Attitude stability of a class of partially flexible spinning satellites
Thomas W. Flatley, Goddard Space Flight Center, United States. National Aeronautics and Space Administration
National Aeronautics and Space Administration, 1969 - Science - 15 pages
What people are saying - Write a review
We haven't found any reviews in the usual places.
AERONAUTICS AND SPACE ANALYSIS angle angular velocity arbitrary Associate asymptotic ATTITUDE STABILITY beam stiffness bending boom is attached boom length boom stiffness factor boundary conditions calculated center of mass central body centrifugal CLASS OF PARTIALLY Compute configuration Consider constant corresponding curve deflected design chart elastic rod energy dissipation envelope Equilibrium Beam Equations Figure Flatley Goddard Space FLEXIBLE SPINNING SATELLITES forced rotation given Goddard Space Flight Greenbelt hand side hinged booms hinged rod increase integrate kinetic energy limiting lineal mass density linear maximum moments of inertia N-l n n=l j=l NATIONAL AERONAUTICS nominal spin axis Parameter PARTIALLY FLEXIBLE SPINNING plot points potential energy Power Series Solution presence of energy qualitative quantity radial booms radius reduce region rigid SATELLITES By Thomas SPACE ADMINISTRATION Space Flight Center spacecraft stability boundary stability criterion becomes symmetric tion torque values various spin rates