An assessment of spacecraft target mode selection methods

Mercer, Judith; Aglietti, Guglielmo S.; Remedia, Marcello; Kiley, Andrew

doi:10.1016/j.actaastro.2017.09.013

Cited by 6 publications

(3 citation statements)

References 10 publications

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“…Essentially these methods consist of modifying some of the parameters of the FE model, to improve the match between mode shapes predicted by the FEM and those retrieved during the physical test. Normally this exercise is performed only for a relatively small number of mode shapes (target modes) [38] that are particularly relevant. Reference to 'target modes' is important since it is not the assessment of measured quality (e.g.…”

Section: Vst As a Post-test Tool For Model Updatementioning

confidence: 99%

Spacecraft Structure Model Validation and Test Philosophy

et al. 2019

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This article examines the new practice of Virtual Shaker Testing (VST), starting from its motivation to its practical implementations and future possible implications. The issues currently experienced during large satellites' vibration testing are discussed, examining practical examples that highlight the coupling existing between the item under test and facility, and that are the basis for the motivation behind the new methodology (i.e. VST). VST is proposed as a way to bypass some of these issues, and here its use as a pre and post shaker test tool is discussed. In the article VST is applied to real test cases (Airbus' large spacecraft Bepi Colombo, built for the European Space Agency's first mission to Mercury), showing computations and real physical test data to illustrate the advantages of the methodology. These are mostly in terms of de-risking of the physical test campaigns (due to the capability to simulate realistically the future physical test thus reducing the probability of aborts and stops during the runs), and an improvement of the quality of the correlation process and related FEM update (resulting from the capability to separate the dynamics of the satellite from the effects of the test equipment); ultimately providing a tool to address questions arising from test response observations, which are many. This tool also offers the possibility to improve vibration testing using 6 DOF facilities. The article is concluded articulating a possible way forward to take maximum advantage of the new methodology, drawing a parallel with the current Satellite/Launch Vehicle Coupled Load Analysis cycles, and proposing a different design and validation philosophy.

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Section: Vst As a Post-test Tool For Model Updatementioning

confidence: 99%

Spacecraft Structure Model Validation and Test Philosophy

et al. 2019

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“…Different approaches to correlate reduced models of satellites have been presented in [5][6][7] to have more accurate results in CLA. In [8,9], the low stiffness attachment of a spacecraft with a vibration isolation system is studied. This type of mechanical interface configuration has the advantage of reducing the levels of vibrations that are transmitted to the spacecraft, but the drawback of decreasing the main natural frequencies of the attached spacecraft to the same frequency range as the modes of the launcher.…”

Section: Introductionmentioning

confidence: 99%

Dynamic coupling on the design of space structures

García-Pérez

Sanz-Andrés

Alonso

et al. 2019

Aerospace Science and Technology

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For the design of space structures, the dynamic coupling between equipment and the satellite (or between a satellite and the launcher) is usually avoided due to negative effects like high stresses produced by structural resonance. The usual procedure to assure the dynamic decoupling is by limiting the minimum value of natural frequency of the secondary structure to a value high enough above the main natural frequencies of the main structure. However, in some spacecraft configurations, it is unavoidable that some parts or equipment present natural frequencies close to the main natural frequencies of the spacecraft because these parts may be massive or may have a special interface design with low stiffness. This dynamic coupling provokes modifications on the modal behavior of the satellite, which can lead to a significant decrease in the first natural frequency of the entire satellite. To analyze this phenomenon, a representative but simple mathematical model is studied to evaluate the influence of the design parameters of space structures. Analytical expressions are obtained that can help to highlight the influence of the parameters. The results are demonstrated with the example of the UPMSat-2 satellite design.

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“…In CLA simulations, a model composed of the finite element model (FEM) of the launcher and a reduced model of the satellite is considered, and in this way, the influence of modal coupling between launcher and satellite is taken into account for more realistic environments. Different approaches to correlate reduced models of satellites have been presented in [59][60][61] to have more accurate results in CLA. In [62,63], the low stiffness attachment of a spacecraft with a vibration isolation system is studied.…”

Section: State Of the Artmentioning

confidence: 99%

Dynamic phenomena in the design of new concepts of space systems

Perez¹

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An assessment of spacecraft target mode selection methods

Cited by 6 publications

References 10 publications

Spacecraft Structure Model Validation and Test Philosophy

Spacecraft Structure Model Validation and Test Philosophy

Dynamic coupling on the design of space structures

Dynamic phenomena in the design of new concepts of space systems

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