Method of the accelerated calculation of spacecraft motion in the atmosphere with attached tether aerodynamic stabilizer

The method of the accelerated calculation of spacecraft motion in the atmosphere with attached tether aerodynamic stabilizer is considered. Method is based on artificial increase of the oscillation periods. The method allows reducing complexity of calculations in tens of times and allows reducing influence of a computing error on accuracy of numerical integration. The algorithm for aprioristic choice of the magnification factor of oscillation periods is offered.