Orbit-injection-type trajectory design method of solid rocket based on elliptical transfer orbit

Abstract

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.

Description

technical field [0001] The invention relates to the field of launch vehicle ballistic design, in particular to a method for designing a solid rocket trajectory into orbit based on an elliptical transfer orbit. Background technique [0002] There are two types of launch vehicles: solid and liquid. From the perspective of quick response and emergency launch, solid launch vehicles have inherent advantages. For a solid launch vehicle with a three-stage solid + one-stage liquid configuration, the flight sequence corresponding to the traditional ballistic scheme is the first-stage active segment, the first-stage gliding segment, the second-stage active segment, the second-stage gliding segment, the third-stage The first gliding section, the third-stage active section, the third-stage second gliding section, and the final booster section. At the end of the third-stage active stage, the flight altitude is about 200km, and the final stage of the rocket needs to slide to a higher alt...

AI Technical Summary

Problems solved by technology

Generally, the first three stages of solid engines can only be exhausted and shut down. The position and speed deviation of the third stage shutdown point is relatively large. If the target orbit height is high, take 700km as an example. Accumulated errors in speed and position bring great pressure to the design of the guidance system in the final boost phase

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