CUDA-інтеграція контурів керування авіаційного газотурбінного двигуна

The problem of accelerating the process designing aircraft gas turbine engines and their control systems, system "AIRCRAFT-AVIATION ENGINE-FUEL", forming technical type an engine, adapting to new operating conditions within framework experimental design bureaus (EDB) industry is using automated systems with low computing performance incomplete description. Information technologies for developing allow duplication mismatch data, loss information time during transmission processing making parametric structural decisions. To better adaptation characteristics aviation engine (AE) tasks solved by in flight, it necessary integrate systems. Integrated are especially effective managing today's multi-mode aircraft. On basis control, optimal programs power plant (PP) formed criteria evaluating effectiveness This article proposes a paradigm building integrated loops which can be automating processes, automatic system, combined programs. objective this research processes constructing adaptive engines. subject study embedded CUDA architecture. goal improve dynamic through loops, considering various flight modes modes. Objectives: determine main controllable elements adjustable parameters factors according principle adaptation; describe mechanism joint management engines; integration circuit "aircraft - plant" develop concept ACS; define parallel loops. Conclusions. scientific novelty lies formation models engines, different operation