Quaternion based attitude control and suboptimal rendezvous guidance on satellite proximity operation

Moon, Gun-Hee; Lee, Byung-Yoon; Tahk, Min-Jea; Shim, David Hyunchul

doi:10.1109/ecc.2016.7810620

Cited by 3 publications

(3 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…23, and the bounds on the reaction wheels angular momentum and its variation, Eq. (25)- (26). Each one of these constraints is discretized with a time grid within each interval, k. The LOS constraint is gridded with n L equally spaced subintervals of duration T L =T /n L at which the constraint is imposed…”

Section: Discretization Of Time Continuous Constraintsmentioning

confidence: 99%

“…Sliding mode control has also been explored by [23]. References [24,25,26,27] proposed a two stages approach, first they used an optimal control method for the translational motion, LQR in [24,25,26] or convex optimization in [27], and then they designed an attitude controller to obtain the orientations demanded by the translational plan. Reference [28] proposed a covering map to convert the original differential equations into two coupled equations evolving on a 3-D Lie group, this map is applicable to 6-DOF rendezvous.…”

Section: Introductionmentioning

confidence: 99%

“…Amongst the previous works, dual quaternions, which contain information of both translational and rotational states, were used in [17,19]. Concerning the number of thrusters, [17,20,19] assumed a pair of them available on each direction, six in total, whereas [24] considered four thrusters and [25,27,26,22,29] studied the case of single-thruster operations. The results of [28] are applied to both a classical six thrusters configuration and a single thruster one.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

A flatness-based predictive controller for six-degrees of freedom spacecraft rendezvous

et al. 2020

View full text Add to dashboard Cite

This work presents a closed-loop guidance algorithm for six-degrees of freedom spacecraft rendezvous with a passive target flying in an eccentric orbit. The main assumption is that the chaser vehicle has an attitude control system, based on reaction wheels, providing the necessary torque to change its orientation whereas the number of thrusters is arbitrary. The goal is to design fuel optimal manoeuvres while satisfying operational constraints and rejecting disturbances. The proposed method is as follows; first, the coupled translational and angular dynamics are transformed to equivalent algebraic relations using the relative translational states transition matrix and the attitude flatness property. Then, a direct transcription method, based on B-splines parameterization and discretization of time continuous constraints, is developed to obtain a tractable static program. Finally, a Model Predictive Controller, based on linearization around the previously computed solution, is considered to handle disturbances. Numerical results are shown and discussed.

show abstract

Section: Discretization Of Time Continuous Constraintsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

A flatness-based predictive controller for six-degrees of freedom spacecraft rendezvous

et al. 2020

View full text Add to dashboard Cite

show abstract

Time Shift Governor for Constrained Control of Spacecraft Orbit and Attitude Relative Motion in Bicircular Restricted Four-Body Problem

Kim,

Kolmanovsky,

Girard

2024

2024 American Control Conference (ACC)

View full text Add to dashboard Cite

Real-Time Fuel Optimization and Guidance for Spacecraft Rendezvous and Docking

Oumer

Kim

2022

Aerospace

View full text Add to dashboard Cite

Autonomous rendezvous and docking (RVD) fuel optimization with field-of-view and obstacle avoidance constraints is a nonlinear and nonconvex optimization problem, making it computationally intensive for onboard computation on CubeSats. This paper proposes an RVD fuel optimization and guidance technique suitable for onboard computation on CubeSats, considering the shape, size and computational limitations of CubeSats. The computation time is reduced by dividing the guidance problem into separate orbit and attitude guidance problems, formulating the orbit guidance problem as a convex optimization problem by considering the CubeSat shape, and then solving the orbit guidance problem with a convex optimization solver and the attitude guidance problem analytically by exploiting the attitude geometry. The performance of the proposed guidance method is demonstrated through simulations, and the results are compared with those of conventional methods that perform orbit guidance optimization with attitude quaternion feedback control. The proposed method shows better performance, in terms of fuel efficiency, than conventional methods.

show abstract

Quaternion based attitude control and suboptimal rendezvous guidance on satellite proximity operation

Cited by 3 publications

References 5 publications

A flatness-based predictive controller for six-degrees of freedom spacecraft rendezvous

A flatness-based predictive controller for six-degrees of freedom spacecraft rendezvous

Time Shift Governor for Constrained Control of Spacecraft Orbit and Attitude Relative Motion in Bicircular Restricted Four-Body Problem

Real-Time Fuel Optimization and Guidance for Spacecraft Rendezvous and Docking

Contact Info

Product

Resources

About