The invention discloses an
orbit-injection-type trajectory design method of a
solid rocket based on an elliptical
transfer orbit, and relates to the field of carrier
rocket trajectory design. The
orbit-injection-type trajectory design method comprises the steps that a
control variable is initialized; the perigee altitude of the elliptical
transfer orbit is fixed by fixing the final-stage second working hour; according to the set carrier
rocket fight
time sequence, the force-bearing condition in the rock
flight process is modeled, the speed and the position are subjected to numerical integration, and three-degree-of-freedom
particle trajectory calculation is conducted; the calculated speed and position are converted through a coordinate
system, whether the geocentric
radius vector magnitude, the absolute speed magnitude, the
orbit inclination angle and the current trajectory inclination angle meet the requirements or not is judged, if yes, related trajectory parameters such as the speed, the position, the flight program angle and the height are output, and a launch trajectory is designed; and otherwise, the
control variable is adjusted according to the difference between a current value and a target value, and iterative calculation is conducted until the requirements are met. By adopting the orbit-injection-type trajectory design method, the orbit-injection-type trajectory scheme design of the elliptical
transfer orbit of the
solid rocket can be quickly achieved.