Guidance of Ground to Ground Rockets Using Flight Path Steering Method

 

Slobodan Mandić

 

The ballistic flight of ground-to-ground rockets is sensitive to disturbances (total impulse variation, wind, thrust misalignment, etc.). As the range of ground-to-ground rockets increases, the accuracy of rockets free flight decreases. Requirements for the increase of the range and minimization of the impact point dispersions can be solved by adding the guidance and control system to rockets. Based on the differences between the real flight parameters and the calculated parameters for the nominal trajectory, the flight path angle correction algorithm is given in the paper. The efficiency of the proposed algorithm is verified by the numerical simulation of the rocket flight with the guidance and control system for a hypothetical rocket. The results of the simulation are obtained with the assumption that the SDINS instruments measure accelerations and angular rates of rockets without errors and noises.

Key words: multiple launch rocket system, guided rocket, rocket guidance, ground to ground rocket, impact point dispersion, flight path guidance.