Spaceplanes are currently being designed by countries such as the USA, European Union, and China that can carry out the planning descent. The paper aim is a suborbital trajectories optimization of spaceplane associated with the termination of its launch into near-Earth orbit. The approach is an optimization problem solution of maximizing longitudinal flight range and side flight range using the differential evolution algorithm. The spaceplane trajectories are determined for problems without taking into account limitations and taking into account limitations on temperature, vertical g-force and the derivative of the trajectory angle. A comparison made between optimal trajectories, control laws and flight range using two-channel control and three-channel control.