WiFi环境下的微型四轴飞行器系统设计

为改善传统四轴飞行器体积大、不便于携带、航模遥控器操作复杂等问题,从易用性的角度出发,提出了基于WiFi控制的微型四轴飞行器设计方案.系统以STM32处理器为核心,MPU6050、HMC5883组成惯性测量单元测量飞行器姿态,上位机通过WiFi与飞行控制器进行数据交互;并引入RT-Thread嵌入式实时操作系统,以满足飞行姿态控制的实时性要求.经实验测试,飞行器能在较短时间内对上位机的操作指令进行响应,并按照指定操作稳定飞行,系统基本完成预期目标.     

航空飞机计算机通信中滤波器的优化设计

航空飞机计算机通信系统进行通信的过程中,由于航空飞机上的电子设备相互之间的电磁干扰严重,导致信道中存在大量的干扰信号;提出基于小波变换算法的抗干扰滤波器设计方法;根据小波变换算法相关原理,综合航空飞机通信中特有的软阈值特点,利用自适应调整参数的方法得到高空通信中的最优小波系数阈值,使得高空噪声过滤阈值函数具有更强的适应性;利用新的阈值函数设计了新的滤波器,对行滤波模块和列滤波模块的设计进行了详细阐述;实验结果表明;利用设计的滤波器能够对航空飞机计算机通信过程中的干扰信号进行有效滤波,缩短了滤波时间,提高了高空通信系统的抗干扰能力.     

面向分级设计优化的飞行器参数化建模方法

针对飞行器气动隐身外形综合设计优化问题,提出合适的面向分级设计优化流程,建立适应该流程的渐进分层参数化建模方法;用基于敏度分析的参数影响程度分析方法筛选复杂设计变量;采用多学科设计优化（Multidisplinary Design Optimization,MDO）理论和差分进化算法进行飞行器气动隐身外形的综合设计优化.将该方法用于某飞行器外形设计优化,结果表明：该方法合理可行,可为飞行器外形多学科设计优化提供一定参考.     

Influence of wall charge distribution on time lag of address discharge in AC plasma display panels

The influence of wall charge distribution on the time lag of address discharge in an AC plasma display panel is investigated using two different reset waveforms: one (typical reset) induces both face and surface discharges and the other (TR reset) induces face discharges only. The measured formative time lag and statistical time lag of address discharge for TR were 21–31 ns and 31–74 ns shorter than the one for the typical reset, respectively. The TR reset resulted in much less increase of statistical time lag than the typical reset when the reset-to-address time interval was increased, and 70 ns smaller deviation of the statistical time lag among different color cells. Calculations show that the TR reset forms a much smoother wall charge profile, which is less susceptible to cell parameter variations, than the typical reset. The observed differences in the time lags of address discharge between different scan lines and color cells are strongly correlated to the differences of the wall charge profile, indicating that a smooth wall charge profile formed by the reset using face discharges only reduces the time lag of address discharge and minimizes the susceptibility of address discharge to cell parameter variation.     

基于滤噪微分器的四旋翼飞行器控制

在飞行器的控制中, 角速率反馈可以提高控制系统的动态特性, 但速率陀螺价格昂贵, 且随运行时间的增加其性能会不断下降. 对此本文提出了一种基于滤噪微分器的四旋翼飞行器滑模变结构控制律. 该控制律使用的反馈信号仅由角度传感器得到, 而无需角速率传感器. 控制律中的角速率信息由王新华等设计的有限时间收敛的微分器得到. 本文通过数学证明, 给出了当测量信号中含有噪声时该微分器的理论跟踪误差上界. 仿真以及对四旋翼飞行器滚转姿态的控制实验验证了微分器的抑制噪声作用和控制算法可行性.     

基于遗传算法的航空发动机性能曲线逼近

绘制性能曲线是检验航空发动机是否合格的重要工作步骤.利用标准性能曲线板手工绘制往往具有较大的作图和读数误差.变换标准曲线的数值计算方法会带来变换计算量大,求解Y值复杂的问题.求解过程中变换测量点,求出平移和旋转量后,反向变换标准曲线获得实测曲线.通过对平移和旋转量进行编码,采用遗传算法实现了性能曲线逼近.     

改进的自适应阈值区域图像分割方法在飞机目标识别中的应用

阈值分割是图像分割的常用方法。本文提出采用基于改进的自适应阈值区域分割方法,提高了对飞机目标遥感图像的分割效果。结果表明,该分割方法具有针对性,比传统方法具有明显的优势。     

Rationally Designed Anti-Glare Panel Arrays as Highway Wind Energy Harvester

The anti-glare panels along highways can block the dazzling lights of opposing vehicles at night, playing an important role in the highway safety. Inspired by the highway anti-glare panels, wind energy harvesting triboelectric nanogenerator (AG-TENG) arrays to properly capture energy from highway moving vehicles is developed. A single AG-TENG installation module can achieve a high power density of 0.2 Wm⁻² at a wind speed of 3 m s⁻¹. This wind speed is too low to drive conventional wind energy harvesting equipment. The performance of the AG-TENG shows no degradation after 80 h of continuous operation (1 440 000 times). Thus, with the rational consideration and features, the system can generate enough power to drive internet of things (IoT) devices and environmental sensors, as well as offer wireless alarming and radio frequency identification vehicle monitoring. This study provides a promising strategy to properly harvest wind energy on highways using existing infrastructures under the condition of even no natural wind, showing broad application prospects in distributed environmental monitoring, intelligent highways, and the IoT.     

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.