Slender rockets experience significant elastic deformation during flight due to aeroelastic forces, impacting their dynamic behavior and posing challenges for traditional line-of-sight (LOS) angular rate estimation methods. This paper addresses this challenge by proposing a novel and highly accurate line-of-sight angular rate extraction model. This model integrates elastic identification with line-of-sight angular rate extraction, employing estimated generalized coordinates to calculate seeker elastic deformation. After elastic decoupling of the seeker, the slender rocket's line-of-sight angular rate can be estimated accurately. Additionally, the model incorporates a continuous-discrete maximum correntropy Kalman filter (CD-MCKF) to effectively handle the non-Gaussian measurement noise and limitations associated with discretizing the continuous model. Simulations demonstrate that the proposed method achieves significantly higher accuracy compared to existing approaches. The improved accuracy of this method can provide more precise calculations for the design of slender rocket guidance and control systems, ultimately improving the flight stability and control accuracy of rockets, and laying a solid foundation for the integrated guidance and control research of slender rockets.

中文翻译：

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细长火箭的集成弹性识别和视距角速率提取：连续离散最大熵卡尔曼滤波器方法

由于气动弹性力，细长火箭在飞行过程中会经历显着的弹性变形，影响其动态行为，并对传统的视线（LOS）角速率估计方法提出挑战。本文通过提出一种新颖且高精度的视线角速率提取模型来解决这一挑战。该模型将弹性识别与视距角速率提取相结合，利用估计的广义坐标来计算导引头的弹性变形。导引头弹性解耦后，可以准确估计细长火箭的视线角速率。此外，该模型还采用了连续离散最大熵卡尔曼滤波器 (CD-MCKF)，可有效处理非高斯测量噪声和与连续模型离散化相关的限制。仿真表明，与现有方法相比，所提出的方法具有更高的精度。该方法精度的提高可以为细长火箭制导控制系统的设计提供更精确的计算，最终提高火箭的飞行稳定性和控制精度，为细长火箭制导控制一体化研究奠定坚实的基础。