A Proposed Scheme for Maneuver-Dependent Control of Stability

The article presents a maneuver-dependent stability control system. The system is actually an algorithm computing optimal output controls that satisfy stability requirements for aircraft performing maneuvers caused by input pilot control. The system uses a linear filter theory and a model following the technique. Minimization of a quadratic performance index in the state vector estimate error and the control vector yields the optimal control vector. A first-order perturbation approach is used to change the eigenvalues of the model to the desired ones by changing the elements of the model coefficient matrix (i.e., stability derivatives) which thus controls aircraft stability.