Polynomial feedback controls for large-angle, nonlinear spacecraft attitude maneuvers are developed. A five- body configuration consisting of an asymmetric spacecraft and four reaction wheels is considered. Attention is restricted to the momentum transfer class of internal control torques; this, in conjunction with the choice of Euler parameters as attitude coordinates, permits several important order reduction simplifications. Three numerical examples are included to illustrate applications of the concepts presented. APID large-angle attitude maneuvers have become in- creasingly important to the success of many current and future spacecraft missions. These maneuvers are characterized by nonlinear behavior, however, resulting in a control prob- lem that is likewise nonlinear. One approach to feedback con- trol of nonlinear motion is gain scheduling in which the control history is divided into segments, each determined by its own set of linear gains. A more attractive approach is con- trol of the entire nonlinear maneuver by a single set of gains. For the latter approach, a method is presented whereby the optimal nonlinear control problem is solved in polynomial feedback form and a suboptimal control law is determined by truncation. Currently there are two approaches used to deter- mine the polynomial coefficients for the control. One is to ex- pand the coast-to-go functional as a polynomial in the states and then recursively solve the Hamilton- Jacobi-Bellman equa- tion, as discussed by Willenstein,1 Dabbous and Ahmed,2 and Dwyer and Sena.3 In the method used here,4 the control itself is expanded as a polynomial and the coefficients determined recursively from the costate equations.