Vibration Reduction for Flexible Spacecraft Following Momentum Dumping With/Without Slewing

Banerjee, Arun K.; Pedreiro, Nelson; Singhose, William

doi:10.2514/2.4737

Cited by 44 publications

(10 citation statements)

References 13 publications

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“…Using solution (20), we can easily construct the analytic solution. It is inexpedient to construct a numerical solution subject to constraints (17) and (19) because the conditional extremum cannot give a solution that would be better than that obtained based on the unconditional minimization of function (15) in view of constraint (6). Numerical tests for the segments 0 2 …”

Section: Problem Formulationmentioning

confidence: 99%

“…For long-lived spacecraft with a low power-to-weight ratio, it is important to minimize the consumption of energy [17,20,25,26]. For observation satellites that maneuver much, it is important to minimize the maneuver time [5,6,8,9,16,18,19,21,23,24]. The most typical result in this field is bang-bang control, which may appear extremely sensible to simulation errors.…”

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confidence: 98%

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Optimal limited-rate slewing of a flexible spacecraft

Zakrzhevskii

2010

Int Appl Mech

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The paper presents an efficient method of finding the optimal program control for the reorientation of a spacecraft with flexible appendages at a limited slewing rate. The appendages are incorporated into the mathematical model based on the quasistatic approximation. The problem is solved analytically by parametrizing the functional of a multipoint boundary-value problem. The optimal solution is illustrated graphically for different parts of the attainability domains Introduction. Optimal rest-to-rest maneuvers of spacecraft with flexible appendages have long attracted the attention of researchers and are still of interest because new spacecraft designs, new effectors, new control systems are developed.A common practice is to combine feedforward and feedback controls for such systems. The deformation of flexible appendages can only be measured with distributed sensors. If a spacecraft is not equipped with such sensors, there can be no acceptable quality of feedback. Therefore, whether maneuvers of such spacecraft are successful is strongly dependent on the quality of feedforward control. In this field, a number of fundamental results have been obtained. They allow optimization based on various goal functions. For long-lived spacecraft with a low power-to-weight ratio, it is important to minimize the consumption of energy [17,20,25,26]. For observation satellites that maneuver much, it is important to minimize the maneuver time [5,6,8,9,16,18,19,21,23,24]. The most typical result in this field is bang-bang control, which may appear extremely sensible to simulation errors. Sometimes these goal functions are combined into one with weighted components [11].In some cases, it is important to minimize not the fuel consumption and maneuver time, but rather the moment perturbations of the spacecraft because of the vibrations of flexible appendages. The slewing of such spacecraft should be controlled in such a manner that no vibrations of the flexible appendages occur and affect the operation of the spacecraft equipment. First attempts to solve this problem using goal functions with various combinations of generalized coordinates of elastic displacements and their derivatives were made in the 1970s [2, 3, 10]. Later, it was proposed that feedforward control did not include spectral components of the spacecraft as a whole [7]. Modifications of this approach were applied to elastic nonlinear systems [22], but the residual vibrations were nevertheless significant [11]. The cited studies dealt only with one mode of elastic vibrations. Some relevant issues were analyzed in [12][13][14][15].The papers [4, 27] outline a method of designing an optimal slewing program that minimizes the relative accelerations of the flexible appendages of a spacecraft. The method allows for the infinite number of modes of elastic vibrations, not going beyond the finite-dimensional mathematical model. This is possible if the first several modes are described in the usual formulation and all the higher modes in the quasistatic formulation. Of separat...

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Section: Problem Formulationmentioning

confidence: 99%

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confidence: 98%

Optimal limited-rate slewing of a flexible spacecraft

Zakrzhevskii

2010

Int Appl Mech

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“…81,[161][162][163][164][165] Command shaping has also proven beneficial for spacecraft. 67,[69][70][71][73][74][75]95,97,99,100,106,109,115,[166][167][168][169][170] Input shapers were tested in space using the Middeck Active Control Experiment (MACE). 37,171,172 The MACE hardware was designed to represent a typical satellite with multiple pointing mechanisms.…”

Section: Example Applicationsmentioning

confidence: 99%

Command shaping for flexible systems: A review of the first 50 years

Singhose

2009

Int. J. Precis. Eng. Manuf.

371

183

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“…The objective is to show its application for this subject. Here, the input shaping technique, which has been successfully used to control vibration of flexible structures [21][22][23] but rarely for suppressing sloshing is introduced. Several types of input shaper, such as Zero Vibration (ZV), Zero Vibration and Derivative (ZVD) 24) and Extra Insensitive (EI) 25) are designed to achieve the objective.…”

Section: Case Using Advanced Control Algorithmmentioning

confidence: 99%

Dynamic Influence of Propellant Sloshing Estimation Using Hybrid: Mechanical Analogy and CFD

Dong

Wang

et al. 2009

Trans. Japan Soc. Aero. S Sci.

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Liquid propellant sloshing, which induces perturbations to dynamic behavior of spacecraft, is a serious problem. This paper proposes an approach based on equivalent mechanics theory and Computational Fluid Dynamics (CFD) technology to estimate the dynamic influence of propellant sloshing on spacecraft. A mechanical model was built by CFD technique and packed as a ''sloshing'' block utilized in the spacecraft Guidance Navigation and Control (GNC) simulation loop. The block takes the motion characteristics of the spacecraft as inputs and outputs perturbative force and torques induced by propellant sloshing. It is more convenient to utilize in analysis of the coupling effect between propellant sloshing dynamics and spacecraft GNC than CFD packages directly. A validation case is taken to validate the accuracy and the superiority of the approach. The deducing process is applied to practical cases, and the simulation results are presented to demonstrate the proposed approach is efficient in identifying the problems induced by sloshing and evaluating effectiveness of several typical schemes for suppressing sloshing.

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Vibration Reduction for Flexible Spacecraft Following Momentum Dumping With/Without Slewing

Cited by 44 publications

References 13 publications

Optimal limited-rate slewing of a flexible spacecraft

Optimal limited-rate slewing of a flexible spacecraft

Command shaping for flexible systems: A review of the first 50 years

Dynamic Influence of Propellant Sloshing Estimation Using Hybrid: Mechanical Analogy and CFD

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