基于姿态火箭的弹射座椅轨迹控制技术研究OA
Ejection Seat Trajectory Amendment Based on Attitude Rocket
对基于常规姿态火箭进行横滚姿态控制的弹射座椅基本方案进行了阐述，通过仿真计算对不同弹射速度、横滚角度、火箭包延迟点火时间下姿态火箭冲量对人椅相对轨迹高度的影响进行了研究。研究结果表明常规姿态火箭配合火箭包延时点火对提高弹射座椅在不利姿态下弹射时的性能具有显著的效果。
This paper presents a general concept of ejection seat capable of roll control by the normal attitude rocket . Through simulation computation ,the effects of attitude rocket impulse on man‐seat trajectory have been studied at varied e‐jection speeds ,roll angles ,and delayed firing of rocket motor .Results have shown that normal attitude rocked ,coupled by delayed firing of rocket motor ,is significant to seat performances during adverse ejection .
吴晓君;冯光辉;张岩
海军驻襄樊地区航空军事代表室 襄阳 441003航宇救生装备有限公司 襄阳 441003海军驻襄樊地区航空军事代表室 襄阳 441003
航空航天
弹射座椅姿态火箭轨迹控制
ejection seatattitude rocketeuler parameterstrajectory adjustment
《舰船电子工程》 2015 (11)
133-136,4
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