Abstract
Summary A matrix method of linear structural analysis is described for the calculation of stresses and deflections in an aircraft structure divided into a number of structural components (substructures). The necessity for dividing a structure into these components arises either from the requirement that different types of analysis have to be used on different components, or because the capacity of the digital computer is not adequate to cope with the analysis of the complete structure. In the present method each substructure is first analyzed separately, assuming that all common boundaries (joints) with the adjacent substructures are completely fixed; these boundaries are then relaxed simultaneously and the actual boundary displacements are determined from the equations of equilibrium of forces at the boundary joints. The substructures are then analyzed separately again under the action of specified external loading and the previously determined boundary displacements.
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