Research Papers

Dynamic Modeling and Analysis of Spacecraft With Variable Tilt of Flexible Appendages

[+] Author and Article Information
Nicolas Guy

ONERA Centre de Toulouse,
Systems Control and
Flight Dynamics Department,
Toulouse 31055, France
e-mail: nicolas.guy@onera.fr

Daniel Alazard

Université de Toulouse, DMIA, ISAE
Toulouse 31400, France
e-mail: daniel.alazard@isae.fr

Christelle Cumer

Research Scientist
ONERA Centre de Toulouse,
Systems Control and
Flight Dynamics Department,
Toulouse 31055, France
e-mail: christelle.cumer@onera.fr

Catherine Charbonnel

Research Engineer
Thales Alenia Space, DRT/SO,
Cannes 06156, France
e-mail: catherine.charbonnel@thalesaleniaspace.com

1Corresponding author.

Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received June 26, 2012; final manuscript received November 7, 2013; published online January 9, 2014. Assoc. Editor: Evangelos Papadopoulos.

J. Dyn. Sys., Meas., Control 136(2), 021020 (Jan 09, 2014) (10 pages) Paper No: DS-12-1202; doi: 10.1115/1.4025998 History: Received June 26, 2012; Revised November 07, 2013

This article describes a general framework to generate linearized models of satellites with large flexible appendages. The obtained model is parameterized according to the tilt of flexible appendages and can be used to validate an attitude control system over a complete revolution of the appendage. Uncertainties on the characteristic parameters of each substructure can be easily considered by the proposed generic and systematic multibody modeling technique, leading to a minimal linear fractional transformation (LFT) model. The uncertainty block has a direct link with the physical parameters avoiding nonphysical parametric configurations. This approach is illustrated to analyze the attitude control system of a spacecraft fitted with a tiltable flexible solar panel. A very simple root locus allows the stability of the closed-loop system to be characterized for a complete revolution of the solar panel.

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Fig. 1

Spacecraft composed of a main body and an appendage

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Fig. 2

MDK” formulation

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Fig. 3

Appendage dynamic model MPA(s): block-diagram representation based on the residual mass DP,0A.

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Fig. 4

Inverse dynamic model of the satellite [MBA+B(s)]-1 at point B

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Fig. 5

The model H(s) for attitude control

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Fig. 7

Rotation of the appendage

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Fig. 8

Block-diagram representation of y1=cos α u1-sin α u2 with a minimal occurrence of τ2

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Fig. 9

Bode magnitude plot of the transfer between the three components of external torques (computed at Gtotal and written in ℜb) and the three components of the B absolute angular velocity, when α = 0 deg

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Fig. 10

Bode magnitude plot of the transfer between external torque on xb-axis at Gtotal and absolute angular acceleration of B on xb-axis for various title angle α

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Fig. 11

Validation model of the controlled satellite

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Fig. 12

Evolution of the poles of the closed-loop system, when α varies from 0 deg to 180 deg (i.e., τ2 ∈[0,1]).

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Fig. 13

Minimal LFR of system F(s)




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