战斗机平尾翼面损伤对全机气动特性的影响分析

Influence on aircraft aerodynamic characteristics of damaged fighter plane horizontal tail

针对战斗机平尾翼面损伤后飞机的再平衡问题进行了研究。以某轻型战斗机为研究对象,利用Pointwise软件生成飞机无损状态和右侧平尾翼面外端损伤50%的表面网格,然后将网格导入ICEM CFD的Cart 3D模块绘制出用于计算的笛卡尔体网格。分析了典型飞行状态下无损飞机的全机气动特性,基于飞机运动方程得到了初始平飞状态为2°迎角和4°平尾偏角的气动特性和发动机所需推力。运用迭代分析法从理论上分析了右侧平尾翼面外端损伤50%时,维持飞机平飞所需迎角为1.9°,左右副翼偏角分别为1.2°和-1.2°,左平尾偏角为6.7°,方向舵偏角为-0.5°,发动机推力为18.256 3 kN。

The problem of aircraft rebalancing after the damage of fighter plane horizontal tail was studied.A light fighter plane was took as the research object,using Pointwise software to generate surface mesh of the aircraft non-damaged state and the 50% damage of the outer surface of the right horizontal tail.The Cartesian grid was drawn by importing the grid into the Cart 3 D module of ICEM CFD.The aerodynamic characteristics of a non-destructive aircraft under typical flight conditions were analyzed,and the aerodynamic characteristics and the thrust required by the engine were obtained based on the motion equations of the aircraft.The iterative analysis method was used to analyze theoretically the adjustment requirements for keeping the aircraft level flight with 50% damage of the right horizontal tail.The results show that the attack angle is 1.9°,the deflections of the left and right ailerons are 1.2° and-1.2° gespectively,the left horizontal tail deflection is 6.7°,the rudder declination is-0.5° and the engine thrust is 18.256 3 kN.