TY - GEN
T1 - Eliminating perigee rotation in J2 perturbed orbits with a constant radial acceleration
AU - Wilkins, Christopher C.
AU - Kapila, Vikram
PY - 2007
Y1 - 2007
N2 - In this paper, for Earth-orbiting spacecraft in inclined, elliptical orbits, we present a control technique that uses a constant specific thrust (i.e., acceleration) to eliminate the rotation of the perigee that occurs due to the J2 perturbation arising from Earth's oblateness. Specifically, by averaging the rate of change of orbital elements, originating from disturbing accelerations over one orbital period, we obtain an expression that relates the secular growth of the argument of the perigee to a constant radial acceleration control. This control is used to eliminate the secular growth of the argument of the perigee due to the J2 perturbation. To justify the framework proposed in this paper, we also provide analytical expressions for the secular growth of all orbital elements caused by constant accelerations in the radial, in-plane, and out-of-plane directions. Simulation results are presented to illustrate the efficacy of the radial acceleration control in eliminating the rotation of the perigee.
AB - In this paper, for Earth-orbiting spacecraft in inclined, elliptical orbits, we present a control technique that uses a constant specific thrust (i.e., acceleration) to eliminate the rotation of the perigee that occurs due to the J2 perturbation arising from Earth's oblateness. Specifically, by averaging the rate of change of orbital elements, originating from disturbing accelerations over one orbital period, we obtain an expression that relates the secular growth of the argument of the perigee to a constant radial acceleration control. This control is used to eliminate the secular growth of the argument of the perigee due to the J2 perturbation. To justify the framework proposed in this paper, we also provide analytical expressions for the secular growth of all orbital elements caused by constant accelerations in the radial, in-plane, and out-of-plane directions. Simulation results are presented to illustrate the efficacy of the radial acceleration control in eliminating the rotation of the perigee.
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U2 - 10.2514/6.2007-6844
DO - 10.2514/6.2007-6844
M3 - Conference contribution
AN - SCOPUS:37249068452
SN - 1563479044
SN - 9781563479045
T3 - Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007
SP - 5001
EP - 5013
BT - Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - AIAA Guidance, Navigation, and Control Conference 2007
Y2 - 20 August 2007 through 23 August 2007
ER -