{"title":"模拟了热防护涂层在实际工况下的热变形和强度","authors":"L. Gracheva, V. Borisenko","doi":"10.1109/ICIASF.1997.644761","DOIUrl":null,"url":null,"abstract":"The thermal deformation of a heat-protective coating of polymer composite material with a phenol-formaldehyde matrix under conditions simulating the temperature-time interval of a spacecraft deorbiting is considered. It is shown that in the plane of reinforcing of the composite the maximum thermal deformations occur in a direction at 45/spl deg/ to the base of the fabric of the filler and with an increase in heating rate is a significant reduction in its amplitude. The residual relative thermal deformation of the heat-protective material tested according to the program of descent from a trajectory may reach 2% and more. The calculation of thermal stresses occurring in a layer of thermal protection during a spacecraft reentry in dense atmosphere is done using a method of the theory of elasticity with allowance made for physico-mechanical characteristics obtained for conditions simulating the actual ones. The tangential stresses, /spl tau//sub z/spl theta// and /spl tau//sub rz/, at the juncture of the frontal shield with the side surface and also at 1/5th of the length of the reentry vehicle at its both ends, at a depth of 3-3, 5 mm from the outer surface are shown to be the most dangerous for the strength of the heat-protective coating.","PeriodicalId":122871,"journal":{"name":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"16 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"1997-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"1","resultStr":"{\"title\":\"Thermal deformation and strength of heat-protective coatings under operating conditions simulating the real ones\",\"authors\":\"L. Gracheva, V. Borisenko\",\"doi\":\"10.1109/ICIASF.1997.644761\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"The thermal deformation of a heat-protective coating of polymer composite material with a phenol-formaldehyde matrix under conditions simulating the temperature-time interval of a spacecraft deorbiting is considered. It is shown that in the plane of reinforcing of the composite the maximum thermal deformations occur in a direction at 45/spl deg/ to the base of the fabric of the filler and with an increase in heating rate is a significant reduction in its amplitude. The residual relative thermal deformation of the heat-protective material tested according to the program of descent from a trajectory may reach 2% and more. The calculation of thermal stresses occurring in a layer of thermal protection during a spacecraft reentry in dense atmosphere is done using a method of the theory of elasticity with allowance made for physico-mechanical characteristics obtained for conditions simulating the actual ones. The tangential stresses, /spl tau//sub z/spl theta// and /spl tau//sub rz/, at the juncture of the frontal shield with the side surface and also at 1/5th of the length of the reentry vehicle at its both ends, at a depth of 3-3, 5 mm from the outer surface are shown to be the most dangerous for the strength of the heat-protective coating.\",\"PeriodicalId\":122871,\"journal\":{\"name\":\"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities\",\"volume\":\"16 1\",\"pages\":\"0\"},\"PeriodicalIF\":0.0000,\"publicationDate\":\"1997-09-29\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"1\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.1109/ICIASF.1997.644761\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"\",\"JCRName\":\"\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1109/ICIASF.1997.644761","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
Thermal deformation and strength of heat-protective coatings under operating conditions simulating the real ones
The thermal deformation of a heat-protective coating of polymer composite material with a phenol-formaldehyde matrix under conditions simulating the temperature-time interval of a spacecraft deorbiting is considered. It is shown that in the plane of reinforcing of the composite the maximum thermal deformations occur in a direction at 45/spl deg/ to the base of the fabric of the filler and with an increase in heating rate is a significant reduction in its amplitude. The residual relative thermal deformation of the heat-protective material tested according to the program of descent from a trajectory may reach 2% and more. The calculation of thermal stresses occurring in a layer of thermal protection during a spacecraft reentry in dense atmosphere is done using a method of the theory of elasticity with allowance made for physico-mechanical characteristics obtained for conditions simulating the actual ones. The tangential stresses, /spl tau//sub z/spl theta// and /spl tau//sub rz/, at the juncture of the frontal shield with the side surface and also at 1/5th of the length of the reentry vehicle at its both ends, at a depth of 3-3, 5 mm from the outer surface are shown to be the most dangerous for the strength of the heat-protective coating.