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Swerving Orientation of Spin-Stabilized Projectile for Fixed-Cant Canard Control Input

机译:自旋稳定弹丸对固定式Canard控制输入的倾斜方向

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摘要

Due to the large launch overload and high spin rate of spin-stabilized projectile, no attitude sensor is adopted in square crossing fixed-cant canard concept, which causes the lack of existing projectile linear theory for the close form solution of swerving motion. This work focuses on swerving orientation prediction with the restricted conditions. By importing the mathematical models of canard force and moment into the projectile angular motion equations, trim angle induced by canard control force is extracted as the analytical solution of angle of attack increment (AOAI). On this basis, analytical orientations of trajectory angular rate increment and swerving increment are obtained via the frozen coefficient method. A series of simulations under different conditions were implemented to validate the expressions in this effort. Results state that increment orientation of swerving motion can be predicted with available trajectory parameters. The analytical orientations indicate trim value of numerical orientations. Deviations between analytical and numerical orientations relate to initial launch angles and control start time, both lower initial launch angle, and the start time which is closer to the end of flight decreases the deviation convergence time.
机译:由于发射超载大且自旋稳定弹丸的自旋速率高,因此在方形交叉固定斜面鸭式飞机概念中未采用姿态传感器,这导致缺乏用于倾斜运动的近似形式解的现有射弹线性理论。这项工作着重于在受限条件下的转弯方向预测。通过将炮弹力和力矩的数学模型输入到弹丸角运动方程中,提取由炮弹控制力引起的微调角作为迎角增量(AOAI)的解析解。在此基础上,通过冻结系数法获得了轨迹角速率增量和转弯增量的解析方向。在不同条件下进行了一系列模拟,以验证此工作中的表达式。结果表明,可以使用可用的轨迹参数来预测转弯运动的增量方向。分析取向表示数字取向的修整值。分析方向和数字方向之间的偏差与初始发射角和控制启动时间有关,两者都较低的初始发射角,并且更接近飞行结束的启动时间减少了偏差收敛时间。

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  • 来源
    《Mathematical Problems in Engineering》 |2015年第4期|173571.1-173571.11|共11页
  • 作者单位

    Beijing Inst Technol, Sch Mechatron Engn, Beijing 10081, Peoples R China.;

    Beijing Inst Technol, Sch Mechatron Engn, Beijing 10081, Peoples R China.;

    Beijing Inst Technol, Sch Mechatron Engn, Beijing 10081, Peoples R China.;

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