1) beam bender
[航]翼梁折弯机
4) wing spar
机翼主梁
1.
As an examole of analysing the fatigue crack of wing spar in type 5 Fighter-Trainer, The methods of crack propagation life prediction by means of fractography and Zheng-Hirt formula are ntrodued in this paper.
以歼教五机翼主梁疲劳断裂分析为例 ,介绍了用断口金相和Zheng -Hirt公式估算疲劳裂纹扩展寿命的方法 ,为研究老龄飞机的使用寿命问题 ,进行了有益的探
2.
The fatigue fracture of wing spar in type X finhter is observed with scanning electron microscope Both the crack propagation life and the amplitude of stress intersity factor are estimated with fatigue strition and Zheng Hirt formula The estimation is very close to the results of experiment It is a useful attempt to study the service life of old fighter
用扫描电镜观察了某型飞机机翼主梁的疲劳断口 ,用疲劳条带估算了裂纹扩展寿命 ,并用 Zheng- Hirt公式估算出裂纹尖端应力强度因子范围 ,估算结果与实验测定值十分接近 ,从而为研究老龄飞机的使用寿命 ,进行了有益的探
5) Front wing spar
机翼前梁
6) wing with beams
梁式机翼
1.
The design conception of damageable substitute is for the first time applied to control the fatigue life of a wing with beams and it is also verified in the fatigue life tests of main beams of wings and aircraft components.
应用“替损件”的设计思想来控制梁式机翼的疲劳寿命，并在××机翼主梁的寿命试验和全机组合疲劳试验中得到验证，得出十分满意的结果，为梁式机翼结构实现长寿命高可靠性的目标，提供一条成功的途径。
补充资料：板料折弯机
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主要参数内容 | 国际先进 | 国内先进 | 国内一般 | 国内落后 | 评定方法及说明 | ||
（一）板料折弯精度（度） | ±0.5 | ±1 | ±1.5 | ＞±1.5 | 参照GB/T14349-93、ZBJ62006.10-88 | ||
（二）结构性能 | |||||||
采用数控或计算机控制 | 有 | 有 | 无 | 无 | |||
（三）噪声dB（A） | |||||||
公称力630~2500kN 液压 | 82 | 83 | 85 | ＞85 | |||
公称力630~2500kN 机械 | 87 | 88 | 90 | ＞90 | |||
公称力＞2500kN 液压 | 85 | 86 | 88 | ＞88 | |||
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