The paper introduces the difficulties met in A/C loads calculation during abrupt pitching maneuver and rolling pullout, and in wing load calculation during rolling maneuvers.
介绍在使用国军标规范《军用飞机强度和刚度规范》中对于急剧俯仰机动、滚转改出及滚转机动机翼载荷计算时所遇到的困难、解决办法及其软件研制。
The final test occurred Apr. 21 when the wing and trailing edges were subjected to their limit load of around 2.5g, the highest loads expected to be seen in service.
根据4月21最终试验的结果，机翼和后缘的承受的极限负荷为2.5g左右，而实际最高负荷只能在实际服役的时候才能知道。
As an example of large sized structural component, the mechanical model of load calibration test of an airplane wing was analysed.
以飞机机翼等大型结构为例，探讨了大型结构部件载荷标定试验的力学模型。
If this load centroid is behind the elastic axis of the wing structure, then a nose-down twist of the main wing surface results.
如果该载荷重心在机翼结构弹性轴之后，则引起主机翼表面前端向下的扭转。
This paper studies the design of precept of missile's wing and rudder load simulation system whose core is digital signal processor (DSP) and DTC servo driver.
本文研究了以数字信号处理器(dsp)和直接转矩控制器为核心的弹用负载模拟加载系统方案设计。
Note that the pilot's load is supported by a smaller portion of the wing and less lines.
请注意，飞行员的负载是由小部分的伞体及较少的伞绳支撑着。
The drive load may increase with multiply construction but the overall deformation is dependent on the stiffness ratio between the actuators and the wing.
多铺层可以增加驱动载荷，但总体变形效果还取决于结构系统的刚度比例；
The paper deduces the theoretical derivation of figure coefficient of wind load in wing tunnel test, which can do help data processing of wing tunnel test.
较详细的演绎了风洞测压试验中关于风载体型系数的理论推导公式，为风洞试验数据处理提供了帮助。
Abstract :Failure process of a primary load-bearing composite joint in wing root was analyzed by finite element methods, and the ultimate strength of the joint was predicted.
以复合材料机翼翼根后梁下缘条对接试件为研究对象，通过有限元手段分析其失效机理和破坏过程，并对极限强度进行预测。
As the main load-bearing structure, wing box is one of the main optimization objects which has great potential of weight reduction.
翼盒为机翼主要承力部件，优化潜力较大，是机翼结构优化设计的重点对象。
As the main load-bearing structure, wing box is one of the main optimization objects which has great potential of weight reduction.
翼盒为机翼主要承力部件，优化潜力较大，是机翼结构优化设计的重点对象。
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