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推荐的军用规范MIL-A-8591E版《机载悬挂物及其悬挂装置的通用设计准则》一文中,就对外挂物结构设计的受载准则作了些更改。其中两个主要更改是:气动载荷准则和吊耳及臂状止动器反作用力的计算方法。 以前,外挂物上的气动载荷是由攻角与飞机性能有关的准则而规定的,且以现役的主要飞机为基础。在E版中,这些准则已经普通化且以方程式表示。准则的数值从特定的几何参数和性能参数计算出,这些参数能用以表示专用机种或一类飞机,又能按采购方要求表示保守设计。 吊耳及臂状止动器对外载荷反作用力的计算方法,在规范中作为附录,也已修改。为处理静不定的偏航力矩反作用力所必需的假设都根据实验室试验结果作了更改。这种新方法采用载荷分布因数,它是悬挂系统的函数,其数值已凭经验求得。
Recommended Military Code MIL-A-8591E, “General Design Guidelines for Airborne Suspension and Suspension Devices,” makes some changes to the loading guidelines for exterior structure design. Two of the major changes are: Pneumatic load criteria and calculation of reaction forces on lugs and arm stoppers. Previously, aerodynamic loads on external objects were specified by the criteria for angle-of-attack and aircraft performance and were based on active active aircraft. In the E version, these guidelines have been normalized and expressed in equations. The values of the criteria are calculated from specific geometric and performance parameters that can be used to represent a dedicated aircraft or a class of aircraft and to represent the conservative design as requested by the purchaser. Lifting ears and arm stopper external load reaction force calculation method, as an appendix in the specification, has also been modified. The assumptions necessary to deal with the static yaw moment reaction force are all based on the laboratory test results. This new method uses the load distribution factor, which is a function of the suspension system and its value has been empirically determined.