共查询到20条相似文献,搜索用时 31 毫秒
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Time-triggered (TT) embedded software pattern is well accepted in aerospace industry for its high reliability. Fi-nite-state-machine (FSM) design method is widely used for its high efficiency and predictable behavior. In this paper, the time-triggered and state-machine combination software architecture is implemented for a 25 kg thrust micro turbine engine (MTE) used for unmanned aerial vehicle (UAV) system; also model-based-design development workflow for airworthiness software directive DO-178B is utilized. Experimental results show that time-triggered state-machine software architecture and development method could shorten the system development time, reduce the system test cost and make the turbine engine easily comply with the airworthiness rules. 相似文献
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航天智能控制技术让运载火箭“会学习” 总被引:2,自引:0,他引:2
高可靠和智能化是未来智能航天器的主要特点,本文聚焦航天器高可靠、智能化的发展需求。梳理了中国运载火箭从无到有、从有到全的发展历程,提出了航天智能技术从航天器的可靠性做起,航天器的可靠性从航天智能控制做起,航天智能控制从"会学习"的火箭做起。围绕航天智能控制技术如何使运载火箭"会学习"的发展架构,进一步探索了"边飞边学"和"终身学习"智能控制技术的理论研究和应用现状,支撑中国"会学习"运载火箭高可靠和智能化的发展。 相似文献
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基于对多种软件可靠性模型的分析,并结合工程软件之特点,提出一种工程软件适用的可靠性定量评估方法,并将其应用于某航天工程软件的可靠性评估。实践表明,本方法简单、可行,对其它领域的软件可靠性评估同样具有参考价值。 相似文献
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测试复用技术是提高软件测试效率和质量的重要技术手段,在分析航天测控软件行为模式的基础上提出了基于数据操作的航天测控软件测试复用模型,给出了测试用例搜索和匹配算法;以航天测控外测数据处理软件的可靠性测试为例给出了模型的具体应用。结果表明,基于给定模型的测试复用方法可提供该软件约65%的测试用例,有效提高了测试效率,所提出的模型和方法对专业领域软件测试效率和质量的提高具有一定的借鉴意义。 相似文献
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复杂系统可靠度综合计算平台的设计实现 总被引:1,自引:0,他引:1
鉴于复杂大系统可靠度综合计算面临诸多困难 ,分析了其复杂性特征 ,提出了一种一体化建模方法———复合逻辑树模型 (CompositeLogicTreeModel,简称CLTM)及其递归调度综合算法 ,并采用面向对象的思想和技术 ,设计实现了可视化的系统可靠度CLTM综合建模与计算软件平台。介绍了软件的总体框架及其功能 ,并通过实例阐明了相应的系统可靠度综合分析方法 相似文献
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Review of uncertainty-based multidisciplinary design optimization methods for aerospace vehicles 总被引:3,自引:0,他引:3
Wen Yao Xiaoqian Chen Wencai Luo Michel van Tooren Jian Guo 《Progress in Aerospace Sciences》2011,47(6):450-479
This paper presents a comprehensive review of Uncertainty-Based Multidisciplinary Design Optimization (UMDO) theory and the state of the art in UMDO methods for aerospace vehicles. UMDO has been widely acknowledged as an advanced methodology to address competing objectives of aerospace vehicle design, such as performance, cost, reliability and robustness. However the major challenges of UMDO, namely the computational complexity and organizational complexity caused by both time-consuming disciplinary analysis models and UMDO algorithms, still greatly hamper its application in aerospace engineering. In recent years there is a surge of research in this field aiming at solving these problems. The purpose of this paper is to review these existing approaches systematically, highlight research challenges and opportunities, and help guide future efforts. Firstly, the UMDO theory preliminaries are introduced to clarify the basic UMDO concepts and mathematical formulations, as well as provide a panoramic view of the general UMDO solving process. Then following the UMDO solving process, research progress of each key step is separately surveyed and discussed, specifically including uncertainty modeling, uncertainty propagation and analysis, optimization under uncertainty, and UMDO procedure. Finally some conclusions are given, and future research trends and prospects are discussed. 相似文献
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为了提高运动机构的稳定度,步进电机驱动控制通常采用电流细分的方法,从而将一个步距角分解成若干小步。实现步进电机电流细分驱动通常的方法是将电流闭环引入到驱动控制电路中,由此增加电流采样、比较等软硬件功能模块的同时也增加了单机的复杂度,削弱了步进电机本质上开环驱动的优势。为了提高宇航型号步进电机驱动控制器单机的可靠度,提出了一种基于反熔丝FPGA的纯开环驱动方案,通过预置占空比的方式,在不引入电流闭环的前提下实现步进电机电流细分。通过样机调试,验证了设计的有效性,为后续工程研制提供参考。 相似文献
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航天电磁继电器可靠性容差分析技术的研究 总被引:4,自引:0,他引:4
航天电磁继电器是在航天电子系统中完成信号传递、执行控制、系统配电等功能的主要电子元器件之一,其可靠性直接影响整个航天电子系统的可靠性。航天继电器可靠性设计技术是其产品可靠性工程的关键技术。本文分析了当前各领域可靠性研究现状及航天电磁继电器产品的可靠性现状与问题,提出并建立了基于正交试验表的电磁吸力可靠性容差分析数学模型、基于概率统计方法的机械反力可靠性容差分析数学模型及基于“应力-强度干涉法”的吸反力配合特性可靠性容差分析数学模型。以某型号航天电磁继电器为例,进行了可靠性容差分析与研究,给出了对航天电磁继电器可靠性设计具有指导作用的重要结论。 相似文献
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Phased-Mission Systems(PMS) are widely applied in aerospace, telecommunication and intelligent systems for multiple, consecutive and non-overlapping phases of missions. The phasedependent stresses and system structure cause some difficulties to the reliability analysis of PMSs.In this paper, we analyze the physical isolation effects on the degradation speeds and across-phase damage accumulations of failure mechanisms. And, some corresponding reliability and unreliability formulas are derived. Be... 相似文献
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空气动力评估是对飞行器进行全过程、全系统试验与鉴定的重要内容.依据层次分析原理,可分层、分类对飞行器的空气动力特性进行综合评估.采用专家调查法,获得专家个体对评估因素、评估因素的权重、以及评估结果等级与档次的意见;采用综合评估方法综合各专家个体的意见,获得对飞行器空气动力特性综合评估的定性结论和定量结果. 相似文献
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软件可靠性增长测试的研究 总被引:2,自引:1,他引:1
研究、探讨了软件可靠性增长测试的基本概念及其实施过程中的若干问题,按照实际运行剖面选取测试用例、软件可靠性增长预计,以及正确收集故障数据的问题。 相似文献
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Xiangpeng Li Yongsheng Wang Lu Gao 《Aerospace and Electronic Systems Magazine, IEEE》1996,11(7):35-38
In this paper, the advantages and development of GPS applied in a space vehicle are introduced first. Then, the software employed to calculate the applied altitude of GPS in a space vehicle is explained. The detailed software flowchart is also given, and the process of choosing used GPS satellites is described in detail. In order to study the receiving condition in a space vehicle, we also make a simulating calculation with our software. The results of receiving GPS satellites over a certain place are given. The paper has not only the value for using GPS in a space vehicle, but also the significance for an aircraft whose navigation system is GPS 相似文献
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闭环上升制导是吸气式空天飞行器达到快速优化、实时规划以及自主制导的必然要求。采用GHAME吸气式空天飞行器作为研究对象,提出了闭环上升制导最优控制方案,重点论证了该方案不存在关于节流阀值的奇异问题,并阐述了最优推力控制的Bang-Bang控制。引入有限差分法求解两点边值问题,并通过终端时刻调节算法求解终端时刻自由问题。仿真结果表明,所提出的闭环制导算法是有效、可行的,具有显著的优越性。 相似文献
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军用软件可靠性策略研究 总被引:3,自引:0,他引:3
在分析影响军用软件可靠性因素的基础上,借鉴能力成熟度模型(CMM)过程规范思想,提出了一套完整的军用软件可靠性解决策略,包括软件可靠性组织过程、软件可靠性管理过程、软件可靠性工程过程和软件可靠性支持过程,并概要描述了各个过程所涉及的技术和实现方法。 相似文献
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《Aerospace Science and Technology》2007,11(2-3):238-244
The aerospace launch vehicle, developed today by manufacturers, is characterized by high nonlinearity, open loop instability and time-varying behaviors. The transfer functions of the vehicle can be extracted using well-known linearization methodology. This paper presents an alternative to obtain the transfer functions via closed-loop identification using six degrees of freedom nonlinear simulation software. The pitch program is taken into account as the external excitation. Control and stability of the process are performed using robust PID controller. The model structure with some unknown parameters is obtained after mathematical modeling, thus the case of our problem is a parameter identification one. Time-variant parameters are estimated by Kalman filter approach with the aid of ARX model structure. 相似文献
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The application of digital onboard computers for flight control of high-performance aerospace vehicles is desirable, with respect to hardware effort and reliability, as well as operational flexibility. Up to now, digital computers have not been used for the control of short periodic angular oscillations. This task can be solved with the capability of digital computers now available. A good vehicle for the realization of appropriate control equations is the ?frequency transformation?. Using the simplified dynamics of a supersonic aircraft as an example, a procedure for synthesis of a digital control filter is presented. After a first evaluation in the s domain, the design is checked for validity in the frequency domain. If necessary, the original design is corrected appropriately. 相似文献