The aeronautical digital space, oriented towards the aviation domain, focuses on key technologies such as pan-spatial data modeling, spatial analysis and computation, and visual representation to build a digital twin spatial foundation for aviation. This enables the representation of spatial objects such as environments, physical entities, and behaviors. Aligning with the trends in intelligent algorithms and visual representation technologies, Aviation Digital Space holds future potential for applications in numerous scenarios, including navigation visualization, low-altitude economy, and intelligence processing.
开放式系统架构航电系统中的机载计算平台需要提供高性能共享软硬件资源,包括通用数据处理资源、信号处理资源、图像处理资源、并行计算处理资源、网络传输资源、大容量存储资源等.为满足机载计算平台多种资源组合的需求,开展了多用途计算平台的设计,该设计参考VITA系列规范,通过CPU、GPU、FPGA等COTS器件的灵活使用来满足多种功能资源的需求.
本文主要对综合射频信号处理平台中一种多功能核心板卡的主备切换方法进行了分析与设计.从平台架构出发,通过对主备切换的触发条件、涉及的功能以及切换所需的关键技术点进行分析,详细论证了进行主备切换时的技术需求、操作逻辑、关键技术点,并完成了相应的方案设计及测试验证.
本文从民用机载系统集成方角度,提出了一种商用货架产品操作系统型号项目应用中的适航符合性方法:作为具体型号项目的产品组成部分,建议集成方采用商用货架产品操作系统评估、筛选以及设计迭代的方式,确保商用货架产品操作系统满足预期功能和型号审定的需要.该方法意图为民用机载系统集成方开展产品研制、为局方确定相关适航符合性提供参考和借鉴;也可作为商用货架产品操作系统供应商开发适合航电应用新产品的研发考虑.
针对多机分布式体系化协同作战中航电系统资源分散、能力嬗变等特点,研究基于软件定义的系统资源即插即用技术,建立网络化资源接入拓扑结构模型,提出资源抽象与封装、注册、发布和动态管理方法.在此基础上,构建面向有人机/无人机协同的资源接入仿真系统,验证了多平台航电系统资源灵活接入及即插即用能力.
针对当前民机研发过程对系统工程与过程方法理解和运用仍然存在疑虑的问题,本文选择以面向对象的方式观察和分析了项目实践中的航电系统工程及其过程方法,利用系统建模语言建立了一组系统工程与过程的对象模型,以可视化方式展示了抽象层面上系统工程的结构和行为以及它们之间的联系.清晰的模型有利于人们更好地理解和交流,本文重点介绍了如何把经验中的过程方法用对象模型进行表达的方法.文中模型包括系统工程的用例、生命周期、过程规范、系统工程与项目以及系统工程类的操作等.模型是对现实的简化和抽象,对系统工程与过程的本身建模是一次尝试,旨在为民机航电系统产品的开发与体系建设提供理论和实践方面的指导.
美国防部制定的"模块化开放式系统方法"是一种装备采办的总体战略.该方法通过对关键接口定义、系统模块化设计等架构方面的指导,可帮助装备开发中互操作性提升、技术迭代加快、成本降低等目标的实现.美国防部规定2019年以后研发的装备系统必须满足"模块化开放式系统方法".本文从面向要素维度和面向流程角色维度出发,梳理了符合"模块化开放式系统方法"装备架构开发的一些实践.在此基础上对"模块化开放式系统方法"的应用现状和趋势进行了分析及展望.
为了降低装备在整体生命周期的成本,并获得更频繁地升级现有和新型武器系统的能力,美国国防部要求使用开放式系统架构,并已完成许多开放系统架构标准的制定工作.本文将在介绍航空电子领域典型的开放系统架构标准内容、发展状态及商业策略的基础上,对各个标准加以梳理和比较,总结不同开放式架构标准整合情况下可能遇到的问题并给出解决原则;最后,对开放式系统架构标准在新一代航空电子系统中的应用进行展望.
随着软件规模的增长和开发过程的复杂化,定量管理已经成为软件开发过程中不可或缺的一环.本文设计并实现了一个支持GJB5000B四级的软件定量管理系统,该系统通过项目的历史数据,进行相关性分析、回归分析、性能分析,提供可视化的参数配置和结果图表显示.本文详细介绍了系统的设计思路、技术选型以及实现过程,并进行了实验和结果分析.实验结果表明,该系统可以有效地帮助开发团队进行软件定量管理,提高软件开发的质量和效率.
针对需求开发活动中存在的常见问题,将功能点识别方法应用于需求分析过程,从度量软件提供给用户的功能角度进行软件需求分析,并以某软件为例,以软件功能点模型作为约束标准,形成了标准、规范的软件需求规格说明,有效控制了软件需求的边界,亦辅助保证了需求的完整性等要求.
介绍了一种基于GIS的多源数据快速可视化软件设计与实现.在多源数据可视化软件系统设计中,为解决海量多源目标快速显示,辅助用户分析决策,无人机实时探测展示,本文采用了 Canvas绘制、轨迹实时推算技术,提出了软件实现方案,设计了软件架构,实现了软件原型系统.最后利用工具软件测试了原型系统软件显示性能,验证了软件稳定性和响应速度要求.
As a new high-availability data distribution specification in non-deterministic networks, DDS proposes the concept of global data space and communicates through a publish-subscribe mechanism. It is said that DDS is tightly packaged, and many processes considered as black box process to the applications, and it is difficult to accurately grasp the process, and it is difficult to locate and troubleshoot once abnormalities and faults occur. Avionics Ethernet is taken as an example to study the DDS publish-subscribe process and communication behavior in detail, and an example of fault research and troubleshooting is used to illustrate the specific process and logic of DDS publish-subscribe mechanism. And the communication behavior of DDS at Ethernet protocol layer and application layer is studied.
Aiming at the problem that test tool TestBed cannot dynamically implement unit testing of QT program, introduces the definition of unit testing and the principle of unit testing and TestBed tool are introduced, and the problems of unit testing of QT program by TestBed tool are pointed out, then a method that combines TestBed and Visual Studio to do unit testing of QT program is proposed, and detailed steps of design and implementation and a simple implementation method for unit testing of QT program are described. As the result of practical application, the method combining TestBed and Visual Studio in unit testing of QT program improves the efficiency of unit testing, decreases cost of unit testing.
Configuration Management is one of the most important functions to improve aircraft safety. Due to the architecture characteristics of the integrated modular avionics system, configuration management should not only ensure the consistency of software and hardware configuration, but also take configuration data into account. After analyzing the configuration management function design requirements defined by DO-297, the configuration management function is divided into three steps of configuration data generation, data loading and compatibility check according to the function characteristics of different configuration data, and their specific design solutions are described in detail. This whole solution has been successfully applied in the project.
A design method of general vibration tooling based on finite element simulation is proposed, and the design of a mobile general-purpose vibration tooling is completed according to the environmental test requirements for a certain series of avionics products. Data modal analysis and random vibration analysis as well as random vibration analysis for the design plan have been carried out to optimize and improve the tooling based on the simulation results,and a physical prototype have been manufactured to carry out environmental tests. The experiments prove that the error between the experiments result and the data analysis result of the vibration tool’s natural frequency is 6% with sound vibration transmission characteristics. This portable general-purpose vibration tooling can be used in environmental experiments of serialized avionics products to avoid the repetitive work of design and manufacturing, and has good promotion applicability. The design method enriches the traditional design route of vibration tooling, improves the quality of tooling design, and directly guarantees the effectiveness and compliance of product experiments.
To increase the transmission rate and improve the redundancy structure design of the new generation Avionics Full-Duplex Switched Ethernet（AFDX） network, a formal modeling of the frame management mechanism of the gigabit triple redundancy AFDX is established based on the AFDX network standard（ARINC 664 p7）and the SkewMax mechanism described in the AFDX network standard is implemented. The availability of the integrity check and redundancy management functions is verified by UPPAAL formal tool. The verification results show that there is no deadlock in the frame transmission process in this design. The AFDX design document mentions that the loss of a frame in redundancy management may lead to the loss of its redundant backup. For this, a queue is recommended to be setup at the receiving end-system to record those frame sequence numbers of redundant backup frames that arrive later than consecutive frames, thereby reducing unnecessary frame retransmission and improving QoS and data integrity. The results of formal verification can be used as a reference for the formulation and practical application of gigabit AFDX network standards.
Flight management system is the key avionics system of civil aircraft. Manufacturers of flight management systems are responsible for conducting extensive testing of flight management systems to verify compliance with their functions and performance. Taking into consideration the limit of digital validation and the huge cost of test validation,validation of the integrated navigation function of the flight management system is carried out using the vehicle platform. The test results show that the developed flight management system DR/GPS navigation can meet 95% of the flight time to achieve 0.1 nautical mile navigation accuracy requirement in horizontal direction. It provides reference for actual flight test.
The Data Load System of Ground Control Station（GCS） lacks standards at present, and the GCS software architect is complex and the software scale is huge. Therefore, a standard Data Load Protocol is needed to ensure the safety and efficiency of the GCS Data Load System. Based on the in-depth study of the ARINC 615A protocol and according to the actual situation of GCS, the ARINC 615A protocol is tailored and optimized, and a Data Load Protocol suitable for GCS is designed, which is used to ensure the GCS Data Load System more standard, safe and efficient.
Aiming at the typical functional hazard scenarios and architecture design process of TCAS system operation process, aforward design process method of system engineering processa fault detection and fault tolerance design technology is performed on theresearch of TCAS system domain in view of the potential functional failure risk, and a fault detection and isolation architecture design scheme is designedto cover the system software and hardware design levels,so as to improve the creditof anti-collision alarm during installation and operation, and to reduce the impact of flight safety due to missed alarm and false alarm.
To meet the safety requirements of airborne data in complex battlefield situations, it is necessary to establish an effective evaluation method of destroyed key ability of aviation memory card. The purpose of establishing the effectiveness evaluation of destroyed key ability is to ensure the information security of aviation equipment. It is of great significance to scientifically and accurately evaluate whether the destroyed key design meets the requirements. It is also a necessary information security evaluation process before aviation equipment finalization. The typical structure and the hardware destroyed key principle of aviation memory card are analyzed. By studying electrics, physics and chemistry analysis methods behind hardware destroyed key, an evaluation method for the destroyed key ability of aviation memory cards is proposed. The destroyed key effect is evaluated from the readability of the aviation memory card and the damage status of the storage medium. It standardizes the current situation that there is no unified method for the evaluation of the destroyed key ability by the evaluation organization. The effectiveness of the evaluation method is verified through practical application in analyzing the destroyed key effect of an aviation memory card after the hardware destroyed key experiment.
