Development and experimentation of LQR/APF guidance and control for autonomous proximity maneuvers of multiple spacecraft

Bevilacqua, Riccardo; Lehmann, Thomas; Romano, Marcello

doi:10.1016/j.actaastro.2010.08.012

Cited by 71 publications

(29 citation statements)

References 23 publications

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“…For comparison purposes, the same set of docking maneuvers has also been executed using an LQR controller [7][8][9][10][11]. The results show that the docking trajectories performed with the IDVD-SGRA guidance are characterized by a lower amount of total maneuver energy and fuel consumption with respect to the LQR.…”

Section: Introductionmentioning

confidence: 95%

“…In Table 1 are shown the initial positions and the initial masses of the two FSSs. To evaluate the IDVD-SGRA performances, for both types docking execution D1 and D2, the same maneuvers have been performed using an LQR controller [7][8][9][10][11]. Since such controller does not enforce any constraint on the maximum maneuver time, in order to ensure that this parameter is equal for all the controllers, we have first executed the dockings with the LQR then we have set the resulting maneuver times as t MAX for the IDVD-SGRA (Table 1).…”

Section: Test Casesmentioning

confidence: 99%

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A near-optimal guidance for cooperative docking maneuvers

2014

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Section: Introductionmentioning

confidence: 95%

Section: Test Casesmentioning

confidence: 99%

A near-optimal guidance for cooperative docking maneuvers

2014

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“…In this section, before discussing more advanced techniques, we briefly review the classical linear quadratic regulator (LQR), which is frequently considered for attitude stabilization [47]- [50]. In this case, the task of the control function is to provide the force and torque commands which will be executed by the reaction wheels to correct the deviations of the actual state vector from the nominal one, compensating also the effects of disturbances and errors.…”

Section: Linear Quadratic Regulatormentioning

confidence: 99%

“Flyable” Guidance and Control Algorithms for Orbital Rendezvous Maneuver

Capello

Dabbene

Guglieri

et al. 2018

SICE Journal of Control, Measurement, and System Integration

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: Rendezvous orbital maneuvers are planned operations which intend to make two spacecraft meet, while avoiding collisions. Aspects such as trajectory safety and robustness, as well as obstacle avoidance, are fundamental for the mission success. The aim of this paper is to provide an overview of some recent algorithms for guidance and control systems, and also their combined exploitation, which can provide significant enhancements. This overview focuses on those algorithms that are characterized by key selected features: the discussed schemes guarantee low computational effort, low fuel consumption, and high safety and robustness. Different experimental setups, which can be used to evaluate the performance of the considered algorithms, are also taken into account and presented.

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“…5), actuated by compressedair thrusters. More details on the FSS testbed hardware and software architecture were reported in [35,36].…”

Section: A Experiments Setupmentioning

confidence: 99%

Experimental Characterization of Inverse Dynamics Guidance in Docking with a Rotating Target

Wilde

Ciarcià

Grompone

et al. 2016

Journal of Guidance, Control, and Dynamics

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The performance of an inverse dynamics guidance and control strategy is experimentally evaluated for the planar maneuver of a "chaser" spacecraft docking with a rotating "target." The experiments were conducted on an airbearing proximity maneuver testbed. The chaser spacecraft simulator consists of a three-degree-of-freedom autonomous vehicle floating via air pads on a granite table and actuated by thrusters. The target consists of a docking interface mounted on a rotational stage with the rotation axis perpendicular to the plane of motion. Given a preassigned trajectory, the guidance and control strategy computes the required maneuver control forces and torque via an inverse dynamics operation. The recorded data of 150 experimental test runs were analyzed using two-way analysis of variance and post hoc Tukey tests. The metrics were maneuver success, vehicle mass change, maneuver duration, thruster duty cycle, and maneuver work. The results showed that the guidance and control algorithm provided robust performance over a range of target rotation rates from 1 to 4 deg ∕s. = maximum available torque, N · m T z = chaser torque about z axis of laboratory coordinate system, N · m t = maneuver time, s t D = total duration of docking maneuver, s t DA = duration of final docking approach, s t FF = duration of free-flight phase, s t f = final maneuver time, s W = maneuver work, J x C ; y C T = planar position vector of chaser center of mass in laboratory coordinate system, m x T ; y T T = planar position vector of the target center of rotation in laboratory coordinate system, m x; y; z = Cartesian coordinate system fixed in laboratory x 0 ; y 0 ; z 0 = Cartesian coordinate system fixed to chaser spacecraft simulator x 0 0 ; y 0 0 ; z 0 0 = Cartesian coordinate system fixed to target object γ = auxiliary maneuver targeting angle, rad Δm = chaser mass change, kg Δr = positioning tolerance for completion of docking maneuver, m Δt DA = extended maneuver time beyond nominal maneuver time, s Δt G = time step of the guidance algorithm, s ζ = auxiliary maneuver targeting angle, rad θ C = chaser orientation angle in relation to laboratory coordinate system, rad θ T = target orientation angle in relation to laboratory coordinate system, rad χ ij = thruster activity for thruster j at time step ∈ 0; 1, s ω T = target object angular rate, rad∕s

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Development and experimentation of LQR/APF guidance and control for autonomous proximity maneuvers of multiple spacecraft

Cited by 71 publications

References 23 publications

A near-optimal guidance for cooperative docking maneuvers

A near-optimal guidance for cooperative docking maneuvers

“Flyable” Guidance and Control Algorithms for Orbital Rendezvous Maneuver

Experimental Characterization of Inverse Dynamics Guidance in Docking with a Rotating Target

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