THE NUMERICAL METHOD OF AERODYNAMIC COEFFICIENTS AND TRAJECTORY FOR A PROJECTILE FLYING THROUGH A VERY EXTENSIVE ALTITUDE
To simulate trajectory of a projectile, the prediction of aerodynamic coefficients is a fundamental work. During simulation of trajectory, it should be done rigorously at every iterative point on trajectory that the aerodynamic forces and moments are predicted firstly with the flight state and parameters of free-stream air at this point. Since the process above is complicated and the iterative points are huge, it is seldom used in practice. Usually the trajectory is simulated by interpolating the aerodynamic coefficients predicted in advance with a certain condition. If the projectile flies stably and the flight altitude is limited, this error is acceptable. At present the whole trajectories of some projectiles or rockets will pass through the extensive altitude or range which will increase the error of the conventional method. Therefore, a new numerical method of aerodynamic coefficients and trajectory has been investigated in this paper, which is expected to improve the accuracy of flight simulation.
WANG Zhong-yuan ZHANG Bi-sheng LINXian-wu CHANG Si-jiang
Ballistic Research Laboratory of China, Nanjing University of Science & Technology, P. O. Box 210094 Naval Academy of Armament, Beijing, China
国际会议
25th International Symposium on Ballistics(第25届国际弹道会议)
北京
英文
254-261
2010-05-17（万方平台首次上网日期，不代表论文的发表时间）