Nutational Stability of a Dual-Spin Satellite under the Influence of Applied Reaction Torques | Zendy

Peter M. Bainum | Zendy; J. V. Fedor | Zendy

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Nutational Stability of a Dual-Spin Satellite under the Influence of Applied Reaction Torques

Author(s) -

Peter M. Bainum,

J. V. Fedor

Publication year - 1973

Publication title -

journal of spacecraft and rockets

Language(s) - English

Resource type - Journals

SCImago Journal Rank - 0.758

H-Index - 79

eISSN - 1533-6794

pISSN - 0022-4650

DOI - 10.2514/3.61886

Subject(s) - spacecraft , aerospace engineering , spacecraft design , satellite , missile , space (punctuation) , aerospace , torque , dual (grammatical number) , systems engineering , reaction wheel , space exploration , propellant , space technology , engineering , computer science , mechanical engineering , physics , art , literature , thermodynamics , operating system

The nutational stability of a dual-spin satellite under the influence of an applied reaction torque is analyzed. It is assumed that since the solar paddle attachments to the hub of the spacecraft are not rigidly locked, the effect of the solar panels can be replaced by a constant reaction torque acting on the hub of the spacecraft. This could result in the satellite having an equilibrium motion about an axis displaced from the nominal axis of symmetry. The variational equations of motion are developed about such an equilibrium position using the SAS-A spacecraft as a model. Energy dissipation on the rotor as well as the main body is included. This nonautonomous set of differential equations are linearized and transformed to an autonomous set using the Lyapunov Reducibility Theorem. The stability of the kinematically similar system is examined numerically using representative SAS-A parameters for the case when either pair of solar panels is assumed to be loosely attached. Stability is verified for small system nutation angles (0.1 degree) although the time constant associated with the least damped mode is approximately one order of magnitude larger than that for the SAS-A system without the influence of the reaction torques.

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