1) 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。
2) wing flap motion tube
飞机襟翼作动筒
1.
A new repairing technology making use of brush plating of Ni-W coating was established to repair the worn piston of wing flap motion tube,based on the failure analysis of the worn piston of wing flap motion tube.
为解决飞机襟翼作动筒磨损失效活塞的修复问题,开展了电刷镀镍-钨修复镀层的研究。
3) 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。
4) 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。
5) Flap maneuvering speed
襟翼机动速度
6) body flap
机身襟翼
1.
All-C/SiC composites body flap is gas-loaded intensely when the return of the space vehicle into Earth s atmosphere with high-supersonic.
针对全C/SiC复合材料机身襟翼再入过程中受到强烈的气动载荷作用的受力状况,进行了静力试验考核。
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