面向下一代运载火箭的综合电子系统集成技术

介绍了面向下一代运载火箭分布式模块化电子系统(DIMA)的集成技术及系统架构。针对下一代运载火箭复杂电子系统的特点，按照系统集成的路线，对系统设计目标、系统功能需求分析、系统抽象机制、系统综合技术等多方面进行论述。首先，根据电气系统功能获得系统需求，采用功能抽象和层次抽象定义系统抽象模型，提取出高内聚低耦合的原子功能模块，并对模块的属性、交换关系、时序约束关系等进行定义；然后采用可视化表征方法对系统进行深入分析，利用系统综合技术实现了从系统功能到硬件资源的映射，从而给出了集成控制单元和模块的种类；随后采用分时分区的设计理念对系统节点分区划分方案及容错架构进行了定义，并对分区操作系统的调度模型和交换式的数据交互网络进行了论述，最终给出了系统软硬件架构。

Integration Technology of Avionics for Next Generation Launch Vehicle

The system integration technology and architecture of the distributed integrated modular avionics (DIMA) for the next-generation launch vehicle is introduced in this paper. According to the system integration route, a lot of theses are discussed, including the goals of the system designation, system functional requirement analysis, system abstractions, system synthesis technology and so on. Firstly, the system requirement analysis is required in accordance with the avionics functions. In this step, two system abstraction technologies, functional abstraction and layered abstraction, are used to define the abstract system model and the high coherent, low coupling atomic function modules are extracted as a result, at the same time, the attributes, interactions and sequence constraints of these modules need to be defined. And then, the system visual presentation technology is mentioned and used to carry the deep system analysis out. In the next system synthesis process the function modules above can be mapped to the hardware resources, and the integrated control unit and its boards are presented accordingly. At last, the planning of the nodes and partitions, the blue print of the failure tolerance architecture based on the time and space partition technology (TSP) is defined, and the scheduling model of the TSP operating system and switched data interaction network is discussed as well, thus the software and hardware architecture is clear finally.