Design method for limit failure load of mechanical connection structure of ceramic matrix composite and high-temperature alloy under high-temperature thermal mismatch condition
A technology for mechanically connecting structures and composite materials, which is applied in the field of structural design of ceramic matrix composite materials, to achieve the effects of fast prediction methods, saving time and cost of testing, and getting rid of testing links
Active Publication Date: 2021-09-17
HARBIN INST OF TECH +1
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[0003] The purpose of the present invention is to propose a design method for the ultimate failure load of the mechanical connection structure between ceramic matrix composite material and superalloy under the condition of high temperature thermal mismatch, so as to solve the problems existing in the prior art
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[0058] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.
[0059] A design method for the ultimate failure load of a mechanical connection structure between a ceramic matrix composite material and a superalloy under high-temperature thermal mismatch conditions, the design method comprising the following steps:
[0060] S100. According to the geometric parameters, initial assembly parameters and ambient temperature of ceramic matrix composite materials and superalloy convex head or countersunk bolt fasteners, use ABAQUS s...
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The invention discloses a design method for a limit failure load of a mechanical connection structure of a ceramic matrix composite and a high-temperature alloy under a high-temperature thermal mismatch condition. A nonlinear constitutive model, a failure criterion and a material degradation model are written into a user subprogram UMAT file by adopting a Fortran language, and the user subprogram UMAT file is embedded into ABAQUS finite element software to realize progressive damage analysis of a ceramic matrix composite and a high-temperature alloy countersunk bolt fastener under a high-temperature tensile condition. The ultimate failure load of the C / SiC ceramic matrix composite and the high-temperature alloy bolt fastener under the condition of high-temperature thermal mismatch and the corresponding initial and final assembly pre-tightening force and clearance are obtained. Compared with the existing experimental characterization means of the ceramic-based composite material connection structure, the prediction method is quick and efficient, can remarkably save the test time consumption and cost, and can be popularized and applied to many technical fields such as aerospace, military and national defense, energy and chemical industry and the like.
Description
technical field [0001] The invention relates to a design method for the ultimate failure load of a mechanical connection structure between a ceramic matrix composite material and a high temperature alloy under the condition of high-temperature thermal mismatch, and belongs to the field of structural design of ceramic matrix composite materials. Background technique [0002] C / SiC ceramic matrix composites have the characteristics of high specific strength, high specific modulus, low density, moderate fracture toughness, excellent oxidation resistance and high temperature resistance, and are widely used in the thermal protection system and propulsion system of new high Mach number aircraft In components, it has incomparable advantages over traditional heat protection metal materials. Due to the limitation of the weaving process, it is difficult and expensive to manufacture large and complex ceramic matrix composite structural parts. How to realize the connection between compo...
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Login to View More IPC IPC(8): G06F30/23G06F111/10G06F113/26G06F119/08G06F119/14
CPCG06F30/23G06F2111/10G06F2113/26G06F2119/14G06F2119/08Y02T90/00
Inventor 孙茜赵淑媛孙新阳李明瑞
Owner HARBIN INST OF TECH