非匹配不确定性条件下的编队分布式协同控制

针对非匹配不确定性、饱和输入等约束条件下的编队协同控制问题展开研究。通过引入辅助系统和扩张状态观测器实现对系统状态的实时跟踪;设计了滑模扰动观测器,实现在有限时间内精确估计系统的全部未知扰动;在此基础上,提出了反馈控制协议,显著改善了系统控制性能,有效降低了计算负担,使得通过选择合适参数能够保证状态追踪误差收敛到有界域内;最后通过Lyapunov稳定性理论对控制系统稳定性进行严格证明。数值算例验证了控制协议有效性,结果表明所设计的控制协议能够满足复杂约束条件下的编队协同控制要求。

基于CST的三维机翼气动结构解析参数化建模与优化方法

针对概念设计阶段机翼设计需要大范围探索设计空间并进行气动结构一体化设计的需求,提出一种基于类别/形状变换函数(class-shape function transformation,CST)的三维机翼气动结构解析参数化建模与优化方法。在二维CST基础上,推导三维CST参数化几何模型的解析函数形式,通过网格自适应离散与结构特征提取技术建立了三维机翼的气动和结构解析参数化模型,能够同时支持包括机翼几何构型、结构布局、结构尺寸、材料属性等参数的气动结构一体化快速建模与优化求解,具备几何模型大范围参数化以及气动、结构模型的建模过程自动化能力。采用该方法对某大展弦比机翼开展气动结构一体化优化设计,对比固定结构布局优化方案,优化结果梁由2个减至1个,翼肋由20个减至15个,质量相比减少26.1%。

A rapid approach to convective aeroheating prediction of hypersonic vehicles

A rapid approach to hypersonic aeroheating predictions in the stagnation region and downstream is developed in the present paper.The engineering method is used to calculate inviscid hypersonic flowfields to reduce time cost,and a combination of the mass flow balance technique and the axisymmetric analog is proposed to account for the entropy swallowing effects.A three-dimensional linear method is derived to fit the vehicle surface flowfields.Then a new axisymmetric analog method based on linear flowfields and linear surface equations is developed,with the complexity and computational cost reduced dramatically.In the stagnation region,an implicit surface fitting is introduced to approximate the primary curvatures and a robust aeroheating prediction method is constructed.The proposed approach is verified on a variety of configurations including spherically blunted cone,double ellipsoid and aerospace vehicle.Numerical results indicate the followings:1)The approach predicts aeroheating in about one second and the results agree well with CFD simulations and wind-tunnel measurements;2)with the help of entropy correction,the precision is further improved in the streamline diverging regions on the vehicle surface,while little improvement is found after entropy correction in the regions where the streamlines do not diverge.

Color change characteristics of two shear-sensitive liquid crystal mixtures (BCN/192, BN/R50C) and their application in surface shear stress measurements

A previously determined surface shear stress measurement technique using shear-sensitive liquid crystal (SSLC) coating is extended for use in wind tunnel-like conditions. Simple and common everyday equipment is used in the measurement; in particular a tungsten halogen light bulb provides illumination. The color change characteristics of two SSLC mixtures, BCN192 and BN/ R50C, are investigated. BCN/192 is found sensitive to both magnitude and direction of the shear stress at different shear stress levels with little noise, and is suitable for surface shear stress distribution measurements. The spatial shear stress vector distribution beneath a tangential jet is obtained using BCN/192, although the magnitude is not fully calibrated. BN/R50C is found to be sensitive to shear stress magnitude, but only slightly sensitive to shear stress direction at both low and high levels. Moreover, jumps in the reflected hue are found when the viewing orientation is perpendicular to the shear stress direction. These characteristics render the use of BN/R50C for surface shear stress measurement difficult.

Dynamics of a deflectable-nose missile

The dynamics of a supersonic missile with a deflectable nose are studied. To describe the effects of nose deflection on the dynamic model, theorems of momentum and angular momentum are adopted to develop the translational equation and rotation equation, respectively. Because the exact model is complex, it is simplified. The simplified model suggests that the main influence of nose deflection on the dynamic model is due to the product of the time derivatives of the azimuth angle and the elevation angle, which makes the dynamic model an impulsive differential system. Considering the aerodynamic characteristics a numerical simulation is sufficient to show the open-loop characteristics of the missile.

Windtunnel studies of surface shear stress vector distribution measurement using shear sensitive liquid crystal coatings

Shear sensitive liquid crystal coating (SSLCC) can measure surface shear stress vector distribution efficiently with a high spa-tial resolution. The purpose of the present paper is to modify and extend the surface shear stress measurement technique de-termined by Reda et al. to wind tunnel studies. All the facilities employed in the technique are very common and simple. The measurement technique is applied to surface flow beneath a tangential jet and surface flow in a turbulence wedge generated by a small cylinder in windtunnel flow. Spatially resolved shear stresses over planar surface are obtained, although the magnitude is not fully calibrated.