基于高精度解析解的航天器热设计方法

For the thermal design requirements of microsatellites, the two-node dynamic thermal equilibrium equations are solved analytically based on a spherical two-layer lumped parameter model. Multiple harmonic approximations are used to deal with periodic outer heat flux boundaries to eliminate computational errors due to heat flux approximations. With a single linearization, the dynamic thermal equilibrium equations are solved directly and the analytical solution of the dynamic temperature is obtained with high accuracy. Numerical verification is performed using the fourth-order Runge-Kutta method. Based on the high-precision analytical solution, a design procedure for direct control of the spacecraft thermal condition-radiation parameters Is compiled and applied to the thermal design of a specific small satellite model. Simulations are performed to verify the feasibility and accuracy of the design scheme.