating state of the detector in the cabin and out of the cabin
图 8不同多层层数温度比较
Fig. 8The comparison of the temperature under different number of layers
图 9起飞过程管路温度曲线
Fig. 9The temperature curve of the pipe in the process of the rocket take off
表 1推进管路温度统计
Table 1The temperature of the pipe
推进管路测点 指标/℃ 指标/℃ 温度/℃ 温度/℃ 指标 名称 下限 上限 下限 上限 符合性 负X氧管壁温度2 –5 60 21.2 34.3 符合 正Z氧管壁温度1 –5 60 21.9 28.9 符合 正Z氧管壁温度2 –5 60 15.0 20.4 符合 负Z氧管壁温度1 –5 60 15.7 21.2 符合 负Z氧管壁温度2 –5 60 9.9 15.7 符合 负X燃管壁温度1 –5 60 3.8 13.7 符合 负X燃管壁温度2 –5 60 5.0 10.6 符合 正Z燃管壁温度1 –5 60 12.5 23.3 符合 正Z燃管壁温度2 –5 60 35.3 40.6 符合 负Z燃管壁温度1 –5 60 17.0 21.9 符合 负Z燃管壁温度2 –5 60 13.7 17.7 符合 氧化电动气阀测温 –5 60 13.7 18.4 符合 燃料电动气阀测温 –5 60 15.0 21.9 符合 负Z燃管壁温度3 –5 60 2.5 5.5 符合 正Z氧管壁温度3 –5 60 31.8 40.1 符合 正Z燃管壁温度3 –5 60 9.3 19.0 符合 负X氧管壁温度3 –5 60 0.5 3.2 符合 负X氧管壁温度4 –5 60 19.0 23.3 符合 负X燃管壁温度3 –5 60 0.7 5.0 符合 负X燃管壁温度4 –5 60 17.0 20.4 符合 自锁阀LVg9温度 –5 60 17.0 19.7 符合 自锁阀LVg10温度 –5 60 17.7 19.7 符合 加排MLVg4温度 –5 60 24.1 28.9 符合 加排MLVg3温度 –5 60 23.3 27.2 符合 单向DVg1温度 –5 60 8.1 9.3 符合 单向DVg2温度 –5 60 7.5 8.7 符合 加排MLVg5外壁温度 –5 60 23.3 25.6 符合 
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表 2推进管路加热器占空比统计
Table 2The power ratio of the heater on the pipe
飞行
时间管路加
热器1管路加
热器2管路加
热器3管路加
热器4管路加
热器5管路加
热器62020.07.25 0.75 0.59 0.50 0.66 0.53 0.67 2020.08.15 0.90 0.75 0.50 0.79 0.42 0.71 2020.09.01 0.81 0.71 0.52 0.73 0.48 0.68 2020.09.15 0.87 0.73 0.52 0.74 0.55 0.82 占空比
增量0.12 0.14 0.02 0.08 0.02 0.15 下载:
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表 3推进管路测温2的温度变化
Table 3The temperature of the point 2# on the pipe
项目 时间 温度/℃ 升温
速率/（℃·h–1）推进管路2
测温2020.07.30.09:00 19.1 — 2020.07.30.16:00 35.3 2.3 2020.07.31.03:30 47.1 1.0 下载:
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表 4不同管径特性比较
Table 4The characteristic of different pipe diameters
项目 管径Φ6 管径Φ8 管径Φ14 管路加热功率/（W·m–1） 1.00 1.00 1.80 起飞过程升温速率/（℃·min–1） 0.33 0.25 –0.18 加热器占空比 0.45 0.25 0.18 下载:
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