The paper presents development and testing results of the optimized simplified computation method which uses the equal strength criterion in layers. Also it analyzes the prospects for introducing the three-layer honeycomb panels made of polymer composite materials in the aerospace systems. It considers main design cases in loading the honeycomb panels at the initial design stage taking into account specifics of their operation. The paper provides computation expressions. Their use is making it possible to determine the region of permissible values for the honeycomb panel optimal design parameters using limitations in the supporting skin strength, general and local stability loss and stability loss shear form for a flat honeycomb panel. An example of a graphical identification of the region of permissible values for the three-layer honeycomb panel parameters is provided. The paper demonstrates the method testing on the example of computing the helicopter engine fairing honeycomb panel made of the KMU-4L-type carbon fiber. It notes that the obtained results are providing satisfactory accuracy in determining the honeycomb composite panel rigidity and strength taking into account the binder sufficient in the engineering computation.

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