Effect of a guided rocket object’s lateral maneuver on the flight range and lateral deviation

This paper presents the results of testing of mathematical models that analyze the mass-center and about-mass-center cooperative motion parameters of a guided rocket object in different trajectory portions and determine the time evolution of its mass-centering and aerodynamic characteristics. The paper presents a mathematical model that allows one to form a yaw angle variation program in any aeroballistic trajectory portion and study the motion parameters in lateral yaw angle maneuvers. Use is made of mathematical and numerical simulation, which allows one to assess, at the initial design stage and based on the key design parameters, trajectory parameters, and flight control programs, the controllability of a rocket object and its flight range and basic characteristics and study the motion of its mass center and its motion about the mass center in horizontal and vertical maneuvers. The guided rocket object under consideration is a single-stage solid-propellant rocket that is to deliver a payload of desired mass to a given point at given values of kinematic trajectory parameters. The aerodynamic and aeroballistic characteristics are determined for a “normal” layout scheme with aerodynamic rudders to stabilize and control the rocket in flight. A verification is made of the author’s methodology for studying and characterizing a guided rocket object using a limited amount of available information of its mass and dimensions, the power characteristics of its solid-propellant sustainer engine, and the parameters of its aeroballistic trajectory. A study is conducted on the flight of a guided rocket object in lateral yaw angle maneuvers. The effect of a guided rocket object’ lateral maneuver on the flight range is estimated.