摘要
在合理简化基础上,推导了滑块运动与飞行器姿态角运动之间的关系,分析了配平攻角产生机理及条件;同时还深入分析了轴向位置、横向偏移量、质量比等滑块结构参数对配平攻角的影响;以及不同配平条件下弹道落点偏差情况。结果表明,气动阻力与系统质心偏移弹体纵轴是产生配平攻角两个必要因素,系统静稳定是产生配平攻角的前提条件;轴向位置决定了系统静稳定裕度,与配平攻角呈反比关系;横向偏移量改变控制力矩的力臂,与配平攻角呈正比关系;质量比对力臂和系统静稳定裕度均有影响,与配平攻角呈线性或非线性正比关系;变质心控制能力主要体现在低空段。
The relationship between slide＇s motion and vehicle attitude angles are derived by linearized nonlinear equations rationally.The generation mechanism and existence condition of trim angle of attack（AOA） is analysed in detail.Meanwhile,the mass parameters including axial position,lateral displacement,and mass ratio,closely related to the trim AOA are discussed in deeply,and the impact-point deviations in different trim conditions are investigated.Results show that the aerodynamic drag and the offset of mass center of system from vehicle＇s axis line are two necessary elements to produce trim AOA.While keep the system＇s stability is the prerequisite to produce the trim AOA.The axial position determines the system＇s stability and the lateral displacement changes the control torque＇s arm,while the mass ratio has influence on both.The trim AOA is directly proportional to lateral displacement and inversely proportional to axial position and mass ratio.The varying mass center control ability is mainly reflected in low alttitude.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2010年第9期2165-2171,共7页
Journal of Astronautics
基金
国家自然科学基金(10902026)
中国博士后基金(20080440436)
高等学校博士学科点专项科研基金(200802131077)
关键词
变质心控制
空间飞行器
控制性能
配平攻角
Moving mass control
Aerospace vehicle
Control performance
Trim angle of attack
