论文部分内容阅读
对比分析了传统自然稳定与放宽静稳定性亚音速大型飞机操纵上的差异,研究了影响放宽静稳定性亚音速飞机重心范围设计的因素,提出了放宽静稳定性亚音速飞机重心范围设计准则,给出了不同影响因素下,平尾相对面积和重心之间的关系式。利用这种关系式,可以绘制出异于传统飞机重心范围设计的“剪刀图”。如果飞机的平尾相对面积给定,则可以很容易确定飞机的重心范围。为了说明所提放宽静稳定性亚音速飞机重心范围设计准则的可行性和可靠性,以某飞机为例,对设计准则进行验证性计算,对影响飞机重心边界确定的重要因素进行仿真分析,通过对计算结果的分析可知,起飞抬前轮和地面滑跑稳定性是影响放宽静稳定性亚音速飞机重心范围设计的主要因素,后期可通过调整起落架位置和设计巡航速度,充分利用性能最佳重心。
The differences between the control of the traditional natural stability and relaxation of the static stability subsonic aircraft are analyzed. The factors affecting the relaxation of the center of gravity range of the static stability subsonic aircraft are studied. The design criteria for relaxing the center of gravity range of the static stability subsonic aircraft are proposed, The relationship between the relative area and the center of gravity of the tail is given under different influence factors. Using this relation, you can draw a “scissor” that is different from the design of the center of gravity of a traditional aircraft. If the aircraft’s flat tail relative area given, you can easily determine the center of gravity range of the aircraft. In order to demonstrate the feasibility and reliability of the design criteria for the gravitational stability of subsonic aircraft, the paper takes a certain aircraft as an example and verifies the design criteria to simulate and analyze the important factors that affect the center of gravity of aircraft. The analysis of the calculation results shows that the stability of lift-off front wheel and ground slip is the main factor that affects the relaxation of the center of gravity range of the static-stability subsonic aircraft. In the latter part, the optimal performance can be fully utilized by adjusting the landing gear position and cruising speed Center of gravity