飞机微波着陆模拟器自动计量系统研制CSCD

本文首先简述了MLS模拟器及其计量性能要求,然后对研制的MLS模拟器自动计量系统进行了详细介绍,包括硬件分系统组成及其关键技术,软件分系统架构及其核心流程;最后将自动计量系统应用于多台MLS模拟器的校准/检定。应用表明,MLS模拟器自动计量系统能够解决MLS模拟器计量保障中存在的问题,确保MLS机载设备各项参数准确一致,进而保证了飞行安全。     

Surface elements and landing strategies for small bodies missions – Philae and beyond

The investigation of small bodies, comets and asteroids, can contribute substantially to our understanding of the formation and history of the Solar System. In-situ observations by Landers play a prominent role in this field.The Rosetta Lander – Philae – is currently on its way to comet 67P/Churyumov–Gerasimenko. It will land in November 2014 and perform numerous experiments with a suite of 10 scientific instruments.Philae has been designed to cope with a wide range of possible comet properties. The considerations taken during its development are relevant for future Lander missions to small bodies in the Solar System.In addition the paper provides a review of alternative concepts, studied or developed for various missions like Phobos, Hayabusa/Minerva or Géocroiseur/Leonard.Various missions to small bodies in the Solar System, including Landers, are currently studied (e.g., Marco Polo). The paper will address the mission options and compare applicable technologies with the solutions chosen for Philae.     

民用运输飞机适坠性要求浅析

全面解读了民用运输飞机适坠性要求,并对CCAR/FAR25与CS25之间差异进行剖析,总结国内外相关经验,提出适坠性后续工作方向。     

Use of land＇s cooperative object to estimate UAV＇s pose for autonomous landing

The research of unmanned aerial vehicles＇（UAVs＇）autonomy navigation and landing guidance with computer vision has important signifcance.However,because of the image blurring,the position of the cooperative points cannot be obtained accurately,and the pose estimation algorithms based on the feature points have low precision.In this research,the pose estimation algorithm of UAV is proposed based on feature lines of the cooperative object for autonomous landing.This method uses the actual shape of the cooperative-target on ground and the principle of vanishing line.Roll angle is calculated from the vanishing line.Yaw angle is calculated from the location of the target in the image.Finally,the remaining extrinsic parameters are calculated by the coordinates transformation.Experimental results show that the pose estimation algorithm based on line feature has a higher precision and is more reliable than the pose estimation algorithm based on points feature.Moreover,the error of the algorithm we proposed is small enough when the UAV is near to the landing strip,and it can meet the basic requirements of UAV＇s autonomous landing.     

两种计算起落架节点载荷方法的比较

Fortran语言编程和有限元是计算起落架节点载荷的两种常用方法。本文运用两种方法计算了某型飞机起落架节点载荷,比较了两种方法的优劣,并得出相关结论。     

Augmented flight dynamics model for pilot workload evaluation in tilt-rotor aircraft optimal landing procedure after one engine failure

An augmented flight dynamics model is developed to extend the existing flight dynamics model of tilt-rotor aircraft for optimal landing procedure analysis in the event of one engine failure.Compared with the existing flight dynamics model, the augmented model involves with more pilot control information in cockpit and is validated against the flight test data. Based on the augmented flight dynamics model, the optimal landing procedure of XV-15 tilt-rotor aircraft after one engine failure is formulated into a Nonlinear Optimal Control Problem(NOCP), solved by collocation and numerical optimization method. The time histories of pilot controls in cockpit during the optimal landing procedure are obtained for the evaluation of pilot workload. An evaluation method which can synthetically quantify the pilot workload in time and frequency domains is proposed with metrics of aggressiveness and cutoff frequencies of pilot controls. The scale of the pilot workload is compared with those of the shipboard landing procedures, bob-up/bob-down and dash/quickstop maneuvers of UH-60 helicopter. The results show that the aggressiveness of pilot collective and longitudinal controls for the tilt-rotor aircraft optimal landing procedure after one engine failure are higher than those for UH-60 helicopter shipboard landing procedures up to the condition of sea state 4, while the pilot cutoff frequency of collective control is lower than that of the bob-up/bob-down maneuver but the pilot cutoff frequency of longitudinal control is higher than that of the dash/quick-stop maneuver. The evaluated pilot workload level is between Cooper–Harper HQR Level 2 and Level 3.     

火星探路者的可膨胀气囊着陆系统综述

火星探路者的再入、下降和着陆系统包括一个独立的子系统—可膨胀气囊 ,用于着陆冲击缓冲。文章介绍了火星探路者可膨胀气囊的发展过程 ,包括 :材料的选择、形状的确定、制造的过程、部件的设计以及打包/展开等。     

前起落架突伸对舰载机起飞特性的影响

研究了前起落架突伸的实现模式和突伸对舰载机起飞特性的影响，分别对四种突伸模式及突伸机构设计参数的作用进行了比较分析，结果表明，前起落架突伸对于减少舰载机离舰后的下沉和缩短飞机起飞滑跑距离有明显的作用。     

飞机起落架系统建模与教学实验平台研究

基于MATLAB/Simulink平台,建立了某大型商用飞机的起落架模型。系统建立了起落架的减震支柱、轮胎侧向力、收放等模型,在此基础上能够实时模拟收放、前起落架转向、主起落架刹车等过程。结合验证数据进行比较证明,仿真结果合理,模型正确。将起落架模型集成到整个飞行实时仿真系统中进行实时仿真,可用于起落架相关的课程教学与研究中。     

载人航天着陆场选择与分析

根据载人航天的任务和特点,结合对着陆场的要求,从工程应用的角度出发,对中国载人航天着陆场进行了选择论证,并进行了综合分析;其正确性和可行性在多次无人飞行试验和两次载人飞行任务中得到实际考核和验证。