临近空间飞行器相变吸热式充排气装置的设计及其性能仿真

赵中元; 李明佳; 李冬; 陈宇

doi:10.7652/xjtuxb202211012

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临近空间飞行器相变吸热式充排气装置的设计及其性能仿真

—————————————————————— | 更新时间：2025-07-09

- 临近空间飞行器相变吸热式充排气装置的设计及其性能仿真
- Design and Performance Simulation of the Pressure Control Device with the Phase Change Material for Near Space Vehicles
- 西安交通大学学报 2022年56卷第11期页码：115-125
- 作者机构：
  
  西安交通大学热流科学与工程教育部重点实验室,西安,710049
- 作者简介：
  
  : 2022-03-28。作者简介: 赵中元(1996—),男,硕士生
  李明佳(通信作者),女,教授,博士生导师。基金项目: 国家自然科学基金创新群体资助项目(51721004)
- 基金信息：
  
  : 2022-03-28。作者简介: 赵中元(1996—),男,硕士生;李明佳(通信作者),女,教授,博士生导师。基金项目: 国家自然科学基金创新群体资助项目(51721004);国家科技重大专项资助项目(J2019-III-0021-0065)
- DOI：10.7652/xjtuxb202211012
  中图分类号： V245.4
- 网络首发：2022-11-10，
  
  纸质出版：2022
- 稿件说明：
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赵中元, 李明佳, 李冬, 等. 临近空间飞行器相变吸热式充排气装置的设计及其性能仿真[J]. 西安交通大学学报, 2022,56(11):115-125.

ZHAO Zhongyuan, LI Mingjia, LI Dong, et al. Design and Performance Simulation of the Pressure Control Device with the Phase Change Material for Near Space Vehicles[J]. 2022, 56(11): 115-125.
赵中元, 李明佳, 李冬, 等. 临近空间飞行器相变吸热式充排气装置的设计及其性能仿真[J]. 西安交通大学学报, 2022,56(11):115-125. DOI： 10.7652/xjtuxb202211012.

ZHAO Zhongyuan, LI Mingjia, LI Dong, et al. Design and Performance Simulation of the Pressure Control Device with the Phase Change Material for Near Space Vehicles[J]. 2022, 56(11): 115-125. DOI： 10.7652/xjtuxb202211012.

摘要

为解决临近空间飞行器的常规被动充排气孔存在的外部高温气体回流致使舱内仪器高温失效的问题

本文创新性地提出了一种用于临近空间飞行器被动充排气系统的相变吸热式充排气装置。该装置增设相变吸热填充区域

在有效平衡飞行器舱内外压差的同时

降低回流气体温度以保障飞行器安全。通过数值仿真对该相变吸热式充排气装置进行了性能分析和结构优化

并将优化后的充排气装置应用于某临近空间飞行器快速上升、机动飞行和快速下降的完整飞行过程中。仿真结果表明:优化后的相变吸热式充排气装置的相变材料填充质量减少了约45%

装置体积缩小了约10%; 优化后的充排气装置能将飞行器内外压差维持在50 Pa以下

同时将回流气体温度降到340 K以下。该相变吸热式充排气装置具有良好的泄压与降温双重性能

在航空航天领域具有较好的应用前景。

Abstract

The venting holes of the conventional passive pressure control system of near space vehicles may cause the high temperature gas outside to flow back into the cabin

thus disabling the instruments inside the cabin. To solve this problem

a pressure control device filled with phase change materials is proposed in this paper. This device can balance the pressure difference inside and outside the cabin

and ensure vehicle safety by cooling the high-temperature backflow. The device performance is analyzed and structure optimized through numerical simulation. The optimized device is then used during rapid ascent

maneuvering flight and rapid descent of a near space vehicle. Numerical simulation results show that the mass of the phase change material and the volume of the optimized device are reduced by about 45% and 10% respectively. Moreover

the pressure difference inside and outside the cabin is maintained below 50 Pa and the backflow temperature is reduced to 340 K after the optimized pressure control device is used on the near space vehicle. Therefore

the proposed pressure control device can both control the pressure and lower the temperature

promising good application prospects in the field of aerospace.

关键词

Keywords

references

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