AbstractAn impulsive optimization method and the results of a suboptimal atmospheric guidance program are combined to produce an efficient solution to the aero‐braking problem. For a specified initial and final orbit, the solution determines: (1) the minimum of the sum of the magnitudes of the impulse vectors, (2) the optimal atmospheric entry and exit state vectors (subject to both equality and inequality constraints) and (3) the optimal coast times. Numerical solutions are presented to illustrate characteristics of the solutio