Transient heat response analysis method for side window of aircraft flat plate

The invention discloses a transient heat response analysis method for a side window of an aircraft flat plate. The transient heat response analysis method comprises the following steps: firstly, establishing a finite element analytical model of the side window of the aircraft flat plate; secondly, loading the heat response analysis time of an aircraft flat plate model and material physical property; thirdly, apply heating boundary conditions and force boundary conditions on the side window of the aircraft flat plate based on APDL language; and fourthly, carrying out solution control and result after treatment on the heat response of the side window of the aircraft. According to the method, the heat response results (including a temperature field, a heat stress field, a heat strain field and a heat deformation field of the side window in the aerodynamic heat environment) of the side window of the aircraft flat plate can be calculated at a time through developed APDL command stream, and the defects of trouble, effort wasting, fallibility due to multiple times of loading of a user interface when the same problems occur can be avoided.