摘要
考虑基于无控方案实现火箭靶弹平飞弹道存在诸多不利因素,提出了一种通过在原型弹上加装鸭舵和简易控制装置实现火箭靶弹平飞弹道的设计思路,并对总体方案进行了阐述。最后根据气动特性数据和弹体结构数据,仿真计算了靶弹在不同条件下的飞行弹道,并结合计算结果对供靶方案进行了分析。仿真结果表明:通过选择不同的发射角和控制舵偏角程序,能够使靶弹获得相对平直的飞行弹道。
Considering the more defects exist in the no controlled scheme for achieving horizontal flight, a design idea about achieving the horizontal flight by assembling canard control vane and simple control sys- tem on the prototype rocket projectile is put forward, and the system concept is described. In the end, according to the aerodynamic characteristic data and missile structure data, the flight trajectory under the different condition are analyzed by using simulation calculations, and combining with the results, the con- cept of supplying target are analyzed. The result of trajectory simulation indicates that a more straight smooth flight trajectory could be gained by choosing the different launch angle and the control program of rudder deflection angle.
出处
《战术导弹技术》
2014年第1期37-41,共5页
Tactical Missile Technology
关键词
超声速
火箭靶弹
控制系统
平飞弹道
supersonic speed
rocket target
control system
horizontal flight trajectory
