复合材料货舱地板立柱压溃响应试验

汪洋; 吴志斌; 刘富

doi:10.13801/j.cnki.fhclxb.20200111.001

复合材料货舱地板立柱压溃响应试验

doi: 10.13801/j.cnki.fhclxb.20200111.001

上海飞机设计研究院，上海 201210

详细信息

通讯作者:
汪洋，硕士，高级工程师，研究方向为冲击动力学及复合材料结构设计　E-mail：wangyang3@comac.cc

中图分类号: V216.1+1；V216.2+3
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- 被引次数: 0
出版历程
- 收稿日期: 2019-10-30
- 录用日期: 2019-12-20
- 网络出版日期: 2020-01-13
- 刊出日期: 2020-09-15

Crush experiment of composite cargo floor stanchions

Shanghai Aircraft Design and Research Institute, Shanghai 201210, China

摘要

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。
- 复合材料结构 /
- 适坠性 /
- 能量吸收 /
- 压溃试验 /
- 复合材料失效模式
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.
- composite structures /
- crashworthiness /
- energy absorption /
- crush test /
- composites failure modes

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图 1 典型复合材料立柱压溃载荷-位移曲线

Figure 1. Typical load-displacement curve of composite crush element

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图 2 试验装置

Figure 2. Experimental setup

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图 3 T700GC碳纤维/环氧树脂复合材料立柱示意图和特征尺寸标示图

Figure 3. Diagram and characteristic dimension of woven T700GC carbon fiber/epoxy composite stanchions

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图 4 T700GC碳纤维/环氧树脂复合材料立柱截面示意图

Figure 4. Plan view of woven T700GC carbon fiber/epoxy composite stanchions

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图 5 试件触发模式示意图

Figure 5. Trigger configuration of tested specimens

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图 6 T700GC碳纤维/环氧树脂复合材料立柱准静态和动态加载变形

Figure 6. Post-test images of woven T700GC carbon fiber/epoxy composite stanchions for static and dynamic tests

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图 7 T700GC碳纤维/环氧树脂复合材料立柱准静态和动态加载载荷-位移曲线

Figure 7. Load vs. displacement curves of woven T700GC carbon fiber/epoxy composite stanchions for static and dynamic tests

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图 8 削尖和三削尖触发的T700GC碳纤维/环氧树脂复合材料立柱试件变形

Figure 8. Post-test images of woven T700GC carbon fiber/epoxy composite stanchions for steeple and three tips trigger configurations

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图 9 波纹型T700GC碳纤维/环氧树脂复合材料立柱变形

Figure 9. Post-test images for waved type woven T700GC carbon fiber/epoxy composite stanchions

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图 10 C型和波纹型T700GC碳纤维/环氧树脂复合材料立柱压溃试验载荷-位移曲线比较

Figure 10. Comparison of load-displacement curves for C type and waved type woven T700GC carbon fiber/epoxy composite stanchions

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图 11 C型/45°倒角触发T700GC碳纤维/环氧树脂复合材料立柱的稳定压缩载荷与截面积的关系

Figure 11. Variation of load with increasing cross section area for C type/45° chamfer triggered woven T700GC carbon fiber/epoxy composite stanchions

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图 12 所有构型T700GC碳纤维/环氧树脂复合材料立柱比吸能E_SEA平均值

Figure 12. Average specific energy absorption E_SEA of woven T700GC carbon fiber/epoxy composite stanchions of all configurations

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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	F_max/kN	F_ave/kN	E_A/J	E_SEA/(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	1.8	1.8	550	C	45°chamfer	Static	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	1.8	1.8	550	C	45°chamfer	Dynamic	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	2.5	2.5	550	C	45°chamfer	Static	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	2.5	2.5	550	C	Steeple	Dynamic	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	3.5	2.5	550	C	45°chamfer	Static	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	3.5	2.5	550	C	45°chamfer	Dynamic	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	3.5	2.5	550	Wave	45°chamfer	Static	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	3.5	2.5	550	Wave	45°chamfer	Dynamic	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	3.5	2.5	250	C	45°chamfer	Static	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	3.5	2.5	250	C	45°chamfer	Dynamic	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	3.5	3.5	550	C	45°chamfer	Static	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	4	4	550	C	Three tips	Static	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	4	4	550	C	Three tips	Dynamic	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); F_max—Triggering load; F_ave—Steady state crushing load; E_A—Energy absorbed; E_SEA—Specific energy absoption.

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