|Table of Contents|

Research on thermodynamic performance of a new aerospace nuclear thermal propulsion system(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2018年06期
Page:
21-28
Research Field:
研究与设计
Publishing date:

Info

Title:
Research on thermodynamic performance of a new aerospace nuclear thermal propulsion system
Author(s):
LI Qiang1;  LI Jiawen1;  WANG Ge2;  QU Wubo1
1.School of Astronautics, Beihang University, Beijing 100191, China; 2.Beijing Institute of Control Engineering, Beijing 100191, China
Keywords:
nuclear thermal propulsion system;  dual mode;  thermodynamic performance;  space propulsion
PACS:
V439+.5-34
DOI:
-
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 thermal propulsion,can effectively reduce the size and weight of the spacecraft.

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Last Update: 2018-12-25