Abstract
Cockpit temperature control system is an important part of the environment control system (ECS) which will directly impact the health and comfort of the pilot. This investigation built the physical model for the cockpit temperature control system of one real aircraft in commercial software, Matlab Simulink. Experimental data of the aircraft cockpit rapid cooling test was used to verify the model. The simulated cockpit temperature curve agrees with the experimental data. The verified model was then used to implement the control logic design based on both PID and cascade control theory. The comparison of these two control logic shows that cascade-PID has a better dynamic response when controlling the cockpit temperature of aircraft with a lower overshoot of 0.12 °C and a shorter settling time of 48 s. The results also show that during a rapid cooling condition, control logic has no impact on the variation trend of cockpit temperature.
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Liu, Y., Wu, C., Min, Z., Zhang, X. (2020). Control Logic Design Based on Modeling of Aircraft Cockpit Temperature Control System. In: Long, S., Dhillon, B. (eds) Man–Machine–Environment System Engineering . MMESE 2019. Lecture Notes in Electrical Engineering, vol 576. Springer, Singapore. https://doi.org/10.1007/978-981-13-8779-1_50
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DOI: https://doi.org/10.1007/978-981-13-8779-1_50
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