火箭推进2018，Vol.44Issue(6)：21-28,8.
新型空间双模式核热推进系统热力学性能研究
Research on thermodynamic performance of a new aerospace nuclear thermal propulsion system
摘要
Abstract
In this paper, a new aerospace nuclear thermal propulsion system scheme is proposed on the basis of re-expand regenerative Brayton cycle. The system performance in power generation mode was simulated and analyzed while helium was used as the working medium. The influence of cycle temperature ratio, pressure ratio and reexpansion distribution coefficient of turbine on the power generation cycle performance were achieved. The results indicate that, with the same design parameters, the efficiency of this cycle is higher than that of regenerative cycle based on Brayton, but its radiator area is less than regenerative cycle based on Brayton. Cycle efficiency increases with the increase of cycle temperature ratio, but decreases with the increase of pressure ratio. The cycle efficiency reached the maximum value while pressure ratio distribution coefficient of turbine is at about 0. 83 and 1. 05 under the conditions of cycle pressure ratio at 3 and 6. With the increase of the cycle pressure ratio, the distribution coefficient corresponding to maximum value of the cycle output power moves to right from left extreme value. This cycle, when used as scheme for power generation mode of space nuclear thermalpropulsion, can effectively reduce the size and weight of the spacecraft.关键词
核热推进系统/双模式/热力学性能/空间推进Key words
nuclear thermal propulsion system/dual mode/thermodynamic performance/space propulsion分类
航空航天引用本文复制引用
李强,李家文,王戈,屈兀波..新型空间双模式核热推进系统热力学性能研究[J].火箭推进,2018,44(6):21-28,8.基金项目
载人航天第三批预先研究项目(1664050201) （1664050201）
