关于新一代飞机的设计载荷

设计载荷是确定飞机结构重量和保证安全的重要因素。常规操纵系统飞机的设计载荷都是由现行的强度规范规定的。但是对于采用主动控制技术和复合材料的高机动飞机,现行的规范已不合适。在过去10年中,飞机界的专家对此问题进行了大量研究。本文根据北约公开的材料介绍这些研究工作。本文首先评述了现有规范并指出其不足,然后讨论了安全系数。为确定主动控制的新飞机的设计载荷,介绍了3种方法,即概率法、作战飞行参数法和飞行参数包线法及其在EF2000飞机设计中的应用;还介绍了飞机设计的各种动载荷;最后提出了确定我国新一代飞机设计载荷的建议。

On Design Loads for New-Generation Fighter Aircraft

The selection of design loads is defining the structure weight of aircrafts and their safety. For conventionally controlled aircraft the design loads are specified in the current specifications. But the aircraft equiped with the active control technology as well as carefree maneuvering features, and constructed with composite materials, these specifications are not adequate, During past decades this subjet has been an increased interest of the aircraft community on design loads for future aircraft. This paper gives a concise introduction of the works done on this topis mainly based on NATO unclassified materials. We first give a review of the current specifications and point out their drawbacks, and then discuss the Factor of Safety. To define the design loads for actively controlled aircraft, three approaches are presented, i.e. Probabilistic Determination of Limit Load, Operational Flight Parameter Approach and Flight Parameter Envelope Approach with its application in EF 2000 design. The variety of dynamic loads are also discussed. Finally, the paper gives suggestions to determine the design loads for our future aircraft.