Research on Thermal Response Characteristics of Space Nuclear Power in High-Temperature and High-Velocity Impact Experiment under Accidental Reentry

Zhou Xu; Hu Yupeng; Wang Yijun; Wan Kun; Deng Zhifang; Zhu Changchun; Hu Shaoquan

doi:10.13832/j.jnpe.2024.06.0047

Volume 45 Issue 6

Dec. 2024

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Zhou Xu, Hu Yupeng, Wang Yijun, Wan Kun, Deng Zhifang, Zhu Changchun, Hu Shaoquan. Research on Thermal Response Characteristics of Space Nuclear Power in High-Temperature and High-Velocity Impact Experiment under Accidental Reentry[J]. Nuclear Power Engineering, 2024, 45(6): 47-54. doi: 10.13832/j.jnpe.2024.06.0047

Citation:

Zhou Xu, Hu Yupeng, Wang Yijun, Wan Kun, Deng Zhifang, Zhu Changchun, Hu Shaoquan. Research on Thermal Response Characteristics of Space Nuclear Power in High-Temperature and High-Velocity Impact Experiment under Accidental Reentry[J]. Nuclear Power Engineering, 2024, 45(6): 47-54. doi: 10.13832/j.jnpe.2024.06.0047

Citation:

Zhou Xu, Hu Yupeng, Wang Yijun, Wan Kun, Deng Zhifang, Zhu Changchun, Hu Shaoquan. Research on Thermal Response Characteristics of Space Nuclear Power in High-Temperature and High-Velocity Impact Experiment under Accidental Reentry[J]. Nuclear Power Engineering, 2024, 45(6): 47-54. doi: 10.13832/j.jnpe.2024.06.0047

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Research on Thermal Response Characteristics of Space Nuclear Power in High-Temperature and High-Velocity Impact Experiment under Accidental Reentry

doi: 10.13832/j.jnpe.2024.06.0047

Institute of System Engineering, China Academy of Engineering Physics, Mianyang, Sichuan, 621999, China

Received Date: 2024-01-28
Rev Recd Date: 2024-07-26
Publish Date: 2024-12-17

Abstract

Abstract

High-temperature and high-velocity impact simulation test is a significant experiment to evaluate the safety of space nuclear power reactor in the accident impact on ground after accidental reentry. In this paper, a finite volume model coupling conduction, convection and radiation is established for the heat loading and high-velocity flight phase of the test, and the thermal response characteristics of the core simulator of the space nuclear reactor in the test are numerically studied, and the effects of loading temperature change rate and diameter-height ratio are analyzed. The results show that during the heat loading phase, the highest temperature and the lowest temperature of the core simulator are located at the junction of the side surface and the bottom surface and at the center of the simulator respectively. The time to reach thermal equilibrium is not only affected by the change rate of loading temperature, but also depends on the diameter-height ratio of the simulator. In the high-velocity flight phase, the highest and lowest temperatures of the core simulator are opposite to those in the heat loading phase, and the lowest temperature decreases with the increase of the diameter-height ratio and flight time. The research results can support the development and experimental design of high-temperature and high-velocity impact simulation test system.

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References(25)

References

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