A Dissipative Control Design for Jupiter Icy Moons Orbiter

2007 ◽  
Vol 129 (4) ◽  
pp. 559-565 ◽  
Author(s):  
Jianjun Shi ◽  
Atul G. Kelkar
Keyword(s):  
Dynamic Model ◽  
Nonlinear Dynamic ◽  
Concept Design ◽  
Nonlinear Dynamic Model ◽  
Icy Moons ◽  
Guaranteed Stability ◽  
Body Dynamics ◽  
Dissipative Control ◽  
Flexible Body Dynamics ◽  
Exhaustive Study

This technical brief presents a nonlinear dynamic model of Jupiter Icy Moons Orbiter (JIMO), a concept design of a spacecraft intended to orbit the three icy moons of Jupiter, namely, Europa, Ganymede, and Callisto. The work presented in this paper represents a part of a feasibility study conducted to assess control requirements of the JIMO mission. A nonlinear dynamic model of JIMO is derived that includes rigid body as well as flexible body dynamics. A nonlinear dissipative control law with guaranteed stability is used to perform a representative in-orbit maneuver. The results presented are part of an exhaustive study conducted to evaluate various controller designs.

Feedback Linearization Based Generalized Predictive Control of Jupiter Icy Moons Orbiter

2008 ◽  
Vol 131 (1) ◽  
Author(s):  
Jianjun Shi ◽  
Atul G. Kelkar
Keyword(s):  
Dynamic Model ◽  
Predictive Control ◽  
Attitude Control ◽  
Nonlinear Dynamic ◽  
Feedback Linearization ◽  
Hybrid Control ◽  
Generalized Predictive Control ◽  
Concept Design ◽  
Nonlinear Dynamic Model ◽  
Icy Moons

This paper presents a nonlinear dynamic model of Jupiter Icy Moons Orbiter (JIMO), a concept design of a spacecraft intended to orbit the three icy moons of Jupiter, namely, Europa, Ganymede, and Callisto. The work in this paper represents a part of the feasibility study conducted to assess control requirements for the JIMO mission. A nonlinear dynamic model of JIMO is derived, which includes rigid body as well as flexible body dynamics. This paper presents a novel hybrid control strategy, which combines feedback linearization with generalized predictive control methodology in a two-step approach for attitude control of the spacecraft. This feedback linearization based generalized predictive control (FLGPC) law is used to accomplish a representative realistic in-orbit maneuver to test the efficacy of the controller. The controller performance shows that the FLGPC is a viable methodology for attitude control of a similar class of spacecraft. The results presented are a part of exhaustive study conducted to evaluate various controller designs.

Analysis of Tourism Ecology Capacity Based on the Nonlinear Dynamic Model

2009 ◽  
Vol 11 (2) ◽  
pp. 163-168
Author(s):  
Long LV ◽  
Zhenfang HUANG ◽  
Jiang WU
Keyword(s):  
Dynamic Model ◽  
Nonlinear Dynamic ◽  
Nonlinear Dynamic Model

scholarly journals Rattle dynamics of noncircular face gear under multifrequency parametric excitation

2021 ◽  
Vol 12 (1) ◽  
pp. 361-373
Author(s):  
Dawei Liu ◽  
Zhenzhen Lv ◽  
Guohao Zhao
Keyword(s):  
Dynamic Model ◽  
Parametric Excitation ◽  
Nonlinear Dynamic ◽  
Velocity Ratio ◽  
Harmonic Balance Method ◽  
Transmission Error ◽  
Dynamic Responses ◽  
Discrete Fourier Transformation ◽  
Nonlinear Dynamic Model ◽  
Face Gear

Abstract. A noncircular face gear (NFG) conjugated with a pinion is a new type of face gear which can transmit variable velocity ratio and in which two time-varying excitations exist, namely the meshing stiffness excitation and instantaneous center excitation. Considering the tooth backlash, static transmission error and multifrequency parametric excitation, a nonlinear dynamic model of the NFG pair is presented. Based on the harmonic balance method and discrete Fourier transformation, a semi-analytic approach for the nonlinear dynamic model is given to analyze the dynamic behaviors of the NFG. Results demonstrate that, with increase in the eccentric ratio, input velocity and error amplitude, the NFG will undergo a non-rattle, unilateral rattle and bilateral rattle state in succession, and a jump phenomenon will appear in the dynamic responses when the rattle state of the gears is transformed from unilateral rattle to bilateral rattle.

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