AN ANALOG STUDY OF AnROTATING-SOLID-ROCKET CONTROL SYSTEM AND ITS APPLICATION TO ATTITUDE CONTROL OF A SPACE-VEHICLE UPPER STAGE

摘要

A study of the characteristics of a control system employing rotating-solid propellant rockets for control forces is presented. The particular control system studied was developed originally for the George C. Marshall Space Flight Center under a contract. An open-loop analysis as well as a closed-loop analysis of the control system is presented. The results of the open-loop analysis are given in the form of a nonlinear mathematical representation of the system's dynamic operation. This mathematical representation is used in the closed-loop study which is a guidance and control analysis of a typical vehicle system. The guidance and control analysis employs a guidance system simulation incorporating various nonlinearities present in the system, a three-dimensional trajectory simulation and six-degree-of-freedom rigid-body vehicle simulation, as well as the derived nonlinear simulation of the control system.