The improvement of mission capability of remote sensing satellites has made it more demanding for the in-depth, detailed, and intensive design. It is required that the ultimate goal of system performance should be carried out around the mission capability, which results in significant changes in product integration and verification pattern. This paper firstly introduces the concept and requirements of multi-disciplinary integrated design method, and then presents the key issues of the method in worldwide developments and applications. Finally, the practice in integrated collaborative analysis platform establishment is demonstrated, and the simulation verification is conducted and summarized.
In recent years, Model-Based Systems Engineering (MBSE) is rising rapidly in Systems Engineering (SE) field. The process of MBSE adoption for cabin temperature control system design of Civil Aircraft is described. The temperature control system model consists of a discrete model and a continuum model, which are built respectively. And the discrete model is built by Systems Modeling Language (SysML), a graphical modeling language. A method for MBSE, MagicGrid, is employed during the establishment of the discrete model, which includes requirements analysis, function analysis, and system architecture analysis. The FMI-based co-simulation of discrete model and continuum model are carried out to integrate the two models to support model verification, validation and iteration.
A system of systems (SoS) is a set of systems where independent systems are integrated into a larger system that delivers unique capabilities. With the increasing numbers of system elements and interactions within a system, the complexity of SoS increases significantly. Thus, SoS modeling is becoming fairly difficult and important as well. Traditional strategies fail to manage the complexities in SoS leading to inconsistent and incomplete analyses. Thus, this paper proposed an SoS modeling case study on the Air Traffic Management system (ATM) with UPDM, a unified profile to model enterprise architectures from capabilities to components. From the Operational View, capabilities and missions are studied to determine what the SoS should be done, which further motivates the System View analysis. From the System View, more detailed analyses are conducted by decomposing SoS into elements to investigate the functions, operations, and interactions. By iterative analyses and simulation, models are consistent, verifiable, and traceable leading to better SoS modeling and engineering.
It has been a trend that the Integrated Modular Avionics (IMA) systems use more and more open system architecture, and more functions are integrated. The high coupling between modules resulting in a dramatic increase in the complexity of the system, which would result in safety issues due to the complex interactions. When the system is reconstructed, the complexity of system management is increased because of the increase of reconfiguration scope and the large increase of system state space. In this paper, what we need to do now is to decompose the dynamic reconfiguration process into a few of steps of the conversion process in the system modal, and to complete the analysis of the reliability of the system for each task, which is, task reliability. In this paper, each dynamic reconfiguration process can be decomposed into several tasks, of which the reliabilities are analyzed at the first. After all the tasks are proposed that may happen during the process, the reliabilities of components that are analyzed which are required to complete the tasks, and the reliability of each task could be calculated with those parts. Then, the reliability of the reconfiguration process is calculated by the tasks in series, as well as in the parallel case. Based on Petri net translated by AADL model, the IMA dynamic reconfiguration process tasks’ reliability calculation is established. Adding the required components with their reliability attributes of each sub-state task to the model, by which the original dynamic reconfiguration process model would be enriched. It will be a great usage in analyzing the safety of dynamic reconfiguration in IMA system.
In the development of the embedded real-time operating system which follows ARINC653 (Standard Interface of Avionics Application Software), the partition protection and address translation algorithm of the memory management unit based on PowerPC E200 processor is proposed and formally verified. Using the interactive theorem proving tool Coq, firstly, address translation is formally modeled. Secondly, the three requirements that the algorithm must meet are expressed in the form of theorems. Finally, the strategies and construction methods of the tool are used to prove the correctness of the algorithm. The algorithm verification results show that the formal method theoretically guarantees the correctness of the key algorithm of the operating system, overcomes the incompleteness of the traditional test methods, and provides a strong guarantee for the development of high-quality safety critical software.
