Crush experiment of composite cargo floor stanchions
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摘要: 复合材料已经在民用飞机结构上得到广泛应用,并逐渐应用到主承力结构中,复合材料的脆性特点给飞机的适坠性设计和评估提出了新的挑战。复合材料机身货舱地板支撑立柱作为坠撞过程中的重要吸能元件,对机身结构抗坠撞性能有重要影响。复合材料货舱地板支撑立柱在压溃失效模式下吸收的能量明显多于整体弯曲失效模式。根据民用飞机复合材料货舱地板立柱的设计需求,对不同试件触发模式、高度、截面形式、截面面积等设计参数变化的T700GC碳纤维/环氧树脂复合材料立柱开展准静态和动态压溃试验,得到立柱吸能特性的关键影响参数和设计因子。Abstract: Composite materials have been widely used in aircraft structures, and gradually applied to the main load-bearing structures. However, the brittle characteristic of composite materials has brought new challenges for aircraft crashworthiness design and evaluation. As the important energy-absorbing element, the composite stanchions for the cargo floor structure seriously affect the crashworthiness properties of composite fuselage. Composite stanchions can be designed to absorb much more energy through crushing failures than in a brittle global buckling mode. Based on the design requirements of the civil aircraft composite cargo floor stanchion, the trigger configuration, height, section, and section area were evaluated using quasi-static and dynamic crushing tests. The key influence factors of energy absorption characteristic properties for woven T700GC carbon fiber/epoxy composite stanchions were estimated. It provides reference for the structure design.
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Key words:
- composite structures /
- crashworthiness /
- energy absorption /
- crush test /
- composites failure modes
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表 1 T700GC碳纤维/环氧树脂复合材料立柱准静态和动态压溃试验结果
Table 1. Static and dynamic test results of woven T700GC carbon fiber/epoxy composite stanchions
CN SN a/mm b/mm h/mm Section type Trigger type Loading rate Fmax/kN Fave/kN EA/J ESEA/(J·g−1) 1-1 150-1 1.8 1.8 550 C 45°chamfer Static 35.40 17.00 3 636.20 52.60 150-2 30.67 19.20 3 796.00 54.90 Average 33.04 18.10 3 716.10 53.75 1-2 150-3 1.8 1.8 550 C 45°chamfer Dynamic 54.52 16.10 4 810.80 40.80 150-4 50.63 10.70 5 123.50 29.00 Average 52.58 13.40 4 967.15 34.90 2-1 160-1 2.5 2.5 550 C 45°chamfer Static 44.01 29.20 5 319.00 55.40 160-2 38.24 26.60 5 383.00 56.00 Average 41.13 27.90 5 351.00 55.70 2-2 160-3 2.5 2.5 550 C Steeple Dynamic 42.78 19.80 4 813.30 35.30 160-4 59.68 18.00 4 821.40 34.80 Average 51.23 18.90 4 817.35 35.05 3-1 170-1 3.5 2.5 550 C 45°chamfer Static 58.46 27.60 5 849.70 51.70 170-3 57.37 26.40 5 768.00 51.00 Average 57.92 27.00 5 808.85 51.35 3-2 170-4 3.5 2.5 550 C 45°chamfer Dynamic 58.82 21.80 4 731.90 31.00 170-5 56.58 22.40 4 744.10 33.00 Average 57.70 22.10 4 738.00 32.00 4-1 180-2 3.5 2.5 550 Wave 45°chamfer Static 61.47 40.00 8 766.10 73.50 180-3 60.48 37.60 8 390.40 70.40 Average 60.98 38.80 8 578.25 71.95 4-2 180-4 3.5 2.5 550 Wave 45°chamfer Dynamic 63.38 24.90 4 584.00 36.80 180-5 57.47 23.30 4 572.70 33.80 Average 60.43 24.10 4 578.35 35.30 5-1 190-1 3.5 2.5 250 C 45°chamfer Static 59.71 25.10 5 531.80 48.90 190-2 55.76 29.40 5 802.90 51.30 Average 57.74 27.25 5 667.35 50.10 5-2 190-3 3.5 2.5 250 C 45°chamfer Dynamic 56.52 22.40 4 669.00 33.00 190-4 46.36 18.70 4 738.20 27.10 Average 51.44 20.55 4 703.60 30.05 6-1 210-3 3.5 3.5 550 C 45°chamfer Static 51.45 28.10 6 079.90 45.20 210-4 63.60 42.40 8 935.00 66.40 Average 57.53 35.25 7 507.45 55.80 6-2 210-5 3.5 3.5 550 C 45°chamfer Dynamic 85.97 28.10 4 467.50 32.20 7-1 220-1 4 4 550 C Three tips Static 80.40 66.70 12 048.00 78.40 220-2 73.90 57.70 11 864.00 77.20 Average 77.15 62.20 11 956.00 77.80 7-2 220-5 4 4 550 C Three tips Dynamic 35.08 21.90 4 720.00 23.30 220-6 37.15 28.70 4 551.00 27.50 Average 36.12 25.30 4 635.50 25.40 Notes:CN—Configuration number of test specimens; SN—Serial number of test specimens; a, b, h—Characteristic dimension of tested specimens(see Fig.3); Fmax—Triggering load; Fave—Steady state crushing load; EA—Energy absorbed; ESEA—Specific energy absoption. -
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