Propellant/lining interface crack critical intensity stress factor detection method

A detection method and stress factor technology, applied in the direction of strength characteristics, measuring devices, instruments, etc., can solve the problems of uncertain evaluation indicators and complicated action process, and achieve the effects of reasonable indicators, convenient sample preparation, and reliable data

Inactive Publication Date: 2015-11-25
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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Problems solved by technology

The interfacial debonding of the propellant / liner directly reflects the interfacial fracture characteristics of the propellant / liner. The action process is complex and the evaluation index is uncertain. Therefore, the interfacial fracture characteristics of the propellant / liner are still in the exploratory stage.

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  • Propellant/lining interface crack critical intensity stress factor detection method
  • Propellant/lining interface crack critical intensity stress factor detection method
  • Propellant/lining interface crack critical intensity stress factor detection method

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Embodiment Construction

[0015] The present invention is further described by the embodiments provided by the accompanying drawings below.

[0016] Taking the NEPE / HTPB / EDPM system as an example, NEPE is nitrate plasticized polyether, HTPB is hydroxyl-terminated polybutadiene, and EDPM is EPDM rubber. Propellant / liner interface crack stress intensity factor.

[0017] Step 1, sample preparation: sample selection and block making, test block slicing and cutting. When selecting samples and making blocks, select samples containing propellant / lining interface of different ages. The samples are cuboid test blocks containing propellant, liner, and thermal insulation layer. The specification is 10mm×10mm×20mm. The length direction is consistent with the horizontal direction of the propellant / liner interface. When slicing and cutting the test block, use a microtome to cut the test block into slices with a thickness of 1 mm, and cut the slices through a stamping die to obtain a propellant / lining interface sam...

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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 [0001] The invention relates to a solid rocket motor structural integrity and storage life evaluation technology, in particular to a propellant / lining interface crack critical strength stress factor detection method. Background technique [0002] Usually, a wall-mounted cast solid rocket motor is mainly composed of a casing, a thermal insulation layer, a liner and a propellant, and the interface bonding performance of the propellant / liner is a key factor determining the overall life of the engine. The fusion and expansion of microvoids and microcracks at the propellant / liner interface under load is the main cause of interfacial debonding. The interfacial debonding of the propellant / liner directly reflects the interfacial fracture characteristics of the propellant / liner. The action process is complex and the evaluation index is uncertain. Therefore, the interfacial fracture characteristics of the propellant / liner are still in the exploration stage. Contents ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/00G01N3/06
Inventor 庞爱民张峰涛池旭辉彭松杨根杜锡娟朱学珍
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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