Reference : Orbit Maintenance Strategies for Sun-Earth/Moon Libration Point Missions: Parameter S...
Dissertations and theses : Bachelor/master dissertation
Engineering, computing & technology : Aerospace & aeronautics engineering
Orbit Maintenance Strategies for Sun-Earth/Moon Libration Point Missions: Parameter Selection for Target Point and Cauchy-Green Tensor Approaches
Muralidharan, Vivek mailto [University of Luxembourg > Interdisciplinary Centre for Security, Reliability and Trust (SNT) > Space Robotics >]
Purdue University, ​West Lafayette, ​​USA
Master of Science in Aeronautics and Astronautics
Howell, Kathleen C.
Spencer, David A.
Frueh, Carolin E.
[en] Stationkeeping ; Circular Restricted Three-Body Problem ; Astrodynamics ; Stretching Direction ; Control ; Near Rectilinear Halo Orbits ; Halo Orbits ; Floquet Mode ; Libration Points ; Manifold Theory ; Guidance Navigation and Control
[en] The libration point orbits in the Sun-Earth/Moon system are formed by concurrent gravitational influences by various celestial bodies, originating in a nonlinear dynamical regime. Coupled with the unstable nature of the orbit, the impact of any perturbations are expected to increase rapidly. The feasibility of a flow-based, Cauchy-Green tensor control strategy for station-keeping is examined. An orbit consistent with the mission objectives is selected for examination. The station-keeping process is stochastic, thus Gaussian random errors are introduced for simulation. The evolution of a velocity perturbation over time is monitored, beyond which the attainable state in the accessible region nearest to the target state is employed as a feedback to compute the necessary full, three-component corrective maneuver. The application and appropriateness of single axis control maneuvers for orbit maintenance are also evaluated. The selection procedure for certain parameters such as tolerances and weighting values are developed to incorporate the available dynamical information, yielding a versatile and straightforward strategy. Weighting matrices within the target point approach are effective in influencing the station-keeping costs as well as size and direction of maneuvers. Moreover, selection of appropriate tolerance values in the application of the Cauchy-Green tensor exploits the dominant stretching direction of the perturbation magnitude to inform the maneuver construction process. The work is demonstrated in the context of the upcoming Aditya-1 mission to a Sun-Earth/Moon L1 halo orbit for solar observations and the James Webb Telescope to a Sun-Earth/Moon L2 halo orbit for astronomy.

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