Nonlinear system guidance

This work is motivated by aircraft guidance problems. At a certain stage in our guidance procedure we want our output to track bounded time signals that are neither outputs of exosystems nor necessarily absolutely integrable functions of time. We are interested in a “stable inversion” of the nonlinear system. Since our systems are perturbations of “pure feedback systems” with outputs we find a solution to the stable inversion problem in two steps. The first step ignores the perturbation error and computes the causal principal part of the desired control and corresponding state trajectory. The second step computes the remaining control and states by finding a noncausal and stable solution to an “error driven dynamical equation”