隔转鸭舵式弹道修正弹双旋通道参数辨识

Parameter Estimation of Axial Dual-spin System in a Trajectory Correction Projectile with Decoupled Canards

双旋弹概念为旋转稳定榴弹的智能化改造提供了新思路,解耦后前后级之间通过执行机构进行控制。为实现对控制内回路的高效设计和分析,建立双旋通道的动力学模型。该模型以准静态气动力和改进形式的Lu Gre摩擦之间的匹配关系预测鸭舵的运动。通过瞬态数值计算和动态风洞试验获取气动力和摩擦的时域数据,利用最小二乘方法对模型的参数进行估计。研究结果表明:鸭舵的侧向力和滚转力矩分别受到相位角和滚转速率的影响,准静态气动力的估计精度在4×10-3以内;前后级之间的摩擦是轴向力和相对转速的函数,改进的Lu Gre模型对摩擦的估计能够满足工程需求。飞行试验中双旋参数的测试结果验证了双旋模型在全弹道过程中对鸭舵运动预测的可行性,为双旋修正弹的工况预测和控制系统设计提供了分析方法。

The concept of dual-spinning becomes a new approach to upgrade a conventional spin-stabilized projectile,wherein an actuator is used to control the phase of forward canards. To design and analyze the inner control channel efficiently,a dual-spin ordinary differential equation,including a quasisteady aerodynamic model and an optimized Lu Gre friction model,is established. All aerodynamic and kinematic data in time-domain,as input in least square estimation,is obtained in transient numerical model and dynamic wind tunnel test. The results indicate that the side force and roll moment supplied by canards are affected by phase angle and roll rate,and the estimated accuracy of quasi-steady aerodynamics is lower than 4 × 10- 3. The friction between forward and aft parts is a function of axial pressure and relative roll rate,which can be estimated by the optimized Lu Gre model. The feasibility of using the dualspin model to predict the canard movement is validated by measurement in a flight test. The proposed approach promotes the pace of engineering application of dual-spin projectiles.