以国产高模M40J级碳纤维为增强材料,使用不同树脂浸润程度的传统热压罐预浸料及热压罐外(OoA)预浸料,结合热压罐成型工艺和OoA成型工艺制备了两种试验件。通过A扫超声检测、金相检测、力学性能测试等方法对比了两种试验件的内部质量及力学性能。结果表明:超声A扫波型显示两种成型工艺制备的同类型试验件其内部质量均无明显缺陷;金相检测显示热压罐成型的试验件孔隙率为0.06%,OoA成型的试验件孔隙率为0.11%,均小于引起试样力学性能下降的临界孔隙率;力学性能检测显示两种成型工艺试验件的拉伸、压缩、弯曲、层间剪切强度平均值分别相差0.65%、3.0%、6.7%和2.7%,拉伸、压缩、弯曲模量平均值分别相差0.94%、3.74%和3.91%。另外,使用该OoA预浸料制造出了合格的无人机主承力结构件主翼梁,进一步说明了国产高模OoA预浸料制备航空航天主承力结构件具有较高的可行性。
Two test specimens were fabricated by combining autoclave molding process and OoA molding process using domestic high-modulus M40J-grade carbon fiber as the reinforcement material and traditional autoclave prepregs and out-of-autoclave (OoA) prepregs with different resin impregnation levels.The internal quality and mechanical properties of the two test specimens were compared through A-scan ultrasonic testing,metallographic testing,and mechanical property testing.The results showed that the A-scan ultrasonic waveforms of the two types of test specimens prepared by the two molding processes had no obvious defects in internal quality.Metallographic testing revealed that the porosity of the autoclave-molded test specimen was 0.06%,and that of the OoA-molded test specimen was 0.11%,both of which were less than the critical porosity that caused a decrease in mechanical properties of the specimens.Mechanical property testing indicated that the average values of tensile,compressive,flexural,and interlaminar shear strengths of the test specimens prepared by the two molding processes differed by 0.65%,3.0%,6.7%,and 2.7%,respectively,and the average values of tensile,compressive,and flexural moduli differed by 0.94%,3.74%,and 3.91%,respectively.In addition,qualified main wing spars of unmanned aerial vehicle (UAV) main load-bearing structural components were fabricated using this domestic high-modulus OoA prepreg,further demonstrating the high feasibility of preparing aerospace main load-bearing structural components with domestic high-modulus OoA prepreg.
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