Abstract
The paper presents a novel application of the State Dependent Riccati Equation (SDRE) guidance approach with state constraints for a chaser spacecraft in the close proximity of a passive target. The dynamics are described by full 6 degree of freedom rigid-body relative motion. The final trajectory is defined by a passively safe approaching cone, which acts as path constraint and follows the attitude motion of target. A Near Rectilinear Halo Orbit in the Earth-Moon system is the selected rendezvous scenario to fully validate the proposed solution, even though the parameters related to the constraints and weighting functions are kept as general as possible, thus applicable to other similar missions.
Highlights
In the past few years there has been an increased interest in space exploration
An international effort is undergoing to plan a mission to the Moon consisting in a target space station located in a near rectilinear halo orbit (NRHO) about the L2 Lagrangian points of the Earth - Moon system, and a lunar lander equipped with a rover collecting lunar samples and bringing them back to the station, to later be returned to Earth [2]
The target moves on a NRHO and we simulate rendezvous maneuvers both at the aposelene, as well as in the worst case condition, i.e. close to periselene
Summary
In the past few years there has been an increased interest in space exploration. In particular, the International Space Exploration Roadmap was proposed in February 2018 [1] indicating, as objectives, a permanent return to the Moon, and unmanned and manned missions to Mars.Within this context, an international effort is undergoing to plan a mission to the Moon consisting in a target space station located in a near rectilinear halo orbit (NRHO) about the L2 Lagrangian points of the Earth - Moon system, and a lunar lander equipped with a rover collecting lunar samples and bringing them back to the station, to later be returned to Earth [2]. The paper proposes and verifies a State Dependent Riccati Equation technique as an effective approach to the close range rendezvous in a three-body problem, with particular reference to the future Artemis program. 2. Section 3 describes the motion constraints introduced in the State Dependent Riccati Equation general algorithm.
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