小型子弹抛撒后的飞行力学特性影响研究
|
摘要
利用子弹尾翼展开过程风洞试验气动特性和尾翼在驱动力作用下在不同张开位置对应时间的测量结果,分析研究子弹抛撒引起的初始角速率对飞行攻角的影响;根据子弹飞行过程中最大攻角限制,确定子弹抛撒初始角速率控制范围。子弹抛撒初始角速率要求可进一步放宽,研究结果对子母弹药子弹抛撒设计中姿态调整具有现实意义。
Based on the aerodynamic characteristics of submunition which tested in wind tunnel during its empennage expansion process, and the measured time of different expansion position caused by the drive force, the impact of initial angular velocity derived from submunition's ejection on angle of attack is analyzed. Thus with the limitation of angle of attack during flight, that of submunition's initial angular velocity can also be settled. The expanding time of submunition's empennages in the limit velocity targeting test is analyzed, it shows that the requirement of initial angular velocity of submunition's ejection could be further relaxed. The results are of vital importance for attitude adjustment of the submunition ejection design.
Based on the aerodynamic characteristics of submunition which tested in wind tunnel during its empennage expansion process, and the measured time of different expansion position caused by the drive force, the impact of initial angular velocity derived from submunition's ejection on angle of attack is analyzed. Thus with the limitation of angle of attack during flight, that of submunition's initial angular velocity can also be settled. The expanding time of submunition's empennages in the limit velocity targeting test is analyzed, it shows that the requirement of initial angular velocity of submunition's ejection could be further relaxed. The results are of vital importance for attitude adjustment of the submunition ejection design.
引文
[1]王国雄.弹头技术[M].北京:宇航出版社,1993.
[2]徐延万.控制系统[M].北京:宇航出版社,1989.
[3]杨军,杨晨,段朝阳,贾晓洪.现代导弹制导控制系统设计[M].北京:航空工业出版社,2005.
[4]杨启仁.子母弹飞行动力学[M].北京:国防工业出版社,1999.
[5]刘赛,庞桂凤,郭珂,等.子母弹抛撒参数优化与抛撒/盲区半径误差分析[J].导弹与航天运载技术,2014(6):42-45.
[6]钱杏芳,林瑞雄,赵亚男.导弹飞行力学[M].北京:北京理工大学出版社,2011.
[7]赵汉元.飞行器再入动力学和制导[M].长沙:国防科技大学出版社,1997.
[8]贾沛然,陈克俊,何力.远程火箭弹道学[M].长沙:国防科技大学出版社,1993.
[2]徐延万.控制系统[M].北京:宇航出版社,1989.
[3]杨军,杨晨,段朝阳,贾晓洪.现代导弹制导控制系统设计[M].北京:航空工业出版社,2005.
[4]杨启仁.子母弹飞行动力学[M].北京:国防工业出版社,1999.
[5]刘赛,庞桂凤,郭珂,等.子母弹抛撒参数优化与抛撒/盲区半径误差分析[J].导弹与航天运载技术,2014(6):42-45.
[6]钱杏芳,林瑞雄,赵亚男.导弹飞行力学[M].北京:北京理工大学出版社,2011.
[7]赵汉元.飞行器再入动力学和制导[M].长沙:国防科技大学出版社,1997.
[8]贾沛然,陈克俊,何力.远程火箭弹道学[M].长沙:国防科技大学出版社,1993.