Structure thermal design checking of solid rocket motor

According to thermal protection layer model with fixed thickness [4], the expression of the carbonization layer thickness is as follows:

x kt (1)

k H cv v v

=

( )T Tc df ( )T Tdi i

λ ρ

(2)

where, x is thickness of carbonization layer, t is operating time of solid rocket motor, λ is thermal conductivity, Tc is gas temperature, Tdf is the end temperature at decomposition district, Tdi is the initial temperature at decomposition district, Ti is initial temperature, ρv is density of thermal protecting material, H is heat of decomposition, cv is average specific heat of thermal protecting material.