Approximate analytical solutions of an axially moving spacecraft appendage subjected to tip mass

Abstract

Approximate solutions for vibrations of flexible beam-type appendages subjected to tip mass are studied while uniform and exponential profiles for arm deployment are simulated. Applying an equivalent dynamical system and following Lagrangian approach, the equations of motion of the system are derived as nonlinear ordinary differential equations (ODEs) (with time-varying coefficients), in which the effect of the tip mass can be considered as some nonlinearity added to the 'no tip mass' case dynamics. The approximate closed-form solutions are obtained through a novel methodology using a computer algorithm, in which the solutions of the 'no tip mass' case are expanded by imposing quadratic perturbations on the independent variable. The mean square of errors (MSEs) for the obtained approximate analytical solution is computed. Using this method, the amplitude and frequency of the arm response are presented by the algebraic equations, which help the parametric design of such systems. In addition, effects of tip mass as an indicator of nonlinearities added to the system dynamics, on the amplitude and frequency of the beam response, are investigated during arm deployment.

Effect of drive mechanisms on dynamic characteristics of spacecraft tracking-drive flexible systems

“…In order to improve model precision, Matsuno [11], Yang [12,13], Chalhoub [14], Diken [15], Shina [16], Ghaleh [17], Endoa [18] and Na [19] modeled the flexible structure as either a cantilevered beam or a clamped-free-free-free rectangular plate. They derived a partial differential equation and a set of boundary conditions that represent vibration of the flexible structure.…”