Nonlinear Control Tools for Low Thrust Orbital Transfer
نویسندگان
چکیده
We consider the problem of orbital transfer under propulsion constraints. The solution is arrived at by appealing to several recent nonlinear control design methods including backstepping, forwarding, and a modified form of JurdjevicQuinn control.
منابع مشابه
Thrust - Limited Optimal Three - Dimensional Spacecraft Trajectories
Several optimal three-dimensional orbital transfer problems are solved for thrust-limited spacecrafts using collocation and nonlinear programming techniques. The solutions for full nonlinear equations of motion are obtained where the integrals of the free Keplerian motion in three dimensions are utilized for coasting arcs. In order to limit the solution space, interior-point constraints are use...
متن کاملQuaternion-based Finite-time Sliding Mode Controller Design for Attitude Tracking of a Rigid Spacecraft during High-thrust Orbital Maneuver in the Presence of Disturbance Torques
In this paper, a quaternion-based finite-time sliding mode attitude controller is designed for a spacecraft performing high-thrust orbital maneuvers, with cold gas thrusters as its actuators. The proposed controller results are compared with those of a quaternion feedback controller developed for the linearized spacecraft dynamics, in terms of settling time, steady-state error, number of thrust...
متن کاملHigh-performance three-dimensional maneuvers control in the area of spacecraft
Contemporary research is improving techniques to maneuvers control in the area of spacecraft. In the aspect of further development of investigations, a high-performance strategy of maneuvers control is proposed in the present research to be applicable to deal with a class of the aforementioned spacecrafts. In a word, the main subject behind the research is to realize a high-performance three-di...
متن کاملAsymptotic Behavior of Time Optimal Orbital Transfer for Low Thrust 2-body Control System
In the studies of low thrust time optimal orbital transfer it was conjectured that, when the thrust modulus tends to zero, the product of this modulus by the minimum transfer time admits a finite limit. The purpose of the present note is to better frame the nature of this asymptotic behavior and to prove this conjecture.
متن کاملLow-Thrust Maneuvers for the Efficient Correction of Orbital Elements
In this study, low-thrust strategies aimed at the modification of specific orbital elements are investigated and presented. Closed loop guidance laws, steering the initial value of a given orbital element to a target value, are derived, implemented and tested. The thrust laws have been defined analyzing the Gauss form of the Lagrange Planetary Equations isolating the relevant contributions to c...
متن کامل