Abstract
Future space telescopes require tight thermomechanical stability. The thermal analysis may be based on a nonlinear steady solution with a superimposed linear transient perturbation. This linearity allows frequency domain (FD) thermal solutions that retain high resolution when scaled. Linearity allows generality through superposition. Linear superelements can represent subsystems and thereby simplify interfaces. The (rare) prior spacecraft FD thermal analyses have been with N×N system matrices, converting lumped parameter (LP) time domain models to FD. This paper includes continuously distributed resistance and capacitance elements. Exact distributed element results differ greatly from LP renditions at higher frequency. Two FD methods are used together: a 2×2 matrix method with a bridge to an N×N matrix method. The 2×2 method allows the combination of elements in series/parallel configurations into overall elements. The 2×2 matrices can then be used in an N×N system matrix formulation. This paper includes FD analysis and programming methods, FD testing methods, and model to data comparisons. A thermal signal generator was developed for FD testing.
Published Version
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