Spacecraft Angular Velocity Stabilization Using A Single-Gimbal Variable Speed Control Moment Gyro

اسناد مشابه

• Spacecraft Angular Velocity and Line-of-Sight Control Using A Single-Gimbal Variable-Speed Control Moment Gyro

  سند علمی۲۰۰۵Hyungjoo Yoon, Panagiotis Tsiotras

  It is well known that complete attitude control of a spacecraft is not possible with only one single-gimbal Variable-Speed Control Moment Gyro (VSCMG) due to the conservation of the angular momentum. However, partial attitude control without violating the angular momentum conserv

• IAA-AAS-DyCoSS2-14 -07-06 ATTITUDE CONTROL OF A SPACECRAFT WITH A DOUBLE-GIMBAL VARIABLE-SPEED CONTROL MOMENT GYRO VIA LPV CONTROL THEORY

  سند علمی۲۰۱۴Takahiro Sasaki, Takashi Shimomura

  In this paper, we analyze dynamics of a DGVSCMG(Double-Gimbal VariableSpeed Control Moment Gyro) and develop an easy-to-use LPV (Linear ParameterVarying) model, in which we deal with 3-axis attitude control of a spacecraft equipped with a DGVSCMG. Although it is hard to consider

• Spacecraft Line-of-Sight Control Using a Single Variable-Speed Control Moment Gyro

  سند علمی۲۰۰۶Hyungjoo Yoon, Panagiotis Tsiotras

  Complete attitude control of a spacecraft is not possible with only one single-gimbal variable-speed control moment gyro due to the conservation of angular momentum. However, partial attitude control without violating the angular momentum conservation principle is still possible.

• Attitude Dynamics/Control of Dual-Body Spacecraft with Variable-Speed Control Moment Gyros

  سند علمی۲۰۰۴Marcello Romano, Brij N. Agrawal

  The dynamics equations of a spacecraft consisting of two bodies mutually rotating around a common gimbal axis are derived by the use of the Newton–Euler approach. One of the bodies contains a cluster of single-gimbal variable-speed control moment gyros. The equations include all

• Singularity Analysis and Avoidance of Variable-Speed Control Moment Gyros – Part II : Power Constraint Case

  سند علمی۲۰۰۴Hyungjoo Yoon, Panagiotis Tsiotras

  A Variable Speed Control Moment Gyro (VSCMG) is a relatively recent torque actuator device for spacecraft attitude control. As implied by its name, a VSCMG is a singlegimbal control moment gyro (CMG) with a flywheel having variable speed. Owing to this extra degree of freedom, a

• Singularity Analysis and Avoidance of Variable-Speed Control Moment Gyros – Part I : No Power Constraint Case

  سند علمی۲۰۰۴Hyungjoo Yoon, Panagiotis Tsiotras

  Single-gimbal control moment gyros (CMGs) have several advantages over other actuators for attitude control of spacecraft. For instance, they act as torque amplifiers and, thus, are suitable for slew maneuvers. However, their use as torque actuators is hindered by the presence of