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<p>To improve the flight performance of a compound helicopter, the parameter optimization method based on the adaptive genetic algorithm is used. The flight performance model consists of a rotor model, a propeller model, a wing model, a vertical tail model and a horizontal tail model. The importance of the flight state is represented as weight factor in the objective function. Three different cases are analyzed, which highlight the performance at hover, medium-speed or high speed. The helicopter powers decrease by 34.3%, 25.0%, and 13.7% at 0, 200, and 400&#xa0;km/h in the case emphasizing hover, and the powers also decrease in the other two cases. At 0&#xa0;km/h, increasing the propeller radius, decreasing the propeller blade twist, and pitching up the fuselage help to reduce the propeller power and helicopter power. At 200&#xa0;km/h, to reduce the helicopter power, the fuselage should pitch up to a position where the negative thrust of the left propeller is near zero, which can effectively decrease the rotor-induced power and increase the rotor drag power. At 400&#xa0;km/h, in the case emphasizing high-speed, the rotor drag power is the highest and increases by 21.8%, due to the smallest wing area, the largest horizontal tail area, and the pitching up attitude of the fuselage. The parameter optimization method based on the adaptive genetic algorithms is an effective method in improving the flight performance of compound helicopters.</p>

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Parameter Optimization Based on Adaptive Genetic Algorithm to Improve the Flight Performance of a High-Speed Compound Helicopter

  • 期刊论文

  • 发表日期：

    2025年6月21日

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  • Yilan Zeng,
  • Dong Han,
  • Zhuangzhuang Liu

摘要

To improve the flight performance of a compound helicopter, the parameter optimization method based on the adaptive genetic algorithm is used. The flight performance model consists of a rotor model, a propeller model, a wing model, a vertical tail model and a horizontal tail model. The importance of the flight state is represented as weight factor in the objective function. Three different cases are analyzed, which highlight the performance at hover, medium-speed or high speed. The helicopter powers decrease by 34.3%, 25.0%, and 13.7% at 0, 200, and 400 km/h in the case emphasizing hover, and the powers also decrease in the other two cases. At 0 km/h, increasing the propeller radius, decreasing the propeller blade twist, and pitching up the fuselage help to reduce the propeller power and helicopter power. At 200 km/h, to reduce the helicopter power, the fuselage should pitch up to a position where the negative thrust of the left propeller is near zero, which can effectively decrease the rotor-induced power and increase the rotor drag power. At 400 km/h, in the case emphasizing high-speed, the rotor drag power is the highest and increases by 21.8%, due to the smallest wing area, the largest horizontal tail area, and the pitching up attitude of the fuselage. The parameter optimization method based on the adaptive genetic algorithms is an effective method in improving the flight performance of compound helicopters.