CAJ | 학술논문

针对某型空地导弹机动性分析时气动参数的非线性特性，提出采用逐步逼近最终达到力矩平衡求解最大平衡攻角及可用法向过载的方法，解决了具有非线性气动特性导弹的可用法向过载计算问题，通过弹道仿真，对需用法向过载和可用法向过载进行了计算和对比．计算结果表明该导弹具有足够的机动能力，为总体设计和控制系统设计提供了依据．
침대모형공지도탄궤동성분석시기동삼수적비선성특성，제출채용축보핍근최종체도력구평형구해최대평형공각급가용법향과재적방법，해결료구유비선성기동특성도탄적가용법향과재계산문제，통과탄도방진，대수용법향과재화가용법향과재진행료계산화대비．계산결과표명해도탄구유족구적궤동능력，위총체설계화공제계통설계제공료의거．
To address the nonlinear characteristic of aerodynamic parameter when mobility of a certain air- to -ground missile fitted to helicopter is analyzed, this study puts forward the method of stepwise approximation which approaches moment balance to attain the maximum balance attack angle and useable normal overload. The problem of useable normal overload concerning missiles＇ nonlinear aerodynamic characteristic is solved. Useable normal overload and necessary normal overload are calculated and compared by means of trajectory simulation. The results testify that missiles＇ mobility is sufficient, which will provide theoretical fundamentals and practical results for its further conceptual and control system design.