1) wing-tip missile
翼尖弹
3) winglet
[英]['wiŋlit] [美]['wɪŋlɪt]
翼尖小翼
1.
To match these needs,a bigger wing aspect ratio and winglet are adopted as the improvement measures,hopefully the lift-drag ratio of the modified UAV could be increased.
为延长某无人机的留空时间,加大航程和提高升限,用适当加大机翼展弦比和加装翼尖小翼的办法对原型机的气动特性进行了改进,以期能使该无人机的升阻比有较大提高。
2.
Modification of winglet is adopted to raise the lift-drag ratio of the UAV for extension endurance,for enlarge range and for increase ceiling.
为延长无人机留空时间,加大航程和提高升限,可采用加装翼尖小翼的方法使无人机的升阻比有所提高。
4) wing-tip aileron; rotating wing-tip
翼尖副翼
5) missile wing
弹翼
1.
It is shown that the scheme of the aerodynamic simulation load device is practicable;the aerodynamic loads of missile wings can be simulated in a practical and equivalent way,which may greatly reduce the time and expense for related development.
实践应用表明气动模拟加载装置方案基本能够真实、等效的模拟弹翼气动载荷,利用该装置大大地缩短研制周期、节省研制经费,可以进行推广应用。
2.
For missile wing,introduce its computation model,load conditions,development plan,test circuit,test results etc.
介绍了弹翼展开装置的计算模型、载荷条件、研制方案、测试电路、试验结果等,在地面模拟确定弹翼展开过程中所需的气动力参数,从而优化了作动筒参数,保证了弹翼的顺利展开。
3.
The high real-time requirement of the spreading of missile wing requires that electric loading system be used.
基于实时性要求极高的导弹弹翼电动加载系统的硬件结构和控制原理,对多余力矩的产生原因、理论计算及消除方法进行了详细研究。
6) wing
[英][wɪŋ] [美][wɪŋ]
弹翼
1.
Quality Control of C/E Composite Wings;
碳/环氧复合材料弹翼的质量控制
2.
A design of mechanism for unfolding wings with large aspect ratio is put forward.
提出一种大展弦比弹翼张开机构的设计方案 ,该方案选择弹簧、压缩气体或燃气为动力源 ,采用连杆机构传递驱动力 ,符合约束条件与设计规范 ;在此基础上建立弹翼张开机构的运动分析模型 ,包括弹翼张开机构的运动关系、受力分析和动力学方程。
3.
This paper mainly calculated, analyzed and compared two kinds of glide bullets, one has wing, and the other has no wing.
针对滑翔增程弹在有弹翼和无机翼两种情况下 ,气动特性进行了计算、分析和比较 。
补充资料：半硬壳式弹体(见弹道导弹弹体)
半硬壳式弹体(见弹道导弹弹体)
semi-hard-shelled missile body
bQn yingkeshi dan桩半硬壳式弹体(semi一hard一shelled、ssilebody)见弹道导弹弹体。
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