INFLUENCE OF STRUCTURAL ELASTICITY ON ATTITUDE, STABILITY AND DRIFT OF SPACECRAFT.
Final scientific rept. 1 Jun 65-31 May 67,
LOUVAIN UNIV (BELGIUM) INSTITUT DE MECANIQUE APPLIQUEE
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The effect of the spin on the behavior of an elastic satellite has been investigated in different cases of external alternating torques. A solution on analog computer was further obtained for the equations of vibration of the elastic parts of a spin stabilized spacecraft. The effect of the magnetic field on the motion of a spin stabilized satellite has been treated in a first approximation as for a rigid body defined from the average configuration. A rigorous treatment of an elastic satellite, and the stability thereof investigated in Lia pounov sense. In view of the following, and further investigations in this field, a chapter has been devoted to finding an approximate solution for systems of quasilinear ordinary differential equations. An investigation of the effect of orbital ellipticity on the behavior of an elastic satellite has been considered and a thorough analysis made first for a rigid body, where discrepancies have been found, as far as conditions of stability are concerned, with existing literature. The problem of the controlled thrust on an elastic slender booster has been considered, and the equations written in the general case where several differently located sensors control the thrust angle, while fuel sloshing is being taken into account. The treatment of the booster as a Timoshenko beam leads to a system of linear differential equations, whose treatment as an eigenvalue problem has been investigated in terms of operators in matrix notation. Author
- Unmanned Spacecraft