模拟训练系统中虚拟仪表设计的方法学研究

在武器装备模拟训练系统研制领域,基于DiSTI GL Studio的虚拟仪表技术已得到广泛应用.针对虚拟仪表设计在模拟训练系统开发过程中存在的实际问题,从虚拟仪表设计的方法学角度出发,在分析虚拟仪表一般设计过程的基础上,重点研究了仿真模型可复用性和多线程机制在虚拟仪表设计中的实现.工程实践表明,这些方法可以大幅提升虚拟仪表的设计质量和虚拟仪表与训练系统的集成效率.     

多功能仪表显示设备软件的开发

文章结合载人航天器返回舱的仪表显示设备的软件开发实践,对如何利用 VAPS 及其相关配套工具所提供的先进功能来完成多功能显示设备软件的开发进行了探讨。指出了传统的 C语言手工编程开发方法的困境,介绍了利用 VAPS 及其相关配套工具进行软件开发的方案和步骤。此技术国外已成功应用到航天及航空的座舱仪表显示设备的研究开发中。     

嵌入式电子飞行仪表显示系统的设计与实现

前言 电子飞行仪表系统(以下简称仪表系统)通过机载计算机收集飞机上的各种传感器数据,再经过实时 的汁算处理,以动态图形的方式显示在CRT或LCD上,给飞行员提供飞行、导航及飞机系统的信息。 由于飞机上的特殊应用环境,对机载计算机体积和应用环境有着特殊的要求。常见的PC由于其较 大的体积和对环境条件的苛刻要求,不适合在飞机上使用。近年来,以ARM为核心的嵌入式CPU发展迅 速。其强大的运算能力,SoC的集成设计,微小的体积,使其非常适合各种嵌入式场合应用。     

计算机自动测试与诊断技术在航天领域中的应用

一、前言 随着计算机的发展,故障测试与故障诊断实现自动化已经成为可能。过去靠人工、仪表实现的故障检测,早已由计算机辅助测试(CAT—Computer Aided Test)系统替代。计算机辅助测试系统大都通过计算机和可编程的仪器、仪表组合成较庞大的测试系统,通过软件实现对被测部件或被测系统的测试,提供了比人工测试更为准确、更加迅速的测试     

地形跟随雷达计算机系统设计

地形跟随雷达的核心是控制计算机系统，它是典型的分布式机载计算机，其完成的功能是：地形跟随雷达的控制、数据处理、数字扫描变换处理和实现与飞机航空电子的通讯等，本文将详细介绍地形跟随雷达计算机系统的硬件设计和系统软件设计。     

基于磨料和电化学作用的去毛刺技术

切削加工过程中形成的毛刺，对产品装配后的性能会造成很严重的影响，尤其在航空、航天精密仪表、伺服机构中，毛刺等这类多余物必须事先清除干净。本文结合我校科研成果，论述了基于磨料和电化学作用的挤压珩磨去毛刺、磁性磨料流去毛刺和磁性磨料流电解去毛刺等几种先进去毛刺技术的原理、特点和适用范围。     

基于动态链接库的虚拟仪表建模与仿真

仿真模型的可复用性是建模与仿真领域的研究重点。在分析基于DiS-TI GL Studio的虚拟仪表一般设计方法基础上,从提升仿真模型可复用性角度出发,研究了基于动态链接库的虚拟仪表和虚拟面板设计方法,提出了仿真系统中虚拟面板的动态加载技术。工程实践表明,该方法可以显著提高仿真模型可复用性,为复杂武器系统中虚拟面板与仿真系统的融合提供高效解决方案。     

电子导航着陆控制系统的仿真设计与实现

介绍了电子导航着陆控制系统的仿真设计原理与实现过程,解决了航空机务培训过程中缺乏电子导航着陆控制系统实装的难题,对增强航空机务维护人员的维护能力、提高航空装备维修保障能力和战斗力具有重要意义。     

航天器器一地对应仪表显示系统软件的设计与实现

仪表显示系统作为航天器性能参数、导航参数显示及航天员人机交互的窗口,在航天飞行任务中发挥着重要作用.针对依据工程遥测源码值监视航天器状态的传统方法直观性差、不便于地面人员监控的特点,文章设计并开发了一套基于VC++和OpenGL的航天器器一地对应仪表显示系统软件,并对其实现进行了分析和说明.该软件仿真了多功能仪表显示器...     

电弧离子镀膜设备与工艺

电弧离子镀膜设备与工艺电弧离子镀膜是一种新型离子镀膜技术，可镀多种金属，也能镀多层膜、合金膜、化合物膜等。膜层可用于耐磨、耐蚀、装饰及软包装镀层。可广泛用于航空、航天、机械、石化、仪表、轻工及装饰等行业。ＬＳＡ－１型电弧离子镀膜机采用最新磁埸设计及电...     

Intelligent and Autonomous Flight Technology for Launch Vehicles

This paper proposes the architecture of an intelligent flight launcher system as well as fundamental solutions to capability prediction and dynamic planning. This effort reflects the latest progress in the applications of intelligent and autonomous technology for launcher flights. The paper first describes the characteristics and capabilities of intelligent and autonomous systems and classifies various related technologies. In the context of intelligent and autonomous technology in aerospace engineering, it then focuses on technical difficulties involved with intelligent flight and reviews developments in the field. An E~3 classification model of an intelligent flight launcher is then proposed and its application scenarios are discussed. Based on an intelligent flight system configuration of the launcher, the online trajectory planning and initial value guess are examined, and vertical landing is provided as an example to explain the effects of the implementation of computational intelligence to flight systems.     

平流层飞艇飞行温度限和飞行速度限分析

平流层飞艇的飞行性能对其飞行安全、机动能力等非常重要.本文结合平流层飞艇的特点,提出"飞行温度限"和"飞行速度限"对其极限飞行性能进行评估,并在理论分析的基础上,提出相应的估算方法.通过具体实例,对平流层飞艇的极限飞行性能进行评估.     

弹载导航星表的设计与实现

根据弹道导弹飞行时间短,飞行姿态相对稳定的特性,提出了一种弹载导航星表的设计方法。分析了导弹飞行轨迹投影的特点,其在天球上投影为大圆,在地心惯性坐标系XOY平面上的投影为椭圆,并对飞行轨迹进行分类。根据限制条件,确定出星敏感器扫描的视场区域,挑选出视场中的恒星,构建出弹载导航星表,并与传统的三角形星表进行比较。仿真结果表明,该方法简单、易行,存储容量较小,同时避免了在两极的情况下,赤经难以表示的问题。减少了星图识别时间,提高了星光制导的数据输出率,满足了星光制导在弹道导弹上应用的要求。     

美国高轨抵近操作卫星MiTEx飞行任务及启示

简述了美国"微卫星技术试验"(Micro-satellite Technology Experiment,MiTEx)计划进展情况,根据目前可获得的最新的MiTEx卫星轨道数据,对其整个飞行过程进行了深入研究,划分了MiTEx-A卫星与MiTEx-B卫星飞行阶段,描述了各阶段飞行轨迹,给出了飞行任务关键数据,对其飞行任务进行了总结。在飞行任务分析的基础上,结合国外对MiTEx卫星的相关报道,分析了MiTEx卫星可能具备的抵近操作任务执行能力,提出了对高轨非合作目标抵近操作应用的启示,总结分析了执行高轨抵近操作任务所需的关键技术。     

Design and implementation of the flight dynamics system for COMS satellite mission operations

The first Korean multi-mission geostationary Earth orbit satellite, Communications, Ocean, and Meteorological Satellite (COMS) was launched by an Ariane 5 launch vehicle in June 26, 2010. The COMS satellite has three payloads including Ka-band communications, Geostationary Ocean Color Imager, and Meteorological Imager. Although the COMS spacecraft bus is based on the Astrium Eurostar 3000 series, it has only one solar array to the south panel because all of the imaging sensors are located on the north panel. In order to maintain the spacecraft attitude with 5 wheels and 7 thrusters, COMS should perform twice a day wheel off-loading thruster firing operations, which affect on the satellite orbit. COMS flight dynamics system provides the general on-station functions such as orbit determination, orbit prediction, event prediction, station-keeping maneuver planning, station-relocation maneuver planning, and fuel accounting. All orbit related functions in flight dynamics system consider the orbital perturbations due to wheel off-loading operations. There are some specific flight dynamics functions to operate the spacecraft bus such as wheel off-loading management, oscillator updating management, and on-station attitude reacquisition management. In this paper, the design and implementation of the COMS flight dynamics system is presented. An object oriented analysis and design methodology is applied to the flight dynamics system design. Programming language C# within Microsoft .NET framework is used for the implementation of COMS flight dynamics system on Windows based personal computer.     

Ultralight deployable booms for solar sails and other large gossamer structures in space

Future solar sail spacecraft which do not need any rocket motors and propellants are a promising option for long-term exploration missions in the solar system. However, they will require ultralight reflective foils and deployable booms which will allow for the unfolding of huge sails. The achievement of an acceptable ratio of reflective sail area and structural mass, which results in a still small, but significant acceleration under the photon pressure of sunlight, is extremely challenging. The same challenging deployment technique is required for the unfolding of large reflector membranes or antennas (gossamer structures). The key elements are the booms which must be stowable in a very small envelope before they reach their destination in space. Such booms were developed by DLR and have been successfully tested under zero-g-conditions during a parabolic flight campaign in February 2009. It could be convincingly demonstrated that the unfolding process is both controllable and reproducible. The booms consisted of two co-bonded omega-shaped carbonfiber half shells with 0.1 mm wall thickness each and had a weight of only 62 g per meter. Two different deployment technologies were tested, one based upon an inflatable 12 μm thick polymer hose inside the boom, the other one using an electromechanical uncoiling device at the tip of each boom. In the latter case, the uncoiling devices will radially fly away from the spacecraft, such that they become “expendable deployment mechanisms” and their mass does not count any more for the spacecraft mass that needs to be accelerated or actively controlled.     

SFMEA方法在飞行控制软件中的应用

为提高飞行控制软件的安全性,分析了飞行控制软件的安全性薄弱环节,探讨了影响飞行控制软件安全性的隐患。简要阐述了软件失效模式、影响(SFMEA)方法,给出软件失效模式分类的方法以及飞行控制软件常见的失效模式,给出适用于航天飞行控制软件的软件危害性等级,结合某型号飞行控制软件进行了SFMEA方法的尝试性应用,分析了软件失效的局部影响和最终影响,形成了52个SFMEA的分析表格,总结了302个飞行控制软件的失效模式,发现了部分安全性薄弱环节,并提出了相应的改进措施,结果表明,SFMEA方法对提高飞行控制软件的安全性有一定的工程价值。     

高速飞行器非视距短波通信的可行性验证飞行试验

当高速飞行器处于失稳失控等紧急情况时，现有航天器测控方法可能面临地面站天线无法及时跟踪和对准飞行器的问题，这将导致测控通信链路的中断，无法传输紧急的安控遥控指令。为了在飞行器失稳失控、非视距通信时与地面站维持通信，提出将短波通信应用于高速飞行器测控通信系统的应急通信，并进行非视距短波通信的飞行试验以验证方法的可行性。在试验中，地面站发射7 MHz的短波信号，高速飞行器内部安装的交流磁场计用于接收短波信号，获得了短波的磁场强度与飞行环境的本底噪声。试验结果表明，随着飞行器海拔的增加，磁场强度减小，高速飞行器始终能在非视距和天线不对准的情况下接收到短波信号，证实了短波应用于高速飞行器应急通信的可行性。试验是进一步验证高速飞行器在远距离、超视距以及拒止环境下应急通信的技术基础，同时，也为高速飞行器短波通信系统的研制提供重要的数据支撑。     

基于闭环解析解的可重复使用运载器轨迹在线生成方法

The relationships between path constraints such as heating rate, dynamic pressure and aerodynamic load and velocity during entry flight are analyzed in  r-V  plane for an entry vehicle with mediate high lift to drag ratio. Through derivation and integration, a unified formula for path constraints is obtained in  r-V  plane. Based on the unified formula and several characteristics an analytical solution is obtained,and an online trajectory generation method is developed. In the method, the coupled longitudinal and lateral motion is considered, and can make the best use of flight capability and satisfy path constraints. Trajectory generation cases with different flight mission and downranges are tested. Simulation results demonstrate the capability and efficiency of the trajectory planning method in dealing with path constraints.     

Shuttle avionics verification and integration testing

The Space Shuttle Orbiter employs a fly-by-wire control system of 200 major avionic hardware devices interfacing with five flight computers through a complex data bus system. Responses to man-in-the-loop commands are dependent on the flight software. Early program development testing of the computer and avionic hardware has been accomplished at Rockwell International's Shuttle Avionics Development Laboratory (ADL). Hardware development has led to complete multi-string system testing and flight software evaluations. This paper provides an overview of the ADL. Its role and test capabilities in support of Shuttle development are defined. The nature of computer driven test programs for the Orbiter displays, the Digital Autopilot, and flight software development describe the test bed provided by the ADL.