Study on optimum calculation model optimization for obstacle limited weight of domestic civil transport aircraft

Abstract

The performance software of a domestic civil aircraft used by an airline for many years can obtain satisfactory results in the accuracy of obstacle limited weight calculation, but the calculation time is long. The optimization model is established by comparing the calculation results and efficiency of the two models of the minimum acceleration height method and the maximum acceleration height method. The obstacle limited weight, acceleration height and calculation time of the two models under different obstacles and different wind speeds are calculated and analyzed. The results show that the calculation results of obstacle limited weight and acceleration height of the two models are basically the same; When there is no obstacle, whether there is wind or not, the calculation time can be reduced by 25% using the optimization model with the minimum acceleration height compared with the original model with the maximum acceleration height; When there are obstacles and there is no wind, the calculation time can be reduced by more than 78% by using the optimization model with minimum acceleration height,and when there is wind, the calculation time can be reduced by more than 75%. The model with the minimum acceleration height can take account of both accuracy and efficiency.

Keywords

• civil transport aircraft
• obstacle limited takeoff weight
• calculation model optimization
• calculation efficiency