Thermal Structure Strength Analysis of Nozzle of Solid Rocket Motor with the Coupled Algorithm

Table 1

Performance parameters of nozzle materials.

Component	Throat insert	Thermal insulation in divergent section	Thermal insulation in the back wall	Thermal insulation in convergent section	Case (shell)
Material	Puncture C/C	Carbon cloth winding	High silicon oxygen cloth winding	Carbon Fiber molding	30CrMnSiA
Modulus GPa	9	12.2	17	10.8	210
Poisson ratio	0.1	0.1	0.12	0.1	0.3
	1.95	1.45	1.65	1.4	7.8
Specific heat J/(kg·K)	2100	920	850	1000	473
Thermal conductivity W/(m·K)	85	1	0.6	1.5	50
^6	1	4.2	12	10	13