use and numerical integration of Eqs. (16) will be little changed from that of the original equations f except that the joint velocities and accelerations with respect to the bodies they connect, £j^ f? J^x^ respectively, must be prescribed and hence £>f7 ^C determined from Eq. (5). To determine the spacecraft attitude with respect to an external frame, a set of first-order equations, such as Euler angle rate equations, must be added. We have found that as a check on the accuracy of the computer code, which can be lengthy, it is helpful to add a routine which determines total system angular momentum about the mass center and check for its conservation when no external torques are considered. References ^Hooker, W.W. and Margulies, M., The Dynamical Equations for an Af-Body Satellite, Journal of the Astronautical Sciences, Vol. 12, winter 1965, pp. 123-128. Hooker, W.W., A Set of r Dynamical Equations for an Arbitrary TV-Body Satellite Having r Rotational Degrees of Freedom, AIAA Journal, Vol. 8, July 1970, pp. 1205-1207. Fleischer, G.E. and Likins, P.W., Attitude Simulation for Systems of Hinge-Connected Rigid Bodies, Jet Propulsion Laboratory Tech. Rept. 32-1592, Pasadena, Calif., 1974. Conway, B.A., Tuliglowski, J.E., and Webber, P.D., Dynamics of Remote Orbital Capture, Proceedings ASS/AIAA Astrodynamics Specialist Conference, Lake Placid, N,Y. 1983.