Static Strength Load and Experimental Study of Composite Wing of M2 Aircraft

Abstract

Composite material is used in the wing structure of M2 light sport aircraft. The strength of the wing is verified by static test. It is of great significance to find the weak links in the wing structure design and the structural modification and development. Firstly, the requirements of strength airworthiness clause of ASTM F2245-16 wing are analyzed. Then, the composite wing loads are calculated by studying the load envelope, environmental impact factor, limiting load and ultimate load of M2 aircraft. Finally, the static test of wing limited load, wing ultimate load and wing damage load are carried out, and the test results are analyzed. The results show that the ultimate load of M2 aircraft meets the test requirements, the deviation of the damage load of composite wing test from the design limit load is 2%, and the structural design of composite wing of M2 aircraft meets the static strength design requirements.

Keywords

• composite material
• wing
• static strength
• loads
• test