摘要
由于火箭的发动机存在推力偏心,火箭发射时火箭滑块会在发射装置导轨定向器凹槽内不断碰撞,这使得发射装置导轨产生一定的变形和挠度,影响火箭离轨射角精度。本文采取理论方法分析了火箭离轨时导轨的转角,确保了子午工程"鲲鹏1B"探空火箭的离轨扰动角满足要求,为其成功发射提供有力的理论支撑。
Because the rocket engine has thrust eccentricity,when the rocket is launching,the slider of the rocket will collide with the groove of the launcher,this causes the guide rail of the launcher to have certain deformation and deflection,influence on the accuracy of rocket's departure angle.In this paper,the theoretical method is used to analyze the angle of the guide rail when the rocket leaves the orbit,it ensures that the off orbit disturbance angle of the"Kunpeng 1b"sounding rocket of the Ziwu project meets the requirements,and provide strong theoretical support for successful launch of sounding rocket.
作者
张乐
曾志
肖登宝
ZHANG Le;ZENG Zhi;XIAO Deng-Bao(The 41st Institute of Fourth Academy of Aerospace Science And Technology Corporation,Xi'an Shaanxi710049,China;Beijing Key Laboratory of Lightweight Multi-functional Composite Materials and Structure Technology,Beijing Insititute of Technology,Beijing 100081,China;State Key Laboratory for Strength and Vibration of Mechancial Structures Xi'an Jiaotong University,Xi'an Shaanxi710049,China)
出处
《机电产品开发与创新》
2020年第3期63-65,共3页
Development & Innovation of Machinery & Electrical Products
基金
国家自然科学基金(11802031)
西安交通大学机械机构强度与振动国家重点实验室开放基金(SV2020-KF-11资助)。
关键词
探空火箭
发射装置
离轨扰动
理论计算
sounding rocket
launcher
derailment disturbance
theoretical calculation.
