Rapid generation of boost trajectory for boost-glide missile

A rapid boost trajectory generation algorithm is presented in this paper, considering the new requirements of hypersonic boost-glide missiles, such as the low terminal altitude, high velocity, and wide range coverage. The algorithm divides the boost trajectory into the longitudinal and lateral sub-planes. In the longitudinal sub-plane, the angle of pitch is designed as the time segment function. The maximum angle of attack and the pitch rate are selected as the key parameters to be determined. Newton iteration scheme is used to calculate the key parameters, according to the strict terminal altitude and velocity constraints. In the lateral sub-plane, an analytical calculation of the azimuth angle is proposed based on the theory of spherical triangle, which guarantees an initial aiming at the preselected target. Furthermore, new boost modes, such as intermittent boost mode and low altitude direct boost mode, are proposed. The trajectory characteristics and the application prospect are deeply analyzed. Finally, a three-stage solid rocket is used in the simulation. The results demonstrate that the algorithm can rapidly generate the boost trajectory for hypersonic boost-glide missile and achieve complex flight missions.