[an error occurred while processing this directive]
���¿��ټ��� �߼�����
   ��ҳ  �ڿ�����  ��ί��  Ͷ��ָ��  �ڿ�����  ��������  �� �� ��  ��ϵ����
�������պ����ѧѧ�� 2006, Vol. 32 Issue (01) :40-45    DOI:
���� ����Ŀ¼ | ����Ŀ¼ | ������� | �߼����� << | >>
֣�1, ͯ����1, �̹��1, ����2*
1. �������պ����ѧ �ѧԺ, ���� 100083;
2. �������ն����о���, ���� 100076
Simulation and optimization of liquid propellants rocket engine for system design
Zheng Yuntao1, Tong Xiaoyan1, Cai Guobiao1, Chen Jun2*
1. School of Astronautics, Beijing University of Aeronautics and Astronautics�� Beijing 100083, China;
2. China Aerospace Science and Technology Corporation Eleventh Inst., Beijing 100076, China

Download: PDF (0KB)   HTML 1KB   Export: BibTeX or EndNote (RIS)      Supporting Info
ժҪ ������ijҺ����������ϵͳ��Ƶķ���ģ������Ӧ�Ķ�Ŀ���Ż�ģ��,������ϵͳ�������,����iSIGHT�����ƽ̨����Բ�ͬ���Ż�Ŀ��Է���������Ʋ��������Ż�.����������Ż�����,��϶ൺ�Ŵ��㷨�����ж��ι滮�㷨�ֱ����ȫ��Ѱ�ź;ֲ�Ѱ��,���ȫ�����ŵ�.�����˵�ȼ��������ѭ��ϵͳ������ģ��,���Ż������п����˷�������Ҫ�����ṹ������ϵͳ���ܵ�Ӱ�졣��ȼ����ѹǿ����ϱȺ���ܳ��ڷ�ѹΪ��Ʊ���,�Ż�Ŀ������������ȳ塢��Ч�غɡ��ṹ�������ܶȱȳ塢�ػ�ʱ�����ٶȡ��ƽ����ۺ��ܶ�.�����ݽ��������ȼ����ѹǿ�ͻ�ϱȶԷ��������ܵ�Ӱ��.
Email Alert
�ؼ����� �Ż�   ϵͳ����   ���   ���������   Һ���ƽ���     
Abstract�� The system simulation model and the relevant multi-objective optimization model were established for a type of liquid propellants rocket engine. A system simulation procedure was programmed. Design parameters of system were optimized owing to different optimization objectives on iSIGHT software platform. A type of hybrid algorithm, which combined the multi-island genetic algorithm and the sequential quadratic programming algorithm, was used to find global optimum in given design space during the optimization procedure. Weight model of single gas generator cycle system was established. Main components weights were concerned in optimization because of their influence on system performance. The optimization design variables were the combustor pressure, mixture ratio, and the outlet pressure of pipe. The optimization objectives were engine specific impulse, payload, engine weight, engine density specific impulse, flight speed at shutting down and engine compositive density. The effects of combustion chamber pressure and mixture ratio on engine performance were analyzed based on simulation.
Keywords�� optimization   systems analysis   design   rocket engines   liquid propellants     
Received 2004-10-27;


About author: ֣���(1979-),Ů,�����差��,��ʿ��, ehuamei@sina.com.
֣�, ͯ����, �̹��, ����.Һ����������ϵͳ��Ʒ������Ż�[J]  �������պ����ѧѧ��, 2006,V32(01): 40-45
Zheng Yuntao, Tong Xiaoyan, Cai Guobiao, Chen Jun.Simulation and optimization of liquid propellants rocket engine for system design[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2006,V32(01): 40-45
http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2006/V32/I01/40
Copyright 2010 by �������պ����ѧѧ��