Journal of Aeronautics & Aerospace Engineering
Open Access

Development of algorithms for controlling the orientation of a large elastic spacecraft

3^rd International Conference and Exhibition on Satellite & Space Missions

May 11-13, 2017 Barcelona, Spain

Alexander Panferov, Alexander V Nebylov and Sergey A Brodsky

Saint Petersburg State University of Aerospace Instrumentation, Russia

Posters & Accepted Abstracts: J Aeronaut Aerospace Eng

Abstract :

One of the promising directions for space study and exploration is the design of large spacecraft (SC), equipped with a powerful power block with high thermal output and efficient engines. The desire to distance the instrumentation section from the power plant determines the length of a large spacecraft assembly of 50 meters or more. The main mass of the spacecraft of more than 15 tons is concentrated in the instrument compartment (located in the same place as the payload) and a power plant. Structurally these two massive compartments are connected by a light rod with variable section. The difficulty of controlling such a spacecraft control is determined by its considerable elasticity and complexity of the spatial configuration. This paper considers problems of control law synthesis for the spacecraft orientation at large increments of the angular position in the non-uniform gravitational field of the Earth and in outer space. To solve these problems, the Pontryagin maximum principle is used. Solutions of problems of accurate stabilization of the spacecraft with errors on the order of tens of arc minutes which take into account the elasticity of all the elements relative to the three axes are presented. Recommendations are given for construction of actuators for stabilization system with high fuel efficiency. The basis for the synthesis of control laws are mathematical models of elastic spacecraft. These models are obtained based on a special software package, developed by the author over the past 10 years. The software allows developing a mathematical model of the spacecraft in the form of a system of differential equations with variable parameters or transfer functions for different phases of flight, based on the information about the construction, materials and the elastic properties of separate elements of the construction.

Biography :

Alexander Panferov is a Professor at Saint Petersburg State University of Aerospace Instrumentation, Russia and Senior Researcher at International Institute for Advanced Aerospace Technologies. He led many R&D projects in the field of Aerospace Instrumentation, Control Systems Design for the aero-elastic object, micromechanical gyroscopes and systems. He is a Co-author of more than 12 patents and 100 articles in reputed journals.

Email: panferov@aanet.ru