CN105092360A - Propellant/lining interface crack critical intensity stress factor detection method - Google Patents
Propellant/lining interface crack critical intensity stress factor detection method Download PDFInfo
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- CN105092360A CN105092360A CN201410198902.0A CN201410198902A CN105092360A CN 105092360 A CN105092360 A CN 105092360A CN 201410198902 A CN201410198902 A CN 201410198902A CN 105092360 A CN105092360 A CN 105092360A
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Abstract
The invention provides a propellant/lining interface crack critical intensity stress factor detection method for evaluating the structural integrity and the storage life of a solid rocket engine. The detection method comprises three steps: a step 1: preparing a sample, including selecting the sample and producing blocks, and cutting the test blocks into slices and carrying out incision; a step 2: carrying out a tensile test and recording an image; a step 3: processing data and carrying out calculation for analysis. The unidirectional tensile test is carried out for the sample by a stretcher, a crack initiation time and the image are recorded during a crack initiation and expansion process by a CCD digital optical microscope, the obtained image is processed by a digital image processing technology, a displacement change of a front corresponding point of the crack tip in the sample stretching processing, a change relation of the propellant/lining interface crack critical intensity stress factor over time is calculated, and finally the propellant/lining interface crack critical intensity stress factor is obtained from the change relation and the crack initiation time. The detection method has the advantages of sample preparation convenience, reasonable indexes, accurate calculation and reliable data.
Description
Technical field
The present invention relates to a kind of solid propellant rocket structural intergrity and storage life assessment technology, particularly a kind of propellant/lining interface crackle critical intensity stress factor detection method.
Background technology
Usually, adherent casting type solid rocket engine is formed primarily of housing, heat insulation layer, lining and propellant, and the interfacial adhesion of propellant/lining is the key factor determining the overall engine life-span.The Micro-v oid of propellant/lining interface and the fusion of micro-crack under load effect are the main causes causing interfacial detachment with expansion.The interfacial detachment of propellant/lining directly reflects the interfacial fracture characteristic of propellant/lining, and its mechanism is complicated, evaluation index is uncertain, and therefore the interfacial fracture characteristic of propellant/lining is still in the exploratory stage.
Summary of the invention
The object of the invention is to provide a kind of propellant/lining interface crackle critical intensity stress factor detection method, it can accurately utilize image processing techniques quantitatively to calculate the Interface Crack stress intensity factor of propellant/lining, effectively utilize stress intensity factor-time curve determination Interface Crack critical stress intensity factors, reliably realize solid propellant rocket structural intergrity and life appraisal.
Design a kind of propellant/lining interface crackle critical intensity stress factor detection method, comprise the following steps:
Step one, prepared by sample: sample is chosen and clamp dog, test block section and cutting.When sample is chosen with clamp dog, select Different years containing the sample of propellant/lining interface, sample is the rectangular parallelepiped test block containing propellant, lining, heat insulation layer, and specification is 10mm × 10mm × 20mm, and the length direction of test block is consistent with propellant/lining interface horizontal direction.When test block section and cutting, adopt microtome test block to be cut into the section that thickness is 1mm, cut into slices through diel cutting, namely obtain propellant/lining interface sample.
Step 2, tension test and photologging: tension test selects sensor, range to be the drawing machine of 20N, photologging adopts the digital optical microscope of CCD.During tension test, utilize fixture to fix propellant/lining interface sample, propellant is fixed in one end, and heat insulation layer is fixed in one end, and the rate of extension of drawing machine is 5mm/min; For photologging is the digital optical microscopes of 25 times of CCD, and optical lens is placed in propellant/lining interface sample dead ahead, and lens focus is near the sample crack tip of interface; In stretching, adjustment camera lens is to ensure that lens focus is near crack tip in good time, and drawing process is by the digital optical microscope video record of CCD.
Step 3, data processing and computational analysis: the digital image processing techniques adopting Matlab software, crack initiation time and the view data of crackle crack initiation and crack propagation process is obtained by the digital optical microscope of CCD, digital image processing techniques are utilized to process view data, and then obtain the change in displacement of crack tip front corresponding point in sample drawing process, calculate Interface Crack stress intensity factor, set up stress intensity factor-time curve, determine Interface Crack critical stress intensity factors.
During data processing, the video record according to the digital optical microscope of CCD finds out the Interface Crack crack initiation time, and through the Digital Image Processing of Matlab software, video record is converted into a series of drawing process photo, the time interval between adjacent photo is 20s.Two photos before and after duplicate distortion, choose two points that r=2mm place, crack tip front corresponds respectively to propellant and lining edge, i.e. A (x
1, y
1) and B (x
2, y
2), then by Digital Image Processing, show that the new position in drawing process not in the same time corresponding to A and B 2 is respectively A ' (x
1', y
1') and B ' (x
2', y
2').
During computational analysis, first calculate Interface Crack stress intensity factor, be resilient material at setting propellant and lining, under interface sample drawing process is the condition of plane strain, go out Interface Crack stress intensity factor by formulae discovery; Then according to the calculating data of Interface Crack stress intensity factor, obtain not propellant/lining interface stress intensity factor of crack in the same time, set up stress intensity factor-time curve, curve is found out stress intensity factor corresponding to crackle crack initiation time, is Interface Crack critical stress intensity factors.
Advantageous Effects of the present invention is: owing to introducing the concept of Interface Crack critical stress intensity factors in the interfacial detachment evaluation index of propellant/lining, thus establishes the numerical relation between the interfacial fracture characteristic of propellant/lining and rocket motor structure integrality, storage life.Simultaneously because testing process have employed the digital optical microscope of CCD, thus for image record, Time transfer receiver and image procossing provide conveniently.In addition owing to applying the digital image processing techniques of band software, thus provide possibility for the subsequent analysis such as the identification of change in displacement, the foundation of stress intensity factor-time curve calculates.The present invention also has sample preparation convenience, index is reasonable, calculating is accurate and the reliable advantage of data.
Accompanying drawing explanation
Fig. 1 is section schematic diagram.
Fig. 2 is sample schematic diagram.
Fig. 3 is stress intensity factor-time plot.
In figure, 1, propellant, 2, lining, 3, heat insulation layer.
Embodiment
The present invention is further described for the embodiment provided below by accompanying drawing.
For NEPE/HTPB/EDPM system, wherein, NEPE is nitrate plasticising polyethers, and HTPB is end hydroxy butadiene, and EDPM is ethylene-propylene-diene rubber, detects the propellant/lining interface stress intensity factor of crack of the bonding system of NEPE/HTPB/EDPM propellant.
Step one, prepared by sample: sample is chosen and clamp dog, test block section and cutting.When sample is chosen with clamp dog, select Different years containing the sample of propellant/lining interface, sample is the rectangular parallelepiped test block containing propellant, lining, heat insulation layer, and specification is 10mm × 10mm × 20mm, and the length direction of test block is consistent with propellant/lining interface horizontal direction.When test block section and cutting, adopt microtome test block to be cut into the section that thickness is 1mm, cut into slices through diel cutting, namely obtain propellant/lining interface sample.
First the propellant containing the bonding system of NEPE/HTPB/EDPM propellant/lining interface sample is cut into slices, complete section by hand, utilize vernier caliper measurement slice thickness, selection thickness is the section between 0.95 ~ 1.05mm, with mould, section is cut again, obtain the propellant/lining interface sample of the bonding system of NEPE/HTPB/EDPM propellant.
Step 2, tension test and photologging: tension test selects sensor, range to be the drawing machine of 20N, photologging adopts the digital optical microscope of CCD.During tension test, utilize fixture to fix propellant/lining interface sample, propellant is fixed in one end, and heat insulation layer is fixed in one end, and the rate of extension of drawing machine is 5mm/min; For photologging is the digital optical microscopes of 25 times of CCD, and optical lens is placed in propellant/lining interface sample dead ahead, and lens focus is near the sample crack tip of interface; In stretching, adjustment camera lens is to ensure that lens focus is near crack tip in good time, and drawing process is by the digital optical microscope video record of CCD.
Step 3, data processing and computational analysis: data processing selects the digital image processing techniques of Matlab software, crack initiation time and the view data of crackle crack initiation and crack propagation process is obtained by the digital optical microscope of CCD, digital image processing techniques are utilized to process view data, and then obtain the change in displacement of crack tip front corresponding point in sample drawing process, calculate Interface Crack stress intensity factor, set up stress intensity factor-time curve, determine Interface Crack critical stress intensity factors.
During data processing, the video record according to the digital optical microscope of CCD finds out the Interface Crack crack initiation time.First, change video record with Premiere software, draw a series of drawing process picture, the time interval between adjacent photo is 20s; Secondly, resolve with the Digital Image Processing based on Matlab software, two photos before and after duplicate distortion, choose two points that r=2mm place, crack tip front corresponds respectively to propellant and lining edge, i.e. A (x
1, y
1) and B (x
2, y
2); Then, by Digital Image Processing, show that the new position in drawing process not in the same time corresponding to A and B 2 is respectively A ' (x
1', y
1') and B ' (x
2', y
2'); Finally, calculate the stress intensity factor not playing propellant/lining interface in the same time, draw stress intensity factor-time curve.
During computational analysis, first calculate Interface Crack stress intensity factor, be resilient material at setting propellant and lining, under interface sample drawing process is the condition of plane strain, go out Interface Crack stress intensity factor by formulae discovery; Then according to the calculating data of Interface Crack stress intensity factor, obtain not propellant/lining interface stress intensity factor of crack in the same time, set up stress intensity factor-time curve, curve is found out stress intensity factor corresponding to crackle crack initiation time, is Interface Crack critical stress intensity factors.
According to Fig. 3-stress intensity factor-time plot, the crackle crack initiation time of finding interface sample from stretching video record is 392s, and corresponding stress intensity factor is 0.158
, can determine that the critical stress intensity factors of the propellant/lining interface crackle of the bonding system of NEPE/HTPB/EDPM propellant is Kc=0.158 like this
.
Claims (3)
1. propellant/lining interface crackle critical intensity stress factor detection method, is characterized in that: comprise the following steps:
Step one, prepared by sample: sample is chosen and clamp dog, test block section and cutting;
Step 2, tension test and photologging: tension test selects sensor, range to be the drawing machine of 20N, photologging adopts the digital optical microscope of CCD;
Step 3, data processing and computational analysis: the digital image processing techniques of data processing select tape Matlab software, crack initiation time and the view data of crackle crack initiation and crack propagation process is obtained by CCD optical microscope, digital image processing techniques are utilized to process view data, and then obtain the change in displacement of crack tip front corresponding point in sample drawing process, calculate Interface Crack stress intensity factor, set up stress intensity factor-time curve, determine Interface Crack critical stress intensity factors.
2. propellant according to claim 1/lining interface crackle critical intensity stress factor detection method, it is characterized in that: during data processing, video record according to the digital optical microscope of CCD finds out the Interface Crack crack initiation time, through the Digital Image Processing of Matlab software, video record is converted into a series of drawing process photo, the time interval between adjacent photo is 20s;
Two photos before and after duplicate distortion, choose two points that r=2mm place, crack tip front corresponds respectively to propellant and lining edge, i.e. A (x
1, y
1) and B (x
2, y
2), then by Digital Image Processing, show that the new position in drawing process not in the same time corresponding to A and B 2 is respectively A ' (x
1', y
1') and B ' (x
2', y
2').
3. propellant according to claim 1/lining interface crackle critical intensity stress factor detection method, it is characterized in that: during computational analysis, first Interface Crack stress intensity factor is calculated, be resilient material at setting propellant and lining, under interface sample drawing process is the condition of plane strain, go out Interface Crack stress intensity factor by formulae discovery; Then according to the calculating data of Interface Crack stress intensity factor, obtain not propellant/lining interface stress intensity factor of crack in the same time, set up stress intensity factor-time curve, curve is found out stress intensity factor corresponding to crackle crack initiation time, is Interface Crack critical stress intensity factors.
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Cited By (5)
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| CN105699218A (en) * | 2016-01-26 | 2016-06-22 | 清华大学 | Method for performing online measurement on fatigue crack propagation of organic glass |
| CN112098168A (en) * | 2020-08-14 | 2020-12-18 | 上海交通大学 | Preparation method of defect-containing sample and fatigue crack propagation real path reduction method |
| CN112903442A (en) * | 2021-01-26 | 2021-06-04 | 北京市理化分析测试中心 | Method for testing I-type fracture toughness of bonding interface of composite material bonding structure |
| CN114838852A (en) * | 2022-05-10 | 2022-08-02 | 重庆科技学院 | Experimental device and experimental method for determining direction of geological stress field |
| CN116754211A (en) * | 2023-08-22 | 2023-09-15 | 中国人民解放军火箭军工程大学 | Method and related device for acquiring mechanical property information of solid rocket propeller |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105699218A (en) * | 2016-01-26 | 2016-06-22 | 清华大学 | Method for performing online measurement on fatigue crack propagation of organic glass |
| CN112098168A (en) * | 2020-08-14 | 2020-12-18 | 上海交通大学 | Preparation method of defect-containing sample and fatigue crack propagation real path reduction method |
| CN112098168B (en) * | 2020-08-14 | 2021-06-29 | 上海交通大学 | Preparation method of defect-containing sample and fatigue crack propagation real path reduction method |
| CN112903442A (en) * | 2021-01-26 | 2021-06-04 | 北京市理化分析测试中心 | Method for testing I-type fracture toughness of bonding interface of composite material bonding structure |
| CN114838852A (en) * | 2022-05-10 | 2022-08-02 | 重庆科技学院 | Experimental device and experimental method for determining direction of geological stress field |
| CN114838852B (en) * | 2022-05-10 | 2023-05-30 | 重庆科技学院 | Experimental device and experimental method for determining direction of geological stress field |
| CN116754211A (en) * | 2023-08-22 | 2023-09-15 | 中国人民解放军火箭军工程大学 | Method and related device for acquiring mechanical property information of solid rocket propeller |
| CN116754211B (en) * | 2023-08-22 | 2023-12-19 | 中国人民解放军火箭军工程大学 | Method and related device for acquiring mechanical property information of solid rocket propeller |
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Application publication date: 20151125 |