Gain-scheduled Steering Control Law for Variable Speed Control Moment Gyros

Kasai, Shinya; Kojima, Hirohisa

doi:10.2514/6.2013-4796

Cited by 3 publications

(3 citation statements)

References 9 publications

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“…A conventional application of the gyroscopic effect is stabilizing a ship's roll motion as discussed in [5] by Townsend and Shenoi. In aerospace and astronautic engineering, the gyroscopic effect is used in attitude guidance system for spacecraft and satellites in [6], Lemus and Berry in [7] applied it to develop balance assistance device for human.…”

Section: Introductionmentioning

confidence: 99%

A Control Simulation for a Bicycle with an Active Stabilizing Assistant System

Chen¹,

Chu²,

Chien³

2018

dtetr

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In this research, a design of an active stabilizing assistant system (ASAS) for a bicycle is proposed. Using gyroscopic effects of two spinning flywheels, the ASAS generates assistant torques which can assist the rider to stabilize his/her bicycle in various riding strategies. Hence, it can improve the riding performance and also the rider's safety. To simulate the dynamic behaviors of the system, a model of a bicycle-rider system with the ASAS on the rear seat is developed. This model consists of 14 degrees of freedom and is derived by using Lagrange equations.

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Section: Introductionmentioning

confidence: 99%

A Control Simulation for a Bicycle with an Active Stabilizing Assistant System

Chen¹,

Chu²,

Chien³

2018

dtetr

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“…The authors previously proposed a mode-scheduling steering law for VSCMGs, where the suitable set of initial gimbal angles is selected in the constant-speed control moment gyro (CSCMG) mode considering singularity avoidance during an agile attitude manoeuvre, and the steering mode is then transited to the reaction wheel (RW) mode smoothly according to the attitude error of the spacecraft during highly accurate pointing control in the final state of the manoeuvre [6]. Kasai and Kojima proposed the gain-scheduled steering law of VSCMGs [7], focusing on the condition numbers of the Jacobian matrix in an inverse matrix calculation in addition to the consideration of the attitude error. As shown in Figure 2 [7], there is a trade-off relationship between the condition numbers of the Jacobian for the CSCMG mode and that for the RW mode.…”

Section: Introductionmentioning

confidence: 99%

“…Kasai and Kojima proposed the gain-scheduled steering law of VSCMGs [7], focusing on the condition numbers of the Jacobian matrix in an inverse matrix calculation in addition to the consideration of the attitude error. As shown in Figure 2 [7], there is a trade-off relationship between the condition numbers of the Jacobian for the CSCMG mode and that for the RW mode. The method of Kasai and Kojima changes to the gimbal angles for which the condition number of the RW mode is most well-conditioned in the final state of a single manoeuvre, and its validity has been confirmed by numerical simulation.…”

Section: Introductionmentioning

confidence: 99%

Mode-Scheduling Steering Law of VSCMGs for Multi-Target Pointing and Agile Maneuver of a Spacecraft

Nanamori¹,

Takahashi²

2017

ijacsa

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Abstract-This study proposes a method of selecting a set of gimbal angles in the final state and applies the method to the mode-scheduling steering law of variable-speed control moment gyros intended for multi-target pointing manoeuvres in the threeaxis attitude control of a spacecraft. The proposed method selects reference final gimbal angles, considering the condition numbers of the Jacobian matrix of the reaction wheel mode in the final state of a single manoeuvre and that of the constant-speed control moment gyro mode at the start of the upcoming manoeuvre to keep away from the singularities. To improve the reachability of reference final gimbal angles, the nearest set of gimbal angles among nominated sets according to the Euclidean norm is selected as the reference final set at the middle of the single manoeuvre, and then realised by adopting gimbal angle feedback steering logic using null motion. In addition, the manoeuvre profile is designed such that the second half of the single manoeuvre is more gradual and takes longer than the first. Numerical simulation confirms the validity of the proposed method in consecutive manoeuvres.

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