The problem of stabilizing and controlling rockets during the boost phase is considered. The rocket may be either fin-stabilized or spin-stabilized in open loop, with additional control surfaces available to enhance stability and disturbance rejection in closed loop. Flight conditions change drastically under forward acceleration. Instead of applying gain scheduling, direct linear timevarying methods, or nonlinear control strategies, the problem is reformulated into a linear timeinvariant system by changing the independent variable from time to distance. The control law, designed in the distance domain, is then transformed back to the time domain, resulting in a linear time-varying controller. Nonlinear simulations confirm the effectiveness of the method.