考虑飞行品质约束的空天飞行器控制舵面设计及优化

Control Surface Design and Optimization for Aerospace Vehicle Under Handling Quality Constraints

针对放宽静稳定度条件下水平起降空天飞行器控制舵面尺寸设计难度大的问题,提出了一种基于代理模型的控制舵面—控制参数一体化设计方法。首先,基于鸽群算法构建了包含结构参数的空天飞行器气动特性代理模型,获得了气动特性参数随飞行条件、控制舵面尺寸及质心位置的变化关系,为控制舵面一体化设计提供输入。然后,设计了基于C*结构的空天飞行器纵向参考模型跟踪控制律,并将考虑飞行品质约束的空天飞行器控制舵面一体化设计问题转化成多约束条件下的多目标优化问题。并采用非光滑优化算法计算得到了同时满足飞行品质、舵面饱和、舵面偏转速率等约束的最小控制舵面及对应的控制参数。仿真结果表明,该方法能够在满足性能指标约束的前提下有效减小控制舵面的尺寸,具有较强的工程应用价值。

Control surface design and optimization is a main challenge of horizontal take-off and horizontal landing(HTHL)aerospace vehicles with relaxed static stability.An integrated control surface/parameter design method based on surrogate model is proposed in this paper.Firstly,an automatic aerodynamic surrogate model is established based on improved pigeon swarm algorithm for aerospace vehicles with different control surface size,which effectively reflects the relationship of aerodynamic coefficients with flight conditions,control surface size,and center of gravity position,providing necessary input for integrated design.Then,the longitudinal reference model tracking control structure is built based on C*control law,and the integrated design is transformed into multi-objective optimization under multi-constraints.The non-smooth optimization algorithm is adopted to solve this non-convex problem,resulting in minimum control surface size and corresponding control parameters,which simultaneously satisfies handling quality,control surface deflection,and deflection rate saturation constraints.Finally,simulation results indicate that the proposed integrated design method can effectively reduce the control surface size while satisfying the performance constraints,making it suitable for industrial applications.