1) leading-edge flap
前缘机动襟翼
1.
In order to provide a numerical proof in the improved maneuvering flap design at the big sweepback and small aspect-ratio wing, the improved aero characteristic effect of maneuvering flap in high-subsonic phase is investigated by means of calculating and compare the state of leading-edge flap, trail-edge flap and their combination.
通过对前缘机动襟翼、后缘机动襟翼以及前后缘襟翼配合使用的状态作计算分析和比较,研究了机动襟翼在高亚音速段对构型气动特性的改善作用,为大后掠角、小展弦比机翼加装机动襟翼的改进设计提供了数值计算依据。
2.
According to it s fatigue tests, Fracture analysis of critical parts, comparision of life evaluations, The service life and repairing method of the leading-edge flap are given in the paper.
通过对某型飞机前缘机动襟翼疲劳试验、断口反推、两种载荷谱下的损伤比较以及关键部位类比寿命估算等 ,给出了某型飞机前缘机动襟翼的使用寿命 ,为前缘机动襟翼的使用维护及修理提供了依据。
3) trail-edge flap
后缘机动襟翼
1.
In order to provide a numerical proof in the improved maneuvering flap design at the big sweepback and small aspect-ratio wing, the improved aero characteristic effect of maneuvering flap in high-subsonic phase is investigated by means of calculating and compare the state of leading-edge flap, trail-edge flap and their combination.
通过对前缘机动襟翼、后缘机动襟翼以及前后缘襟翼配合使用的状态作计算分析和比较,研究了机动襟翼在高亚音速段对构型气动特性的改善作用,为大后掠角、小展弦比机翼加装机动襟翼的改进设计提供了数值计算依据。
4) maneuvering flap
机动襟翼
1.
According to the operating principle and technical conditions of aircraft maneuvering flap servo-control system, the structure and the design of hardware and software of the integrated testing system for aircraft maneuvering flap servo-control system are introduced in this paper.
根据飞机机动襟翼伺服控制系统的工作原理和技术条件 ,介绍了机动襟翼伺服控制系统的综合测试系统的结构及软、硬件设计原理。
补充资料：襟翼
见增升装置。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条