Spacecraft dynamics

The dynamics of spacecraft attitude control are presented in a text designed for use in a two-semester graduate-level course. The focus is on the formulation of equations governing the parameters of mathematical models of spacecraft dynamics. Each section consists of a statement of a principle, its derivation, and a sample practical application. Four sets of problems, which can be worked with or without the use of computers, are appended. The kinematical relationships underlying rigid-body dynamics are considered, and the effects of gravitational forces are discussed in detail; single-rigid-body or gyrostat spacecraft are treated using the angular-momentum principle. A more refined method for the solution of complex-spacecraft problems is developed, including consideration of generalized active and inertial forces, linearized dynamical equations, discrete multi-degree-of-freedom systems, lumped-mass models, spacecraft with continuous elastic components, and the use of the finite-element method for the construction of modal functions.