Guidance algorithms for autonomous rendezvous of spacecraft with a target vehicle in circular orbit

Giri

Proceedings of the Institution of Mechanical Engineers, Part G:

2023

This paper investigates the dynamics of on-track rendezvous and docking of two spacecraft, and stabilization using hybrid Coulomb control. Modeling electrostatic forces and torques for control of complex spacecraft geometries like cylinders is challenging. Point mass assumption of the spacecraft that disregards the chaser dynamics will lead to errors in force estimation during the terminal docking phase, resulting in a mission failure. This paper uses the effective sphere method to model Coulomb interactions between the chaser and the target. The method is coupled with the chaser’s tumbling motion about its body axes to develop a relationship between electrostatic force and attitude. The relative attitude dynamics of the chaser is then derived and incorporated into the system dynamics. Differential gravity and hybrid thrusters are used to stabilize the relative attitude of the two bodies. The charge-voltage relations are used to compute potential variations for the Coulomb control. An optimal linear quadratic tracking control is proposed for tracking a reference trajectory generated using solutions of Clohessy-Wiltshire-Hill’s equations. Numerical simulations are carried out for both non-linear and linear models of the Coulomb spacecraft to validate the proposed concept. Results have also been compared with an existing voltage feedback controller to demonstrate the merits and challenges of electrostatic actuation for rendezvous and docking.

Section: Control Lawmentioning

confidence: 99%

Section: Reference Trajectory Designmentioning

confidence: 99%

Optimal hybrid Coulomb control for on-track rendezvous and docking of spacecraft

Giri

Proceedings of the Institution of Mechanical Engineers, Part G:

2023

“…When there is no control (ux = uy = uz = 0), an analytical solution exists. Assuming that the initial relative position is r0 and relative velocity is v0, then the relative state of the spacecraft at time t can be obtained by (5) where Φrr、Φrv、Φvr and Φvv are the state translation matrixes, whose detailed expressions can be found in [22]. For complex on-orbit service missions, orbit transfer processes involve multiple maneuvers, producing a variety of trajectories with distinct geometry.…”

Section: Relative Motion Dynamicsmentioning

confidence: 99%

“…Based on the CW equation, numerous researchers proposed a series of orbit transfer strategies. Pearson proposed a multi-pulse glide algorithm for space shuttle rendezvous and docking [4], based on which, Hablani et al studied the guidance and navigation strategies for multi-pulse gliding and circular forced fly-around [5]. Wang et al enhanced and supplemented the multi-pulse glide algorithm by considering constraints such as safety speed, guidance error, and maximum acceleration [6].…”

Section: Introductionmentioning

confidence: 99%

The Modular Relative Orbit Design Method for Spacecraft Proximity Motion

Zhong

et al. 2022

J. Phys.: Conf. Ser.

This paper presents a modular relative motion trajectory design tool for proximity operation of on-orbit service spacecrafts. First, a series of commonly used relative motion trajectories are defined. The dynamics are solved such that each type of trajectory is encapsulated into different modules. The input parameters of each module include the key geometrical features, such as the initial position, desired final position, and flying time. Different modules are connected via the same position and velocity. The modular orbit design tool is able to cover most of the typical proximity operation scenarios. Following that, two notational on-orbit service missions are given as examples to describe the specific usage process of the tool. It includes three major steps, namely, determining the appropriate module sequence according to the mission requirements, designing the pending input parameters of each module by taking consideration of constraints, and computing the details of module sequence to generate relative trajectories. Compared with the traditional maneuver-optimized orbit design approach, the modular method has fewer parameters to solve. Additionally, the modular application tool is versatile and can be used for a variety of different on-orbit service missions. This tool is of great importance in standardizing the space operations.

“…A spacecraft travels through way-points on a trajectory to make use of the natural dynamics and to minimize fuel consumption. There are multiple tracking and control methods tested on orbit and offered in the literature [61][62][63][64][65][66][67][68][69].…”

Section: Glideslope R-bar and V-barmentioning

confidence: 99%

Model predictive control for spacecraft rendezvous and docking with uncooperative targets

Burak¹

Firstly, I would like to sincerely thank my supervisor for his continuous support.Secondly, I would like to thank Mr. Luca Simonini and Dr. Vincent Dubanchet from Thales Alenia Space for being inspirer leaders who have always shown their faith in me and who continuously supported my dreams to come true. Next, the core part of my thesis is achieved in DLR/German facilities. Hence, I would like to thank the head of GNC/Bremen department Dr. Stephan Theil, head of G&C department Dr. David Seelbinder for providing me the opportunity to conduct my experiments. In DLR, Dr. Markus Schlotterer had always been supportive in the test, and verification phase of the embedded systems. That was remarkable and I appreciate to receive his support. Last but not the least, I am grateful to have Prof. Jan Maciejowski in my thesis advisory committee. I would like to thank Prof Jan. for his support and enthusiasm for my work. ix "If I had one hour to save the world, I would spend 55 minutes defining the problem and only five minutes finding the solution."