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李涛 《民用飞机设计与研究》2020,(2):97-102
在民用飞机型号合格适航取证过程中,申请方需要开展符合性验证试验、试飞、分析等符合性验证活动来证明飞机型号设计符合相应的型号合格审定基础,以获得适航当局颁发的型号合格证。在此过程中,需要将符合性验证活动分解为便于管理的任务,使这些任务得以合理、有序地完成,这类分解后的符合性验证活动的载体就是一份份型号合格审定计划。审定计划是民用飞机型号合格取证的关键工具,它提供了详细的产品描述和成功完成取证的工作要求。分析了审定计划的适航规章要求和行业标准要求以及两者之间的异同,结合国内民用飞机型号的适航取证经验,提出了审定计划的规划原则、内容要求和协调性检查要求,为国内民用飞机型号合格审定计划的规划和制定提供参考。 相似文献
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卡曼与洛克希德.马丁公司(K-MAX小组)已经通过视线和基于人造卫星的视线数据链,进行卡曼无人机K-MAX自主及遥控飞行执行士兵货物运输再补给任务的能力论证。这项试验在位于犹他州的美国陆军Dugway基地完成,0℃以下的气候与阿富汗前线的战场环境相似。此项试验获得海军陆战队资助。洛克希德.马丁公司航空系统副总裁丹.斯普尔在纽约任务系统传感器工厂说:“在为期3天的验证计划中,我们达到甚至超过了要求。该系统按照计划完成了一项严峻的货物再补给任务,地面操作人员全程监控并只在海军陆战队提出要求时才对直升机定位进行调整。”验证的性能包括:在12000英尺高度携带1500磅吊挂载荷悬停;在6小时内完成两次150海里往返飞行,为前方作战基地运输3000磅货物;由地面操作员遥控进行昼夜的飞行及货物精确投放;飞行中向直升机任务管理系统加载新的任务计划。该项计划还验证了直升机的4吊钩吊盘,能够在单次飞行中运载多种货物,总吊载3450磅。直升机进行了3次预编程的运输飞行,并在每个预定位置自主投放。应海军陆战队的要求,由地面控制人员人工进行第4次投放。从2007年起K-MAX无人机在无人模式下完成了近400小时的飞行。该项验证花费了... 相似文献
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喷气推进实验室 (JPL)的深空任务系统给大量的深空任务提供了跟踪、遥测和遥控 (TT&C)服务。深空网 (DSN)中的TT&C设备正在进行大范围的升级和技术改造 ,升级改造完成后系统性能将更强大 ,并实现数据存取和交互支持的接口标准化。网络简化计划 (NSP)作为改造任务的一部分 ,已经对TT&C的结构和实现进行了重新审查。目前的TT&C功能是通过六个不同的子系统来实现的 ,每个子系统都有各自独立的控制单元 ,这些控制单元的设计没有考虑到不同功能之间的相互作用。NSP正在实现遥测和遥控设备的现代化 ,并重新设计测距处理程序以及跟踪数据… 相似文献
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基于航天器控制语言的东三平台卫星遥控作业设计与实现 总被引:1,自引:0,他引:1
针对东三平台卫星的飞行任务要求,分析了地面测控系统和卫星飞行程序,提出了遥控作业的数据接口及设计原则,并通过作业例程验证了该设计方法。利用该方法设计的系列遥控作业目前已应用在东三平台卫星的测控工程中。 相似文献
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本文概述了缩比为28%、遥控X-36飞机的技术验证方法,特别是对达到验证目的减少费用的那些决策。介绍了由此而引起的飞机、地面站和试验的方案。评审了X-36的试验计划,重点集中在允许快速的系统验证和包线扩展的试验技术上。最后讨论了试验计划的结果及其对研究机未来的影响。评审了遥控飞机优缺点。讨论了所选择的设计、研制和验证的工具。评价了试飞中使用的新技术及仍然使用的老经验。 相似文献
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基于NuSMV的AADL模型形式化验证技术 总被引:1,自引:0,他引:1
结构分析描述语言(AADL)是一种描述任务关键嵌入式系统架构和行为的建模语言,在航空航天领域广泛被应用。为验证AADL模型的任务关键属性和系统行为的正确性,提出基于NuSMV(新符号模型检查器)的AADL模型形式化验证方法。首先,覆盖AADL模型的所有软件构件和行为特征,提出了AADL模型到NuSMV模型的映射规则和转换算法;其次,采用图同构方法分析了转换算法的正确性;然后,在NuSMV模型中采用时态逻辑公式对AADL模型中待验证属性进行描述,以验证AADL模型中安全性、活性和嵌套模态配置的正确性;最后,以飞行控制系统为例,详细阐释了基于NuSMV的AADL模型形式化验证方法,并给出验证属性的统计信息。 相似文献
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航空电子系统综合技术分析 总被引:5,自引:0,他引:5
系统综合是指将机载电子设备综合成以作战、飞行功能为核心的统一控制、管理和显示的系统,这样可以提高系统自动化和智能化的程度,最大限度的发挥载机的战斗效能。本文对系统综合模式、设计方法、作战效能、故障诊断等诸方面进行了论述,并介绍了航电系统的综合试验和试飞评定系统的软件功能。 相似文献
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Lyshevski S.E. Skormin V.A. Colgren R.D. 《IEEE transactions on aerospace and electronic systems》2002,38(1):174-182
Electro-mechanical flight actuators (EMFAs) are core flight-critical vehicle components. Fly-by-wire or fly-by-light control of EMFAs is performed by flight management systems (flight, mission, propulsion, and integrated controls that manage any combination of specific flight, mission, and propulsion functions). Reported here are novel results in the analysis of EMFAs with permanent-magnet synchronous motors, with particular interest in the application of brushless high-torque density motors which have superior characteristics compared with other state-of-the-art motor technologies. It is shown that due to nonlinearities and bounds, new control algorithms must be developed and implemented to achieve a spectrum of performance and requirements for EMFAs. A number of important issues in control, analysis, model development, integration, and verification are studied. Tracking control algorithms are synthesized, stability studied, and novel analysis results are reported. Advanced computer-aided engineering software tools and emerging simulation-based design environments are used to guarantee high fidelity modeling and analysis within data intensive simulation. Proof-of-concept demonstration testbeds for the design of advanced EMFAs and their components are developed, and EMFA imitator performance thoroughly studied. Verification of the concepts reported are formed and documented. Precise tracking, disturbance attenuation, accuracy, stability, robustness, and excellent acceleration capabilities are reported. A demonstration is performed to substantiate the theoretical analyses to add credence to its applicability as an approach and method that the designer of future EMFAs can use to design a new class of actuators for aircraft flight control surfaces 相似文献
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Ivanka Pelivan 《Space Science Reviews》2010,151(1-3):5-23
A generic drag-free simulator has been developed to aid in the design, on-orbit and post-mission data analysis phases of increasingly complex future missions such as Gaia and STEP. Adaptation to the recent science mission Gravity Probe B (GP-B) has been carried out for a first simulator verification with actual flight data. Lessons learned from GP-B have shown that the controls simulator, developed concurrently with GP-B, has been invaluable to test flight control design and furthermore to resolve on-orbit anomalies in a time-saving manner. A complete mission software simulator including controls, full-body dynamics and comprehensive spacecraft environment disturbances has been established for Gravity Probe B. This simulator provides a reference and development platform for future mission design. The importance of this effort lies in the challenge to meet rising science requirements for future missions in the area of maximum disturbance rejection. 相似文献
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《中国航空学报》2020,33(7):2002-2013
For different flight phases in an overall flight mission, different control and allocation preferences should be pursued considering lift, drag or maneuverability characteristics. The multi-objective flight control allocation problem for a multi-phase flight mission is studied. For an overall flight mission, different flight phases namely climbing, cruise, maneuver and gliding phases are defined. Firstly, a multi-objective control allocation problem considering drag, lift or control energy preference is constructed. Secondly, considering different control preferences at different flight phases, the analytic hierarchical process method is used to construct a comprehensive performance index from different objectives such as lift or drag preferences. The active set based dynamic programming optimization method is used to solve the real-time optimization problem. For the validation, the Innovative Control Effector (ICE) tailless aircraft nonlinear model and the angular acceleration measurements based adaptive Incremental Backstepping (IBKS) are used to construct the validation platform. Finally, an overall flight mission is simulated to demonstrate the efficiency of the proposed multi-phase and multi-objective flight control allocation method. The results show that the comprehensive performance index for different phases, which are determined from the Analytic Hierarchy Process (AHP) method, can suitably satisfy the preference requirements for different flight phases. 相似文献
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随着国内军用飞机的技术发展,飞控系统的复杂程度呈指数级上升,这对原有的飞控系统试验验证体系提出了巨大挑战。按照飞控系统设计原则和先进飞机飞控系统验证技术特点,创新构建基于飞控系统综合试验平台的快速验证技术体系,建立参试设备的统一描述框架,通过信号转接技术实现试验过程的自动控制,基于试验任务对环境设备自动识别与配置,实现试验流程的自动化管理与控制,最终将基于飞控系统的可靠性物理验证转变为基于飞控系统试验任务的快速验证。经验证,该技术平均缩短验证周期50%以上。研究结果对提高飞控系统综合试验效率、实现试验环境的柔性配置,具有一定的参考意义。 相似文献
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先进重构飞行控制技术和方法研究 总被引:3,自引:0,他引:3
重构飞行控制技术本质上是一种容错飞行控制技术,它使飞控系统具有适应未知故障和损伤的能力,从而可以有效地提高安全性和任务效能。先进重构飞行控制技术在原有的基础上更加强调自适应的能力,而不再依赖故障诊断和隔离(FDI)系统,因而促进了鲁棒控制、智能控制和逢适应控制技术在该领域的交叉和融合。首先回顾了重构飞行控制技术的发展现状,然后给出了几种先进重构控制方法,并总结了先进重构飞行控制技术的主要技术优势,最后展望了它的发展趋势和应用前景。 相似文献
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This paper studies on a division method of the whole aeroengine loading spectrum flight mission segment and rotor speed mission segment, which is based on the actual flight actions and related to the flight operations of aeroengine and is suitable for the variable-speed aeroengines such as turbojet and turbofan. Through the research, the aeroengine loading spectrum operation-related mission segments can be divided, which can provide important data basis for the life research on the structures wh... 相似文献
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