Session
Session 5: Education 1
Abstract
The design of most hardware-based spacecraft attitude simulators restricts motion in one or more axes. The problem addressed in this paper is how to design and build a reconfigurable spacecraft model and testbed to simulate the attitude control performance for any satellite. A new satellite attitude dynamics and control simulator and testbed was designed to facilitate unrestricted attitude control algorithm testing which solves the restricted motion problem by using a spherical rotor mounted on an air bearing for a 360°, 3-axis capable testbed. The simulator uses reaction wheels as the momentum exchange device in the satellite since most small satellites with attitude control capabilities use reaction wheels as the preferred means of momentum exchange. Inside the spherical rotor is a reconfigurable inertia model capable of simulating any spacecraft inertia within its design envelope. To establish the design envelope for allowable inertia values, data from over 60 satellites were included. While not all satellites are CubeSats, the emphasis of this paper is the benefit to the smaller CubeSat developer of a low-cost testbed for attitude control algorithm design, validation and demonstration.
Presentation
Design and Development of an Unrestricted Satellite Motion Simulator
The design of most hardware-based spacecraft attitude simulators restricts motion in one or more axes. The problem addressed in this paper is how to design and build a reconfigurable spacecraft model and testbed to simulate the attitude control performance for any satellite. A new satellite attitude dynamics and control simulator and testbed was designed to facilitate unrestricted attitude control algorithm testing which solves the restricted motion problem by using a spherical rotor mounted on an air bearing for a 360°, 3-axis capable testbed. The simulator uses reaction wheels as the momentum exchange device in the satellite since most small satellites with attitude control capabilities use reaction wheels as the preferred means of momentum exchange. Inside the spherical rotor is a reconfigurable inertia model capable of simulating any spacecraft inertia within its design envelope. To establish the design envelope for allowable inertia values, data from over 60 satellites were included. While not all satellites are CubeSats, the emphasis of this paper is the benefit to the smaller CubeSat developer of a low-cost testbed for attitude control algorithm design, validation and demonstration.
