A new method for numerical integration of airplane equations of motion

I has been found in Ref. 1 that application of linear transformation methods to the integration of the airplane equations of motion can result in significant savings of computer time over more conventional methods. One of these methods, named the approximate inverse Laplace method, is applied below to the integration of rigid airplane equations of motion. These equations form a set of six simultaneous nonlinear differential equations. By expressing these equations consistently in terms of the dependent variables £7, a, 0, /3, <£, and \(/, it is possible to write these equations in the following form: Longitudinal (Body Axes)