【摘要】 针对未来载人火星探测、大型星际货物运输等的空间动力问题,开展核热推进技术系统循环方案展开对比分析。根据文献调研结果,确定了热抽气循环、冷抽气循环和膨胀循环等3种核热火箭发动机系统循环备选方案,根据自编核热火箭发动机参数平衡计算软件,针对10 t推力的核热火箭发动机应用背景,对上述3种方案进行系统参数平衡计算,得到各方案详细的热平衡工作参数;根据计算结果对3种方案进行对比分析,在相同初始设计条件下,膨胀循环方案推力和比冲均最高,性能最优越,可以作为今后核热火箭发动机系统的首选方案。更多还原

【Abstract】 Targeting the space propulsion issue in future human Mars missions or large scale interstellar cargo transportation, the cycle schemes of nuclear thermal rocket engine(NTRE) were compared and analyzed. According to the literature investigation, three alternative schemes of the system circulation of the nuclear thermal rocket engine including the hot bleeding cycle, the cold bleeding cycle and the expander cycle were determined. Based on the self-written NTRE simulation software, system simulation was conducted for the three cycle schemes of 100 kN thrust. The detailed thermal balance operating parameters of each cycle were obtained. The results showed that with the same initial design condition, the expansion cycle scheme had the highest thrust and specific impulse and the best performance. It can be used as the preferred scheme for the nuclear thermal rocket engine system in the future.更多还原