Although in recent years aircraft structures have tended to become rather complex, it is still possible in many cases to approximate the structure to a single cell tube with four corner booms during the initial design stages. Since extreme accuracy in computation is neither possible nor desirable in the early stages of design, the analysis has been restricted to structures with bulkheads which may be considered to be rigid in their own plane, although the effect of bulkhead flexibility can readily be included if thought to be of importance.

This note is concerned with the solution of the warping constraint problem for such structures without the necessity of solving a large number of linear simultaneous equations. The method is very similar to the Moment Distribution Method for continuous beams.