Add to ORKGThis paper presents the application of two separate discrete time sliding mode controllers, developed in conjunction with a potential function guidance method, to provide control in both position and attitude for a rigid, holonomic spacecraft body. The system is demonstrated in MATLABTM simulations to illustrate effectivenessunder realistic actuator constraints
It is well known that three momentum wheel actuators can be used to control the attitude of a rigid ...
AbstractEigenaxis rotation is generally regarded as a near-minimum time strategy for rapid attitude ...
Recent advances in small, low cost satellite technology has generated a renewed interest in formatio...
Published version of an article in the journal: Abstract and Applied Analysis. Also available from t...
AbstractTo solve the problem of attitude tracking of a rigid spacecraft with an either known or meas...
This paper presents a variable hierarchy six degree of freedom non-linear sliding mode controller fo...
Sliding Mode Control (SMC) is well known as a robust control approach and is proven to be able to de...
The dissertation contributes new results in three related areas: motion planning for noncatastatic n...
AbstractIn this paper, the attitude stabilization problem of a rigid spacecraft described by Rodrigu...
In this work, station-keeping of real Earth–Moon libration point orbits is studied using discrete-ti...
This work focuses on the analysis and application of various nonlinear, autonomous guidance algorith...
The attitude stabilization problem of a rigid spacecraft using control torques supplied by gas jet a...
This paper studies high-order sliding mode control laws to deal with some spacecraft attitude tracki...
The robust optimal attitude control problem for a flexible spacecraft is considered. Two optimal sli...
This thesis describes the development of robust discrete time sliding mode controllers where only ou...
It is well known that three momentum wheel actuators can be used to control the attitude of a rigid ...
AbstractEigenaxis rotation is generally regarded as a near-minimum time strategy for rapid attitude ...
Recent advances in small, low cost satellite technology has generated a renewed interest in formatio...
Published version of an article in the journal: Abstract and Applied Analysis. Also available from t...
AbstractTo solve the problem of attitude tracking of a rigid spacecraft with an either known or meas...
This paper presents a variable hierarchy six degree of freedom non-linear sliding mode controller fo...
Sliding Mode Control (SMC) is well known as a robust control approach and is proven to be able to de...
The dissertation contributes new results in three related areas: motion planning for noncatastatic n...
AbstractIn this paper, the attitude stabilization problem of a rigid spacecraft described by Rodrigu...
In this work, station-keeping of real Earth–Moon libration point orbits is studied using discrete-ti...
This work focuses on the analysis and application of various nonlinear, autonomous guidance algorith...
The attitude stabilization problem of a rigid spacecraft using control torques supplied by gas jet a...
This paper studies high-order sliding mode control laws to deal with some spacecraft attitude tracki...
The robust optimal attitude control problem for a flexible spacecraft is considered. Two optimal sli...
This thesis describes the development of robust discrete time sliding mode controllers where only ou...
It is well known that three momentum wheel actuators can be used to control the attitude of a rigid ...
AbstractEigenaxis rotation is generally regarded as a near-minimum time strategy for rapid attitude ...
Recent advances in small, low cost satellite technology has generated a renewed interest in formatio...