太阳能无人机机翼颤振动力学建模与分析

太阳能无人机作为一种大展弦比轻质飞行器,其机翼的气动弹性效应显著,其中颤振问题尤为关键。此类飞机具有大尺寸和低刚度特点,通过风洞试验研究机翼颤振问题,成本高而且难度大,难以实现,因此仿真计算是分析此类飞机颤振问题的主要手段。针对国内某翼展为40米的太阳能无人机大展弦比机翼,首先对机翼有限元模型进行工程化处理,在此基础上开展结构动力学分析和颤振计算,重点计算了机翼上不同吊舱布置下的颤振速度。经过仿真计算,得到该太阳能无人机机翼颤振速度为26m/s, 满足设计要求,进一步分析表明,可以通过增加发动机连杆的长度、在发动机上增加配重以及改变吊舱在机翼上的展向站位等手段来提高此无人机的颤振速度。     

Detailed design of a lattice composite fuselage structure by a mixed optimization method

In this article, a procedure for designing a lattice fuselage barrel is developed. It comprises three stages: first, topology optimization of an aircraft fuselage barrel is performed with respect to weight and structural performance to obtain the conceptual design. The interpretation of the optimal result is given to demonstrate the development of this new lattice airframe concept for the fuselage barrel. Subsequently, parametric optimization of the lattice aircraft fuselage barrel is carried out using genetic algorithms on metamodels generated with genetic programming from a 101-point optimal Latin hypercube design of experiments. The optimal design is achieved in terms of weight savings subject to stability, global stiffness and strain requirements, and then verified by the fine mesh finite element simulation of the lattice fuselage barrel. Finally, a practical design of the composite skin complying with the aircraft industry lay-up rules is presented. It is concluded that the mixed optimization method, combining topology optimization with the global metamodel-based approach, allows the problem to be solved with sufficient accuracy and provides the designers with a wealth of information on the structural behaviour of the novel anisogrid composite fuselage design.     

Effects of core machining configuration on the debonding toughness of foam core sandwich panels

Core machining is often applied to improve the formativeness of foam core and the manufacturing effectiveness of sandwich panels. This paper investigates the effects of core machining configuration on the interfacial debonding toughness of foam core sandwich panels fabricated by vacuum-assisted resin transfer molding process. Several machining configurations are conducted to foam core, and skin–core debonding toughness of fabricated sandwich panels is evaluated using double-cantilever-beam tests. The sandwich panels with core cuts exhibited higher apparent fracture toughness than the panels without core cut, specifically in the case of perforated core. The relationship between core machining configuration and measured fracture toughness is discussed based on the experimental observations and the numerical analyses of energy release rates.     

一种新型电静液作动飞机刹车系统

多电飞机已成为现代飞机的发展趋势,其刹车系统不再采用传统的液压刹车.提出一种用于多电飞机刹车系统的泵控和阀控相结合的电静液刹车系统.首先分析了电静液作动器的工作原理和数学模型,对电静液机构进行了单独的控制仿真;接着对飞机刹车系统进行数学建模,并将这种电静液作动飞机刹车系统进行控制仿真.仿真结果表明,基于电静液作动器的刹...     

基于80C186处理器的多功能实验板的研制

针对近年来飞机含80C186处理器电路板修理现状,为掌握该系列板件的修理能力,迫切需要开展其软件测试技术研究.从封装、类型以及时序分析角度,在对80C186处理器进行系统阐述基础上,设计并研制一块基于80C186处理器的多功能(包括串口通信、并口检测以及定时计数功能)实验板,给出该板的硬件电路图与软件流程框图,并基于汇编语言在QTH-2008PCI开发环境下进行功能调试,实验结果表明其有效性.所做的含80C186处理器的正向设计与软件编程研究工作对于逆向修理含80C186处理器飞机电路板板件有很大帮助.     

基于光电跟踪的飞机校靶技术研究

在分析机械式校靶方法过程和缺陷的基础上,根据空间向量和矩阵变换运算的基本原理,提出一种采用光电跟踪瞄准技术、数字图像显示技术和数学建模与实时解析技术的数字化飞机校靶方法,介绍了该方法的原理,进行了误差分析仿真,证明该方法校靶精度远高于传统方法,给出了详细飞机校靶工程化解决方案.     

某型飞机振动传感器试验器的研制

为测试某型飞机振动传感器性能,采用背靠背比较法振动测试方法,基于苏试振动台(VT-500)、功率放大器(LA-800)、单轴向电荷输出型加速度标准传感器(Ymc222A25)、电荷放大器(Ymc8102T)、普源信号发生器(DG1032Z)以及研华PCI工控机与A/D板卡(PCI-1716L),搭建振动传感器试验器振动测试平台,以DG1032Z输出作为振动激励信号源,基于VC ++6.0开发出信号发生器远程控制与板卡信号采集软件,对试验器的功能进行试验验证,结果表明其有效性.所研制的试验器可实现振动信号源的产生与标准/被测信号的校准,从而为某型飞机振动传感器的测试与修理提供技术支撑.     

变体飞行器平滑切换LPV 鲁棒控制

针对一类变体飞行器控制问题, 提出一种平滑切换线性变参数(LPV) 鲁棒控制器设计方法. 建立变体飞行器切换LPV 模型, 设计平滑切换控制器, 其中偶数子系统控制器由相邻两个子系统控制器线性插值得到. 给出保证切换LPV 系统指数稳定且具有一定鲁棒性能的充分条件, 由于考虑了调参变量的渐变特性, 所得切换律没有平均驻留时间的限制. 仿真结果表明, 所提出方法使得飞行器系统既具有良好的稳定性和鲁棒性, 又能实现平滑切换.

     

飞机腐蚀搭接板的应力分析

为降低由于铝合金腐蚀产生的膨胀作用引起的枕垫效应对飞机搭接板应力的影响,利用非线性有限元法分别对不同铆钉弹性模量、不同搭接板弹性模量和不同搭接板泊松比下的腐蚀搭接板进行仿真分析.结果表明：枕垫效应对搭接板应力的影响随着铆钉弹性模量的增大、搭接板弹性模量和泊松比的减小而减小.