重心位置对飞机阻力及其飞行性能的影响  

Effect of Center of Gravity Position on Aircraft Drag and Flight Performance

作　　者：许维进[1] 刘志敏[1] 

机构地区：[1]沈阳飞机研究所

出　　处：《飞行力学》1999年第1期54-58,共5页Flight Dynamics

摘　　要：为了降低配平状态下飞机的阻力问题，推导了飞机升致阻力与重心位置间的关系式。以一架典型的后平尾飞机为例，计算了向后移动飞机重心的位置，放宽对飞机固有静稳定度的要求对飞机配平升致阻力和总阻力以及对部分性能的影响。结果表明，当向后移动重心位置时，其配平升致阻力下降，并在某一重心位置时达最小值。对于一架现役飞机，通过重心后移的方法只能得到较小的性能收益。因此。In this paper, in order to reduce the drag in trimming condition, the formula of aircraft induced drag and center of gravity is derived. According to a typical fighter of rear horizontal tail, the effect iscalculated that the center of gravity position of the fighter is moved bake ward, relax static stability on induced drag, total drag and part of flight performance. The result turns out that when center of gravity position is moved bake ward the drag is reduced in trimming condition and attain a minimum value in a certain center of gravity position. As to service aircraft, however, moving bake ward the center of gravity position only attains a little improvement on flight performance. Therefore, relaxed static stability should be considered at the beginning of program designing.

关 键 词：静稳定度 配平阻力 升致阻力 重心 飞行性能 

分 类 号：V212.13[航空宇航科学与技术—航空宇航推进理论与工程] V221.5