M2飞机的复合材料机翼静强度载荷及试验研究

M2轻型运动飞机机翼结构采用复合材料,通过静力试验对其机翼强度进行验证,对发现机翼结构设计薄弱环节以及结构改型和发展具有重要意义。首先分析ASTMF2245-16机翼强度适航条款的要求;然后通过对M2飞机载荷包线、环境影响系数、限制载荷和极限载荷的研究,计算得到复合材料机翼载荷;最后进行机翼限制载荷静力试验、机翼极限载荷静力试验和机翼破坏载荷静力试验,并对试验结果进行分析。结果表明:M2飞机的极限载荷满足试验要求,复合材料机翼试验破坏载荷相对设计极限载荷的偏差为2%,M2飞机的复合材料机翼结构设计满足静强度设计要求。

STATIC STRENGTH LOAD AND EXPERIMENTAL STUDY OF COMPOSITE WING OF LIGHT SPORT AIRCRAFT

The M2 light sport aircraft structure is constructed of composite materials and designed in accordance with ASTM 2245-16 airworthiness specifications. The composite material is an anisotropic material, and environmental factors such as temperature and humidity will reduce the material properties. The environmental impact factor must be established, and the structural load after considering the environmental impact factor will increase. The wing loads need to consider bending, torsion and shear loads. The load conditions include maneuvering loads, gust loads, and inertial loads. The wing load distribution needs to consider the distribution of lift and gravity. The composite wing load was calculated by studying the M2 aircraft load envelope, environmental impact coefficient, limit load and ultimate load. The static test of the wing of the M2 aircraft is based on the symmetrical structure of the wing bearing force, and the sandbag loading on the wing is adopted; The wing root is fixedly supported, and the left and right wings are symmetrically loaded. The wing-limited load static test, the wing ultimate load static test and the wing damage load static test were carried out; The results of the wing static test show that the ultimate load of the M2 aircraft meets the test requirements, and the deviation of the composite wing test failure load relative to the design limit load is 2%. M2 aircraft composite wing structure design meets static strength design requirements. This paper has engineering guiding significance for the structural design of lightweight sports aircraft composites.