Flight envelopes of a lifting space vehicle at constant-altitude hypersonic coasting flight for the purpose of aerorendezvous with initial relative heading angles at 0, 30, 60,..., and 180 deg are presented. Besides the final position, the final velocity vector (both magnitude and heading) also must be specified for aerorendezvous. Therefore, final conditions are very stringent and the coordinate-system rotation technique is used to ease the numerical computation and to save time. The two-point boundary-value problem resulting from the variational formulation is solved by using the direct shooting method. The flight envelopes are found to be functions of two angles: the initial position and the initial velocity heading of the space vehicle. Both are measured relative to the specified final velocity vector. The envelopes for 0 and 180 deg of initial relative heading angles are symmetric with respect to the longitudinal axis. There are two discontinuity points on each of the envelopes. The other flight envelopes are not symmetric, and each has one discontinuity point only.
