ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Optimization of climb trajectory of combined-cycle engine powered aircraft based on improved CSO-Gauss pseudospectral method
Received date: 2024-05-27
Revised date: 2024-07-02
Accepted date: 2024-07-29
Online published: 2024-08-10
Supported by
Fundamental Research Funds for Central Universities(YWF-23-SDHK-L-005);Aeronautical Science Foundation of China(20220048051001);1912 Project
Combined-cycle engine powered aircraft has high percentage of fuel consumption during the climb phase， and its safety during power mode switching and choice of switching time require urgent attention. Therefore， optimization of the climb trajectory is of great importance for the combined-cycle engine powered aircraft. However， the challenges of model nonlinearity， non-convex constraints and strong aircraft-engine coupling make the problem difficult to solve. Firstly， a combined-cycle engine powered aircraft model that represents the characteristic of aircraft-engine coupling is established. Secondly， to solve the problem efficiently， the updating rules of the Chicken Swarm Optimization （CSO） are improved. Then， the CSO is fused with the Gauss pseudospectral method to form a hybrid optimization algorithm. Finally， a correlation analysis between the fuel consumption during the climb phase and the key parameters of the aircraft is performed. The simulation results show that the improved CSO-Gauss pseudospectral method achieves lower fuel consumption than either the CSO or the Gauss pseudospectral method. In addition， the fuel consumption of the proposed model during the climb phase is negatively correlated with the lift-to-drag ratio of the aircraft， and the selection of the power mode switching point also has a significant effect on the fuel consumption but does not show monotonicity.
Yousheng WANG , Liguo SUN , Jinpeng WEI , Wenqian TAN , Yonghao PAN . Optimization of climb trajectory of combined-cycle engine powered aircraft based on improved CSO-Gauss pseudospectral method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2025 , 46(2) : 230737 -230737 . DOI: 10.7527/S1000-6893.2024.30737
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