Abstract
In order to reduce the failure rate of Integrated Modular Avionics (IMA) partition software, due to the reliability block diagram (RBD) method, fault tree analysis (FTA) method and GO method cannot describe the state transition process of partition software, according to the ARINC 653 standard and the actual running status of the partition software, this paper determines the state machine and conversion delay of the partition software, and establishes the stochastic Petri nets (SPN) reliability quantitative model of the partition software. By proving that each transition in the SPN model of the partition software approximately obeying exponential distribution, and according to the reachable state tree of the SPN isomorphic to a homogeneous Markov chain (MC), the steady-state probability of the partition software in the fault state is calculated to be 5.2778*10 <sup xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">-9</sup> by using MC stochastic process theory. The factors affecting the reliability of the partition software are obtained, and the sensitivity of each factor to the model is studied. Finally, the relevant conclusions are drawn to provide guidance for improving the reliability of partition software.
Highlights
In order to further lighten the weight of the aircraft and reduce the operation cost of the entire life cycle of the aircraft, the guidance document RTCA DO-297 from the Radio Technical Commission for Aeronautics (RTCA) resides the originally independent physical equipment in the Integrated Modular Avionics (IMA) system in the form of software [1]
In order to be able to quantitatively evaluate the reliability of the partition software, we proved that each transition in the partition software stochastic Petri nets (SPN) model approximately obeys an exponential distribution
The IMA system is the future of the onboard avionics system
Summary
In order to further lighten the weight of the aircraft and reduce the operation cost of the entire life cycle of the aircraft, the guidance document RTCA DO-297 from the Radio Technical Commission for Aeronautics (RTCA) resides the originally independent physical equipment in the IMA system in the form of software [1]. This paper proposes a reliability modeling and quantitative analysis method based on SPN which is more in line with the running state of partition software by decomposing the interaction process and failure mode of partition software and according to ARINC 653 standard. According to the actual operating status of the partition software, this paper establishes the SPN reliability evaluation model of the partition software of the IMA system based on the partition software state machine defined by the ARINC 653 standard, and determines the trigger delay of each transition.
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