Attitude Control of a Spacecraft with  Single Variable-Speed Control Moment Gyroscope

Jin, Jaehyun; Hwang, Inseok

doi:10.2514/1.53012

Cited by 21 publications

(10 citation statements)

References 10 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Using the advantages of control moment gyros, angular rate damping and attitude control problems are handled in Refs. [8,29], respectively. For an asymmetric rigid spacecraft, Kim et al [14,15] have presented a Davidenko-like homotopy method that generates a nonlinear open-loop solution for three-dimensional maneuvers when only two actuators are available.…”

Section: Introductionmentioning

confidence: 97%

Suboptimal continuous torque attitude maneuvers for underactuated spacecraft

Kim

Turner

2015

Aerospace Science and Technology

View full text Add to dashboard Cite

Section: Introductionmentioning

confidence: 97%

Suboptimal continuous torque attitude maneuvers for underactuated spacecraft

Kim

Turner

2015

Aerospace Science and Technology

View full text Add to dashboard Cite

“…McMahon and Schaub (2010), Richie and Lappas (2007), and Jin and Hwang (2011) have designed variable-speed control moment gyroscopes to produce the exact effective torque required at the cost of increasing the difficulty of dynamical modelling and controller design.…”

Section: Control Moment Gyrosmentioning

confidence: 99%

Attitude Dynamics and Control of Satellites With Fluid Ring Actuators

Nobari

Misra

2012

Journal of Guidance, Control, and Dynamics

View full text Add to dashboard Cite

Successful mission of a satellite depends on maintaining a fixed orientation with respect to the Earth. However, the attitude angles of a satellite can be perturbed because of various natural disturbance sources, such as the Earth's gravity gradient, solar radiation pressure, and the Earth's magnetic field. Modeling the attitude dynamics and developing a controller to stabilize the attitude motion are quite important steps in the design of satellites. Although several actuators exist to control the attitude motion, a novel type considered in the thesis, shows promise of producing a high torque to mass ratio. This potential justifies the in-depth study reported. The novel actuator in question consists of a ring containing fluid, whose flow is regulated by a pump. The control torque is produced due to the variation of the angular velocity of the fluid.In this thesis, first, a redundant actuator system composed of four fluid rings in a pyramidal configuration is studied. The dynamical model of the system is developed for a satellite travelling either in a circular or an elliptical orbit. The dynamical analysis of this system leads to an underdetermined system of nonlinear differential equations, whose solution without considering the control input (the torque produced by the pump pressure) shows that the fluid rings can damp out the attitude disturbances of a satellite in a circular orbit and the roll-yaw disturbances in an elliptical orbit. However, this passive damping effect is fairly slow; an active controller is hence designed in the next step. The effect of the failure of one fluid ring on the performance of the attitude control subsystem (ACS) of a satellite is also studied. It is observed that even in the case of failure of one fluid ring, the satellite can be stabilized by slight modification of the active controller.Later, a sliding mode controller is designed to cope with the uncertainties existing in the fluid model and in other parameters of the system. Although the results achieved are quite satisfactory, the chattering that exists in the steady response of the system is not i desirable; hence a switching controller consisting of a sliding mode and a PID control law is designed to eliminate this chattering effect.Next, the theoretical results obtained are validated by conducting several experiments. To this end, first, a setup with one fluid ring is designed and built. Here, a single fluid ring is attached to a disk so as to verify the controllability of the system with a fluid ring and also the validity of the theoretical model. Although the experimental results confirm the theory developed in this thesis, the large torque-to-mass ratio expected is revealed to be only possible at the cost of a quite high input voltage to the pumps regulating the flow. Therefore, two novel applications of fluid rings are proposed: as an actuator for spin stabilized satellites, or as an auxiliary actuator in satellites with magnetic torquers.Using fluid rings in spin stabilized satellites is proposed in the the...

show abstract

“…Using the example from the simulation in Section XXX, the singularity state could be avoided by altering the speed of flywheels 1 and 3 in such a way that would allow the system to reach an angular momentum vector of = [1.15, 0, 0] with a CMG gain, , > 0 (Jin & Hwang, 2011). A new area of research emerging is the potential to use a variable-speed CMG system for attitude control and power storage.…”

Section: Discussionmentioning

confidence: 99%

“…Other works by Jin &Hwang (2011) andZhang &Fang (2013) investigate the potential of backstepping control methods for use with double-gimbal VSCMG systems. The authors present a dual-loop control system comprising of an attitude loop and an angular speed loop.…”

Section: Gradient/null Motion Weighted Matrixmentioning

confidence: 99%

“…Although the authors investigate the control of a variable speed CMG system which is out of scope for this project, the null motion principles are applicable to a constant speed CMG system. Zhang & Fang (2013) present the control law using Euler notation, Jin & Hwang (2011) develop the controller using quaternion notation however both follow the same logic (Jin & Hwang, 2011;Zhang & Fang, 2013). As the system approaches the singularity state a small random perturbation in null motion is introduced into the attitude control loop to allow the spacecraft to reach the desired attitude while maintaining a non-singular gyroscope orientation (Zhang & Fang, 2013).…”

Section: Gradient/null Motion Weighted Matrixmentioning

confidence: 99%

See 1 more Smart Citation

Comparison of control moment gyroscope control laws for a spacesuit

McNamara¹

View full text Add to dashboard Cite

This report investigates and compares steering laws for a control moment gyroscope (CMG) attitude control system for a spacesuit. If there is an inadequate level of control in a CMG system then the angular momentum vectors of individual CMGs may become aligned. This state, referred to as a 'singularity state', prevents the system from being able to produce torque in one or more directions. The steering law problem has been defined and the momentum envelope is presented to visualize system singularities. A literature review has been conducted to find applicable steering laws that may be used to control a spacesuit sized system and avoid singularities in the momentum envelope. Six potential steering laws are identified as being potentially applicable to a spacesuit sized system; the Moore-Penrose pseudoinverse (MPI), offline planning, preferred gimbal angle, linearly constrained, null motion, and the singularity-robust inverse (SRI).A conceptual pyramid configuration system of 4 CMGs has been constructed to analyse the selected steering laws through a qualitative and quantitative comparison. The qualitative assessment investigates several criteria; the singularity handling method, induced torque error, system efficiency and full utilization of hardware, convergence to singularity arrangements, and the potential for generalization to other CMG arrangements. The results of the qualitative comparison conclude that the SRI control law is the most viable for use with a spacesuit. A computational model was used to compare the behaviour of the conceptual system using the MPI and the SRI control laws. The simulation results support the qualitative analysis. The SRI control law successfully navigates around singularities by inducing a small, proportional torqueing error. It is concluded that a CMG control system can potentially be used with a spacesuit and that the SRI control law is the most viable method to avoid singularities during operation.

show abstract

Attitude Control of a Spacecraft with Single Variable-Speed Control Moment Gyroscope

Cited by 21 publications

References 10 publications

Suboptimal continuous torque attitude maneuvers for underactuated spacecraft

Suboptimal continuous torque attitude maneuvers for underactuated spacecraft

Attitude Dynamics and Control of Satellites With Fluid Ring Actuators

Comparison of control moment gyroscope control laws for a spacesuit

Contact Info

Product

Resources

About