基于导引头-弹体耦合模型和伴随制导系统的火箭弹脱靶量快速估计方法

导引头初步方案设计阶段快速估计制导系统脱靶量是缩短火箭弹研制进度的有效方法。依据刚体运动学和动力学原理，建立俯仰-偏航双框架稳定平台式导引头的耦合数学模型，模型重点考虑了导引头与弹体的耦合作用，在此基础上进一步提出伴随化制导系统脱靶量评估方法。利用导引头耦合数学模型、实际飞行试验数据和简单的制导系统设计参数，快速对火箭弹脱靶量作出估计，在导引头初步方案设计阶段快速更新设计参数、减少迭代设计过程。仿真结果表明，导引头耦合模型具有较高的精确度，结合伴随化方法可以快速估计脱靶量、为导引头和制导系统初步设计提供依据。

Rapid Estimation Method for Miss Distance of Rocket Projectile Based on Coupled Seeker-Projectile Model and AdjointGuidance System

Rapidly estimating the miss distance of guidance system during the preliminary seeker design is an effective way to shorten rocket projectile development schedule. Based on the principles of rigid body kinematics and dynamics, the coupled mathematical model of a pitch-yaw two-frame stable platform seeker is constructed, which mainly considers the seeker-projectile coupling effect. Then, a rapid estimation method for the miss distance of guidance systems based on the adjoint theory is proposed. This method can quickly estimate the miss distance of a rocket projectile, and with the help of the coupled seeker model, real flight experimental data and simple guidance system parameters. the design parameters during the preliminary seeker development can be updated, thus reducing design iteration. The simulation results show that the coupled seeker model has high accuracy, and the miss distance can be rapidly estimated with the adjoint method, providing insights into the preliminary seeker and guidance system design.