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�������պ����ѧѧ�� 2009, Vol. 35 Issue (3) :308-312    DOI:
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1. �������պ����ѧ ���տ�ѧ�빤��ѧԺ, ���� 100191;
2. �ɶ��ɻ�����о���, �ɶ� 610041
Calculation of thermal load and impact factor analysis for hypersonic vehicle
Zhang Lizhen1, Wang Xiaoming1, Dong Sujun2, Wang Jun1*
1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. Chengdu Aircraft Design & Research Institute, Chengdu 610041, China

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Abstract�� Endothermal thermal protection system (TPS) and liquid N2 heat sink were chosen to calculate the characteristics of thermal control system (TCS) in hypersonic vehicle. The methods of radiation balance and double lumped parameter were adopted to obtain the thermodynamic model of adiabatic layer and cabin air temperature. Therefore, aeroheating, adiabatic layer heat transfer and cabin air temperature were decoupled. On the basis of flight profile of X-34 hypersonic vehicle, the thermal load of avionics bay was calculated. Besides, the influence of adiabatic layer, cooling gas velocity and liquid N2 amount on cabin air as well as the equipment temperature were analyzed. The results show that this method could get the response characteristics of heat transfer sections, which played an important part in the primary stage of hypersonic vehicle design.
Keywords�� hypersonic flow   vehicle   thermal control system   thermal protection system   thermal load     
Received 2008-03-19;
Fund:

���տ�ѧ����������Ŀ(2006ZC5135)

About author: ������(1981-),Ů,���Ͽ�����,��ʿ��,zhanglz0914@163.com.
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������, ������,���ؾ�, �� ��.�߳����ٷ��������غɼ��㼰Ӱ�����ط���[J]  �������պ����ѧѧ��, 2009,V35(3): 308-312
Zhang Lizhen, Wang Xiaoming,Dong Sujun, Wang Jun.Calculation of thermal load and impact factor analysis for hypersonic vehicle[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2009,V35(3): 308-312
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