航空用燃料电池及混合电推进系统发展综述

随着世界范围内碳减排需求的日益增长及长航时飞机的发展需要,高效率的燃料电池航空电推进系统逐渐受到重视,氢能航空的理念被人们所熟知。可使用碳氢燃料的高温燃料电池还可与燃气涡轮组成混合动力系统,发电效率进一步提高至70%。本文首先回顾了燃料电池及燃料电池涡轮混合系统在航空能源、动力系统方向应用概况;接着,概述了几种突破现有涡轮发动机技术瓶颈的新概念混合电推进系统,如发电与推进一体化燃料电池涡轮混合动力系统和无涡轮燃料电池混合推进系统;基于此,本文分析了限制燃料电池混合系统实际应用的关键技术难题,主要体现在混合动力系统功重比较低、大分子碳氢燃料重整技术未突破两方面。     

SAR图像舰船目标边缘检测

提出了一种在正则化基础上,利用小波变化实现合成孔径雷达(SAR)图像舰船目标边缘检测的新方法。传统的利用小波变换实现图像边缘检测时,阈值需要人为设定。针对这一问题,文章引入正则化超分辨技术,从贝叶斯框架下的估计问题出发,采用非二次正则化,平滑图像,保护强散射点目标,实现对 SAR图像进行去噪。利用小波变换的局部化特性和多尺度分析能力,检测突变信号,实现对舰船目标的边缘检测。该方法去噪效果好,边缘 定位准确,仿真结果表明了算法的有效性。     

可变构型复合柔性结构航天器动力学建模研究

针对中心刚体加复合柔性结构类航天器采用混合坐标法和子结构模态综合法，建立了可变构型复合柔性结构航天器低阶动力学模型。获得的柔性动力学方程及其各类耦合系数矩阵，适用于全星级可变构型系统和部件级复合柔性附件系统的控制系统设计与仿真，该模型具有阶数低和工程实用的特点。     

用基于混合网格的多重网格法数值模拟绕物体的紊流流动

本文在混合网格基础上用多重网格法求解了紊流N-S方程。混合网格是由在物面附近采用的柱状网格与其他区域则采用的非结构网格组成。方程的求解采用Jamson的有限体积法，紊流模型采用两层Baldwin-Lomax代数紊流模型。用多重网格法来加速解的收敛。数值算例表明，用混合网格及多重网格法来求解紊流Navier-Stokes是非常有效的。     

Hybrid calibration method for six-component force/torque transducers of wind tunnel balance based on support vector machines

A hybrid calibration approach based on support vector machines (SVM) is proposed to characterize nonlinear cross coupling of multi-dimensional transducer. It is difficult to identify these unknown nonlinearities and crosstalk just with a single conventional calibration approach. In this paper, a hybrid model comprising calibration matrix and SVM model for calibrating linearity and nonlinearity respectively is built up. The calibration matrix is determined by linear artificial neural network (ANN), and the SVM is used to compensate for the nonlinear cross coupling among each dimension. A simulation of the calibration of a multi-dimensional sensor is conducted by the SVM hybrid calibration method, which is then utilized to calibrate a six-component force/torque transducer of wind tunnel balance. From the calibrating results, it can be indicated that the SVM hybrid calibration method has improved the calibration accuracy significantly without increasing data samples, compared with calibration matrix. Moreover, with the calibration matrix, the hybrid model can provide a basis for the design of transducers.     

混合回归模型及其在高耸结构风响应时域分析中的应用

针对多维ＡＲ模型同时求解回归系数矩阵所有元素的一些不足之处，本文提出了混合回归模型。通过对某一高耸结构的分析，表明混合回归模型对脉动风的模拟是有效的，并人数值模拟角度验证了，对于线性结构，外激的各态历经性可保证响应的各态历经性。     

High-resolution simulation for rotorcraft aerodynamics in hovering and vertical descending flight using a hybrid method

A high-resolution simulation tool for rotorcraft aerodynamics is developed by coupling CFD with a Vorticity Transport Model (VTM). An Eulerian-based CFD module is used to model the blade near body flowfield, and a Lagrangian-based VTM module is employed for vortex tracking in the far wake. The coupling procedure is implemented by transmitting vortex sources to the VTM module and feeding boundary conditions back to the CFD module. The presented CFD/VTM hybrid solver is firstly validated by hover cases of three different rotor configurations. Simulation results, including the blade surface pressure distribution, rotor downwash, and hover figure of merit, exhibit favorable correlations with available experimental data. Then, a rotor operated in vertical descending flight with a fixed collective pitch is investigated. It is shown that the CFD/VTM coupling method is suitable for rotor wake simulation. Wake instabilities (far wake breakdown in hover and toroidal wake pattern in the vortex ring state) are successfully demonstrated with a moderate computational cost.     

A hybrid lattice Boltzmann flux solver for integrated hypersonic fluid-thermal-structural analysis

In this paper, a hybrid Lattice Boltzmann Flux Solver (LBFS) with an improved switch function is proposed for simulation of integrated hypersonic fluid-thermal-structural problems. In the solver, the macroscopic Navier–Stokes equations and structural heat transfer equation are discretized by the finite volume method, and the numerical fluxes at the cell interface are reconstructed by the local solution of the Boltzmann equation. To compute the numerical fluxes, two equilibrium distribution functions are introduced. One is the D1Q4 discrete velocity model for calculating the inviscid flux across the cell interface of Navier–Stokes equations, and the other is the D2Q4 model for evaluating the flux of structural energy equation. In this work, a new dual thermal resistance model is proposed to calculate the thermal properties at the fluid–solid interface. The accuracy and stability of the present hybrid solver are validated by simulating several numerical examples, including the fluid-thermal-structural problem of cylindrical leading edge. Numerical results show that the present solver can accurately predict the thermal properties of hypersonic fluid-thermal-structural problems and has the great potential for solving fluid-thermal-structural problems of long-endurance high-speed vehicles.     

Interaction mechanisms of shock waves with the boundary layer and wakes in a highly-loaded NGV using hybrid RANS/LES

Accurate predictions of Shock Waves and Boundary Layer Interaction (SWBLI) and strong Shock Waves and Wake Vortices Interaction (SWWVI) in a highly-loaded turbine propose challenges to the currently widely used Reynolds-Averaged Navier-Stokes (RANS) model. In this work, the SWBLI and the SWWVI in a highly-loaded Nozzle Guide Vane (NGV) are studied using a hybrid RANS/LES strategy. The Turbulence Kinetic Energy (TKE) budget and the Proper Orthogonal Decomposition (POD) method are used to analyze flow mechanisms. Results show that this hybrid RANS/LES method can obtain detailed flow structures for flow mechanisms analysis. Strong shock waves induce boundary layer separation, while the presence of a separation bubble can in turn lead to a Mach reflection phenomenon. The shock waves cause trailing-edge vortices to break clearly, and the wakes, in turn, can change the shocks intensity and direction. Furthermore, the Entropy Generation Rate (EGR) is used to analyze the irreversible loss. It turns out that the SWWVI can reduce the flow field loss. There are several weak shock waves in the NGV flow field, which can increase the irreversible loss. This work offers flow mechanisms analysis and presents the EGR distribution in SWBLI and SWWVI areas in a transonic turbine blade.     

Application of novel force control strategies to enhance robotic abrasive belt grinding quality of aero-engine blades

Robotic belt grinding has emerged as a finishing process in recent years for machining components with high surface finish and flexibility.The surface machining consistency, however,is difficult to be guaranteed in such a process.To overcome this problem, a method of hybrid force-position control combined with PI/PD control is proposed to be applied in robotic abrasive belt grinding of complex geometries.Voltage signals are firstly obtained and transformed to force information with signal conditioning methods.Secondly, zero drift and gravity compensation algorithms are presented to calibrate the F/T transducer which is installed on the robot end-effector.Next, a force control strategy combining hybrid force-position control with PI/PD control is introduced to be employed in robotic abrasive belt grinding operations where the force control law is applied to the Z direction of the tool frame and the positon control law is used in the X direction of the tool frame.Then, the accuracy of the F/T transducer and the robotic force control system is analyzed to ensure the stability and reliability of force control in the robotic grinding process.Finally, two typical cases on robotic belt grinding of a test workpiece and an aero-engine blade are conducted to validate the practicality and effectiveness of the force control technology proposed.