Add to ORKGA Feedforward/Feedback Control Law is described for achieving near-minimum time reorientation of a rigid spacecraft. Approximate control switch times are calculated via a quasi closed-form solution. These switch times are used to generate parabolic switching functions in decoupled quasi-coordinate space which are analogous to the single axis minimum time closed loop control. The efficacy of the control law is validated using the rigidized model of the Advanced Structure Technology Research Experiment (ASTREX) developed by the Air Force Phillips Laboratory
This thesis explores concepts for a closed-loop optimal control implementation of minimum-time attit...
The problem of estimating the control switch times for minimum time rest-to-rest reorientation of a ...
The dissertation contributes new results in three related areas: motion planning for noncatastatic n...
The problem of slewing a rigid body from an arbitrary initial orientation to a desired target orient...
Time optimal rest-to-rest reorientation of a rigid spacecraft with an arbitrary initial attitude and...
The nature of time optimal rotations of a rigid spacecraft with distinct principal moments of inerti...
Recent results show that a nonsmooth, time-invariant feedback control law can be used to rotate an a...
The attitude stabilization problem of a rigid spacecraft using control torques supplied by gas jet a...
Most spacecrafts are designed to be maneuvered to achieve pointing goals. This is accomplished usual...
This paper addresses the problem of reorienting a rigid spacecraft from arbitrary initial conditions...
Maintaining the spacecraft attitude precisely aligned to a given orientation, while rejecting a pers...
It is well known that three momentum wheel actuators can be used to control the attitude of a rigid ...
This paper presents a design of a novel feedforward controller for a large-angle reorientation maneu...
This article introduces a time-optimal reorientation manoeuvre controller with saturation constraint...
Recent results show that a nonsmooth, timeinvariant feedback control law can be used to stabilize an...
This thesis explores concepts for a closed-loop optimal control implementation of minimum-time attit...
The problem of estimating the control switch times for minimum time rest-to-rest reorientation of a ...
The dissertation contributes new results in three related areas: motion planning for noncatastatic n...
The problem of slewing a rigid body from an arbitrary initial orientation to a desired target orient...
Time optimal rest-to-rest reorientation of a rigid spacecraft with an arbitrary initial attitude and...
The nature of time optimal rotations of a rigid spacecraft with distinct principal moments of inerti...
Recent results show that a nonsmooth, time-invariant feedback control law can be used to rotate an a...
The attitude stabilization problem of a rigid spacecraft using control torques supplied by gas jet a...
Most spacecrafts are designed to be maneuvered to achieve pointing goals. This is accomplished usual...
This paper addresses the problem of reorienting a rigid spacecraft from arbitrary initial conditions...
Maintaining the spacecraft attitude precisely aligned to a given orientation, while rejecting a pers...
It is well known that three momentum wheel actuators can be used to control the attitude of a rigid ...
This paper presents a design of a novel feedforward controller for a large-angle reorientation maneu...
This article introduces a time-optimal reorientation manoeuvre controller with saturation constraint...
Recent results show that a nonsmooth, timeinvariant feedback control law can be used to stabilize an...
This thesis explores concepts for a closed-loop optimal control implementation of minimum-time attit...
The problem of estimating the control switch times for minimum time rest-to-rest reorientation of a ...
The dissertation contributes new results in three related areas: motion planning for noncatastatic n...