The following is a brief walkthrough of material related to the modeling of spacecraft dynamics with feedforward control as the self-awareness declaration for deterministic artificial intelligence. Specifically, the focus will be on the analysis of various sinusoidal trajectory methods. The methods utilized are the basic MATLAB sine generation function, a Taylor series implementation, and two alternate algorithms for higher speed, lower precision and lower speed, higher precision implementations. The chapter features a brief summary of previous work investigating the impact of step size on Euler and Body angles. This is followed by a high level overview of Euler angle theory, quaternions, direction cosine matrices, kinematics, and dynamics to form a mathematical basis for the core material. With the numerical basis for the modeling efforts outlined, the results of running a SIMULINK model of spacecraft dynamics with feedforward control will be briefly analyzed and explored. The analysis will cover the impacts of varying step size with various sinusoidal trajectory generation methodologies.
Part of the book: Deterministic Artificial Intelligence
This manuscript contains a brief introduction of Control Moment Gyroscopes followed by the mathematical basis for potential singularities and an analysis of how skew angle variability may impact their occurrence. MATLAB is utilized as the primary modeling tool along with WolframAlpha for mathematical derivations of matrix determinants. The results of the modeling efforts show that a uniform skew angle of 90° allows a high maximum angular momentum. Additionally, we attempt to show that having two CMGs at a skew angle of zero could result in similar gains as a uniform 90° configuration and briefly introduce singularity penetration.
Part of the book: Advances in Spacecraft Attitude Control