Suboptimal command generation for control moment gyroscopes and feedback control of spacecraft

Vadali, Srinivas R.; Krishnan, S.

doi:10.2514/3.21552

Cited by 30 publications

(6 citation statements)

References 9 publications

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“…Figure 11 isolates the contribution of the torque from the gimbal acceleration. With only the holding torque and other body rate inertial effects remaining, it is evident that Difference Between Total-array and Gimbal-only Torque Approach (ft-lb) 6 It should be noted that the coxh term in the classical method simulation is directly combined with the control torque at the spacecraft dynamical equations (refer to Eq. 20) while it is embedded in the matrix in Eq.…”

Section: Model Resultsmentioning

confidence: 99%

A practical approach to modeling single-gimbal Control Momentum Gyroscopes in agile spacecraft

Heiberg

2000

AIAA Guidance, Navigation, and Control Conference and Exhibit

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Control Moment Gyroscopes (CMC) have many uses, including the precision steering of spacecraft. In that application, an array of at least three CMGs is used to produce a control torque in any direction. The CMG itself contains a spinning rotor (stored angular momentum vector), which is suspended in at least one gimbal. Single-Gimbal CMGs (SGCMG) have an advantage over multiple gimbal devices in that they easily facilitate "torque multiplication." Torque multiplication describes the operation in which a small input torque from the gimbal actuator produces a much greater torque in a plane formed by the rotating momentum vector. Because the direction of the output torque is a function of the gimbal orientation, loading varies on the mechanical interface to the spacecraft. In addition, angular rotation of the spacecraft couples with the stored CMG momentum vector producing additional torque on the interface. This paper presents a set of dynamical equations in order to properly describe the loading at the mechanical interface to the spacecraft. A standard sign convention and notation is presented in addition to a projection matrix so that the CMG loading can be represented in the global (spacecraft) coordinates. The work presented demonstrates the improved fidelity of this approach in a CMG array steered rigid body spacecraft model.

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Section: Model Resultsmentioning

confidence: 99%

A practical approach to modeling single-gimbal Control Momentum Gyroscopes in agile spacecraft

Heiberg

2000

AIAA Guidance, Navigation, and Control Conference and Exhibit

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“…4,5) In addition, feed-forward control inputs are described by using the optimal control theory considering maneuver time, singularities, or energy consumption. [6][7][8] Although optimal feed-forward control achieves singularity avoidance and optimal maneuvers, initial assumption and iterative calculations are needed to obtain optimal inputs. There are few studies about optimal control laws which have small calculation cost.…”

Section: Introductionmentioning

confidence: 99%

Sub-Optimal Control Law for Minimum Energy Attitude Maneuver using CMGs

Uematsu

Ueno

Higuchi

2014

AEROSPACE TECHNOLOGY JAPAN

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Single Gimbal Control Moment Gyro (SGCMG) is an effective actuator for three axis attitude control of the satellites. Since satellite missions conduct with limited energy supplies in space, it is required to reduce the energy consumption during attitude maneuvers. However there are two problems with finding the optimal solutions for minimum energy maneuvers: the initial assumption and the calculation cost. To solve these problems, this study introduces a new sub-optimal control law to achieve the sub-minimum energy maneuvers without both initial assumption and iterative calculation. Compared to conventional steering law, the sub-optimal control law results in decreasing the energy consumption by more than 80 percent for all maneuver axis.

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“…Encountering a singularity can result in problems such as very high gimbal-rate commands. [1][2][3] In this application, we address the issue of singularities with the use of a special CMG configuration, which is described in the following section.…”

Section: Introductionmentioning

confidence: 99%

Dynamics of a High-Agility, Low-Power Coelostat Telescope

Carpenter

Peck

2006

AIAA Guidance, Navigation, and Control Conference and Exhibit

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Control-moment gyroscopes (CMGs) are power-efficient attitude-control actuators that produce high torques for agile spacecraft. We propose the use of CMGs in actuating joint degrees of freedom in a spacecraft-mounted agile coelostat telescope, whose tasks include acquiring and tracking a high-speed target. High agility, on the order of several radians per second, is a priority for such a system; however, such capabilities are achieved with traditional actuators only at the expense of excessively high electrical power. The proposed design provides reactionless, agile slewing of a telescope for a small fraction of the power required by fixed rotors in a reaction wheel assembly. This study provides explicit equations of motion for the proposed system and demonstrates by simulation that a CMG-driven system offers the same agility with less than 10% of the power of a telescope actuated by reaction wheels. Nomenclature 0 i/

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Suboptimal command generation for control moment gyroscopes and feedback control of spacecraft

Cited by 30 publications

References 9 publications

A practical approach to modeling single-gimbal Control Momentum Gyroscopes in agile spacecraft

A practical approach to modeling single-gimbal Control Momentum Gyroscopes in agile spacecraft

Sub-Optimal Control Law for Minimum Energy Attitude Maneuver using CMGs

Dynamics of a High-Agility, Low-Power Coelostat Telescope

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