Space Environment Modelling and Torque-Optimal Guidance for CubeSat Applications

Abstract

CubeSats and nano-satellites provide flexible low-cost platforms for the academic and scientific communities to conduct cutting-edge research in the harsh environment of space. The mission life of nano-satellites is often limited by the attitude actuators, and it is therefore beneficial to reduce torque and angular momentum usage during reorientation maneuvers.In this capacity, a computationally lightweight torque-optimal guidance algorithm was formulated, solved using pseudospectral methods, and validated in a MATLAB-Simulink environment. A low-computation atmospheric density model, developed in support of this research, was extensively validated via performance assessment of passive CubeSat aerostabilization.Results indicate that this torque-optimal guidance algorithm demonstrates substantial improvements in performance and pointing accuracy over an Eigenaxis controller for similar maneuvers, with low to moderate computational overhead. In doing so, it presents a significant advancement towards the development of intelligent GN&C systems for small satellites.iii I n m em o r yo fC o l um b i aa n dC h a l l e n g e r . T h i s r e s e a r c h i sd e d i c a t e d t o t h o s ew h oh a v e t a u g h t m e t h a t t r u eh a p p i n e s s i n l i f e i s n o ta b o u tr e a c h i n gad e s t i n a t i o n ,b u t i n m a k i n g m em o r i e s f r omt h ea d v e n t u r e sa n d c h a l l e n g e sd u r i n gt h e j o u r n e yt o w a r d s i t . S i c i t u ra da s t r a i v