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针对某型前三点式飞机在首飞前连续低速滑行刹车过程中的偏航问题,假设飞机的起落架、机轮和轮胎为刚性,其侧向、纵向和扭转变形均为零,不考虑机轮和轮胎回转体的质量和转动惯量,忽略轮胎的柔性,建立飞机平稳滑行的力学模型。基于理论力学分析方法,得到该型飞机在水平方向的力矩平衡方程和两侧主机轮刹车力矩最大允差的计算公式,并进行实验验证。结果表明:在排除其它因素的情况下,前三点式飞机在连续低速滑行刹车过程中偏航与否,取决于两侧主机轮刹车力矩的差值。在正常起飞条件下,该型飞机刹车力矩差值大于1 828N·m时,容易偏航;小于1 455 N·m时,不会偏航。这一结果可作为前三点式飞机刹车性能设计的依据,有利于促进炭刹车材料的推广和应用。
Aiming at the problem of yawing of a certain first three-point aircraft during the continuous low-speed braking before the first flight, assuming that the landing gear, wheel and tire of the aircraft are rigid, the lateral, longitudinal and torsional deformations of the aircraft are all zero, irrespective of the wheel And the tire mass and moment of inertia, ignoring the flexibility of the tire, the establishment of aircraft smooth sliding mechanical model. Based on the theoretical mechanics analysis method, the formula of the moment balance of the aircraft in the horizontal direction and the maximum allowable braking torque on both sides of the aircraft are obtained and verified by experiments. The results show that the front three-point aircraft yawing during the continuous low-speed coasting brake with other factors excluded depends on the difference of the brake torque on both sides of the host. Under normal take-off conditions, this aircraft is easy to yaw when its braking torque difference is more than 1828N · m. When it is less than 1 455 N · m, it will not yaw. This result can be used as the basis for the design of brake performance of the first three-point aircraft, which is beneficial to the popularization and application of carbon brake materials.