Date of Award

Spring 1986

Document Type

Thesis

Department

Mechanical & Aerospace Engineering

Program/Concentration

Engineering Mechanics

Committee Director

Chuh Mei

Committee Member

A. Sidney Roberts, Jr.

Committee Member

Jerrold M. Housner

Call Number for Print

Special Collections; LD4331.E56O25

Abstract

The planar liberational dynamics of an arbitrary spacecraft with deployable hinged appendages is presented here both analytically and numerically. The system model consists of a central rigid satellite moving about the earth in a circular orbit at a uniform orbital rate. Attached to the satellite are two unfolding rigid booms with specified mass and length. Tip masses are included at the ends of each boom and deployment is driven by torsional springs at both frictionless hinge points. The equations of motion are developed for both a single- and double-appendage model through the use of Lagrange's equations. The formulation accounts for large angle rotations, Coriolis effects, and the gravitational gradient. Utilizing Newtonian mechanics, the equations of motion for the deployment of a single massless boom are developed and compared with the Lagrangian formulation for validation purposes, The resulting nonlinear, coupled governing equations are not subject to closed-form solutions and are thus integrated numerically. Nondimensional parameters are defined to simplify the single appendage analysis and the equations are linearized about prescribed positions to study the stability of the system. The investigation is applied to the Space Shuttle based deployment of rigid truss-like members. Results indicate that spacecraft inertia parameters, appendage mass and length, deployment velocity, and initial conditions all exhibit considerable influence on the system response. The resulting librational motion is directly related to the size of the deployable payload and gravitational forces lead to vehicle stabilization. These findings may be helpful in assessing orbital effects during the deployment of large space structures or on the motion of satellites with robotic manipulator arms.

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DOI

10.25777/jkxt-e045

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