Multi-Objective Optimization Applied to Real-Time Command Problem of Spacecraft Thrusters

Santos, Willer Gomes dos; Rocco, Evandro Marconi; Boge, Toralf; Benninghoff, Heike; Rems, Florian

doi:10.2514/1.a33178

Cited by 5 publications

(2 citation statements)

References 15 publications

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“…An alternative approach is a multi-objective optimization, as described in the literature [27,42] uses typically the Pareto front instead weight coefficient. For this purpose, two objective functions ( [ē], E[ē]) are considered separately in a two-objective optimization using Pareto front technique as depicted in Fig.…”

Section: Discussion and Resultsmentioning

confidence: 99%

Application of reliability-based robust optimization in spacecraft attitude control with PWPF modulator under uncertainties

Bohlouri

Jalali-Naini

2019

J Braz. Soc. Mech. Sci. Eng.

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The main objective of this paper is to enhance the robustness of an on-off attitude control under uncertainties while limiting the probability of failure in attitude control. To do this, the concept of system optimization is utilized for detailed engineering of spacecraft control using reliability-based robust design optimization (RBRDO). The probability of failure of the attitude control is chosen by the system designer as the input of the RBRDO algorithm. The single-axis spacecraft attitude is controlled using a combination of the observer-based anti-windup modified PI-D with pulse-width pulse-frequency modulator in the presence of external disturbance. The on-off thruster is modeled with a delay followed by a second-order transfer function. The input frequency of the thruster is limited to 50 Hz. The uncertain parameters are given as the spacecraft moment of inertia, thrust level, and thruster delay. The controller gains are determined by using traditional, robust, and reliability-based robust design optimizations under uncertainties and disturbance. The simulations are carried out using quasi-normalized equations, along with reducing problem variables and computational burden, to obtain more applicable results for a preliminary design. The traditional optimization gives the highest pointing accuracy without uncertainty, whereas the robust optimization obtains an approximately flat behavior for the mean of absolute pointing error under uncertainties. Under this situation, RBRDO could satisfy the prescribed reliability with a small loss in accuracy for the on-off attitude control of spacecraft, but under system limitations.

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Section: Discussion and Resultsmentioning

confidence: 99%

Application of reliability-based robust optimization in spacecraft attitude control with PWPF modulator under uncertainties

Bohlouri

Jalali-Naini

2019

J Braz. Soc. Mech. Sci. Eng.

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“…During a guest scientist's work in the OOS-Group, a multiobjective optimation algorithm for thruster management was applied to uncooperative rendezvous [45,46]. The software was integrated into the GNC system Simulink model and tested with EPOS 2.0 [47][48][49].…”

Section: Multiobjective Optimizationmentioning

confidence: 99%

10-Year Anniversary of the European Proximity Operations Simulator 2.0—Looking Back at Test Campaigns, Rendezvous Research and Facility Improvements

et al. 2021

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Completed in 2009, the European Proximity Operations Simulator 2.0 (EPOS 2.0) succeeded EPOS 1.0 at the German Space Operations Center (GSOC). One of the many contributions the old EPOS 1.0 facility made to spaceflight rendezvous is the verification of the Jena-Optronik laser-based sensors used by the Automated Transfer Vehicle. While EPOS 2.0 builds upon its heritage, it is a completely new design aiming at considerably more complex rendezvous scenarios. During the last ten years, GSOC’s On-Orbit-Servicing & Autonomy group, who operates, maintains and evolves EPOS 2.0, has made numerous contributions to the field of uncooperative rendezvous, using EPOS as its primary tool. After general research in optical navigation in the early 2010s, the OOS group took a leading role in the DLR project “On-Orbit-Servicing End-to-End Simulation” in 2014. EPOS 2.0 served as the hardware in the loop simulator of the rendezvous phase and contributed substantially to the project’s remarkable success. Over the years, E2E has revealed demanding requirements, leading to numerous facility improvements and extensions. In addition to the OOS group’s research work, numerous and diverse open-loop test campaigns for industry and internal (DLR) customers have shaped the capabilities of EPOS 2.0 significantly.

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Hardware-in-the-Loop Rendezvous Tests of a Novel Actuators Command Concept

et al. 2016

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Multi-Objective Optimization Applied to Real-Time Command Problem of Spacecraft Thrusters

Cited by 5 publications

References 15 publications

Application of reliability-based robust optimization in spacecraft attitude control with PWPF modulator under uncertainties

Application of reliability-based robust optimization in spacecraft attitude control with PWPF modulator under uncertainties

10-Year Anniversary of the European Proximity Operations Simulator 2.0—Looking Back at Test Campaigns, Rendezvous Research and Facility Improvements

Hardware-in-the-Loop Rendezvous Tests of a Novel Actuators Command Concept

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