Stabilizing an unstable orbit about L3 in the Sun, Earth, Moon system using linear constant gain feedback

Details Stabilizing an unstable orbit about L3 in the Sun, Earth, Moon system using linear constant gain feedback Stabilizing an unstable orbit about L3 in the Sun, Earth, Moon system using linear constant gain feedback

Dec 1979

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1979aifo.reptu....s&link_type=abstract

M.S. Thesis Air Force Inst. of Tech., Wright-Patterson AFB, OH. School of Engineering.

Computer Science

Feedback Control, Four Body Problem, Lagrange Coordinates, Orbital Mechanics, Satellite Orbits, Coordinate Transformations, Equations Of Motion, Librational Motion, Orbit Calculation, Orbital Mechanics

Scientific paper

Equations of motion for a satellite in a planar, elliptic four-body system are used to generate an orbit about L3. Initial conditions and a periodic reference orbit were found using a circular four-body model. Linear constant gain feedback is used to stabilize the orbit about L3 in the planar, elliptic four-body model. The computed L3 orbit is plotted against the reference orbit to assess the effectiveness of position, velocity and position/velocity feedback compensation systems. Also computed is the integrated control gain costs for each type of feedback system used. Long term stable motion near libration point L3 was achieved using position/velocity feedback compensation. Position and velocity feedback when used separately were ineffective as stabilizing feedback compensation systems. The integrated control gain costs also indicate that linear constant gain feedback is not an economical method to stabilize this periodic orbit about L3.

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