Quantitative assessment and visualization of flight risk induced by coupled multi-factor under icing conditions

Aircraft icing has been proven to be one of the most serious threats to flight safety. During the analysis of flight risk under icing conditions, quantitative assessment and visualization of flight risk are quite essential as they provide safe manipulation strategies in intricate conditions. However, they are rarely studied. Since the icing flight accidents are the result of the coupling of multiple unfavorable factors, in present study, we have proposed a method to quantitatively assess flight risk induced by multi-factor coupling under icing conditions by Monte-Carlo simulation and multivariate extreme value theory. The results demonstrate that the flight risk probability increases with the rise of unfavorable factors. Besides, a flight risk visualization method named flight safety window has been presented to build the flight risk distribution cloud maps in different complex conditions. The cloud maps show that the icing would give rise to atrophy of the safety scope, and the consequence would be even more severe when coupled with other more unfavorable factors. The proposed methods in this study would be useful in flight risk analysis under icing conditions and can enhance the pilot's situational awareness in selecting correct strategies within the safety zone to avoid unsafe manipulation.     

利用地月间空间站的载人登月飞行模式分析

为提高空间站利用率，降低载人登月任务成本，有效开发地月空间，研究了基于地月空间不同轨道空间站的载人登月飞行模式。首先对比直接往返登月飞行模式，对基于空间站的载人登月飞行模式进行任务分析，通过空间站将载人登月任务解耦为载人天地往返任务和登月任务两部分；其次通过轨道设计和稳定性分析提出考虑登月任务需求的地月间空间站可运行轨道和停泊点；最后建立一套飞行模式评价模型，从速度增量需求、飞行时间、空间环境、登月任务窗口、测控条件、交会对接技术难度、后续任务支持性和任务可靠性方面对6种不同位置空间站的登月飞行模式进行分析和定量评价。评价结果表明基于L2点Halo轨道空间站的载人登月飞行模式为更优飞行模式。     

一种基于系留无人机的图像遥测系统设计

针对海上船舶甲板的监控需求，本文提出了一种基于系留无人机的图像遥测系统设计方法，即通过系留无人机上的图像采集装置对被监控目标进行视频信号实时采集、压缩，再经过遥测装置的编码、调制、放大后由天线进行辐射，最后由数十公里外的遥测接收机完成接收、解调、解码，可实时显示船舶甲板图像信息。文中介绍了系统的软硬件组成、关键设备的设计方法、综合性能的分析，对相关图像遥测技术应用有一定参考意义。     

一种未来大型天地往返运输系统平台气动方案

针对未来低运行成本、可直接水平起降、重复使用的大型天地往返运输系统平台飞行器研制所需重点解决的全速域气动力性能需求与气动热防护匹配等难题，分析了典型航天飞机方案所存在的能量运行缺陷等主要问题及可能的改善方案。基于放宽气动热防护设计、涡轮/冲压/火箭发动机三动力组合、嵌套式旋转机翼全速域变体、在爬升阶段将飞行动能转化为高度势能以及再入阶段“跳跃式”盘旋减速飞行轨迹控制等设计思想，从能量损失速率控制和回收利用等角度出发，开展了一种新型大型天地往返运输系统平台气动布局概念设计研究。全速域气动力/热性能工程估算以及内/外流整体气动效能初步分析结果表明，该方案可有效满足整个飞行包线内的升重平衡需求，相比航天飞机方案具有显著的整体气动效能优势，值得进一步开展深入研究。     

A CFD-based numerical virtual flight simulator and its application in control law design of a maneuverable missile model

A CFD-based Numerical Virtual Flight (NVF) simulator is presented, which integrates an unsteady flow solver on moving hybrid grids, a Rigid-Body Dynamics (RBD) solver and a module of the Flight Control System (FCS). A technique of dynamic hybrid grids is developed to control the active control surfaces with body morphing, with a technique of parallel unstructured dynamic overlapping grids generating proper moving grids over the deflecting control surfaces (e.g. the afterbody rudders of a missile). For the flow/kinematic coupled problems, the 6 Degree-Of-Freedom (DOF) equations are solved by an explicit or implicit method coupled with the URANS CFD solver. The module of the control law is explicitly coupled into the NVF simulator and then improved by the simulation of the pitching maneuver process of a maneuverable missile model. A nonlinear dynamic inversion method is then implemented to design the control law for the pitching process of the maneuverable missile model. Simulations and analysis of the pitching maneuver process are carried out by the NVF simulator to improve the flight control law. Higher control response performance is obtained by adjusting the gain factors and adding an integrator into the control loop.     

民用飞机飞控系统副翼下垂浅析

在飞机起飞或着陆飞行阶段,当缝翼伸出襟翼放下时,副翼也随之对称地下偏一定偏度,这就增加了机翼的弯度,提高了机翼升力。从而减少了飞机起飞／着陆的速度和场长,改善了起飞和着陆性能。通过介绍X飞机与Y飞机的副翼下垂功能的历史发展、功能原理与功能实现,较详细地分析了副翼下垂功能的实现方式。     

民机新一代驾驶舱显示技术

在研究最新大型民用客机驾驶舱显示技术及平视显示器、电子飞行包、视景增强、合成视景等一系列新兴在研技术基础上,提出新一代驾驶舱显示技术的构想。新一代驾驶舱显示技术将以形象化的信息表达能力为基础,显示更丰富的周围环境,以达到降低飞行员工作量及提高飞行员情景意识和态势感知能力的目的。     

九寨机场航务代理工作浅谈

在分析了九寨机场的气象特点以及环境因素对航空器造成的影响的基础上,就如何做好九寨机场的航务代理工作提出了合理建议和措施,这对提高航班正常率非常重要.     

Design of a canard configured TransCruiser using CEASIOM

CEASIOM is a multidisciplinary software environment for aircraft design that has been developed as part of the European Framework 6 SimSAC project. It closely integrates discipline-specific tools such as those used for CAD, grid generation, CFD, stability analysis and control system design. The environment allows the user to take an initial design from geometry definition and aerodynamics generation through to full six degrees of freedom simulation and analysis. Key capabilities include variable fidelity aerodynamics tools and aeroelasticity modules. The purpose of this paper is to demonstrate the potential of CEASIOM by presenting the results of a Design, Simulate and Evaluate (DSE) exercise applied to a novel, project specific, transonic cruiser configuration called the TCR. The baseline TCR configuration is first defined using conventional methods, which is then refined and improved within the CEASIOM software environment. A wind tunnel model of this final configuration was then constructed, tested and used to verify the results generated using CEASIOM.     

Multi-level virtual prototyping of electromechanical actuation system for more electric aircraft

Electromechanical actuators (EMAs) are becoming increasingly attractive in the field of more electric aircraft because of their outstanding benefits, which include reduced fuel burn and maintenance cost, enhanced system flexibility, and improved management of fault detection and isolation. However, electromechanical actuation raises specific issues when being used for safety-critical aerospace applications like flight controls: huge reflected inertia to load, jamming-type failure, and increase of backlash with service due to wear and local dissipation of heat losses for thermal balance. This study proposes an incremental approach for virtual prototyping of EMAs. It is driven by a model-based system engineering process in order to enable simulation-aided design. Best practices supported by Bond graph formalism are suggested to develop a model’s structure efficiently and to make the model ready for use (or extension) by addressing the above mentioned issues. Physical effects are progressively introduced, and the realism of lumped-parameter models is increased step-by-step. In particular, multi-level component models are architected to ensure continuity between engineering activities. The models are implemented in the AMESim simulation environment, and simulation responses are given to illustrate how they can be used for preliminary sizing, control design, thermal balance verification, and faults to failure analysis. The proposed best practices intend to provide engineers with fast, reusable, and efficient means to assess performance virtually and enhance maturity, performance, and robustness.