摘要
较系统地总结了导弹气动特性和气动载荷计算方面的理论和经验算法,根据细长体理论干扰因子法结果得出了导弹部件升力的计算公式,编写了可用于估算导弹气动特性和气动载荷的软件。通过算例证明,软件的计算结果能够满足初步设计阶段的精度要求。最后用该软件对某在研型号导弹进行气动特性和载荷的计算,给出了计算结果。
Theories and experiences about the calculation of missile aerocharacteristics and aerodynamic load are summarized. According to theory of method, lift formulas of components are obtained. A program about missile aerocharacteristcs and aerodynamic load calculation is developed. Acomputing example shows that the program's result is enough to pre-designing. Finally, the program is used to a target missile, corresponding reslut is listed.
出处
《弹箭与制导学报》
CSCD
北大核心
2004年第2期62-63,77,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
导弹
气动特性
气动载荷
精度
target missile
aerocharacteristcs
aerodynamic load
