Abstract
This paper presents kinematically coupled relative spacecraft motion control in the close proximity of a tumbling target using the state-dependent Riccati equation method for proximity operation mission. In general, a rigid-body dynamics can be expressed as both translation and rotation about the center of mass. However, a kinematic coupling between the rotational and translational dynamics occurs when it is not expressed about the center of mass. Thus, kinematically coupled relative spacecraft motion model is derived to describe the relative motion about the selected arbitrary points on both the target and spacecraft. Then, spacecraft relative motion is represented by combining the relative translational and rotational dynamics of arbitrary points on the spacecraft. The spacecraft is required to achieve the desired position and attitude to track a tumbling spacecraft quickly in the effect of kinematic translation and rotation coupling. The state-dependent Riccati equation method is implemented to design a nonlinear controller in six degrees of freedom. Numerical simulation results validate kinematically coupled relative spacecraft motion control with respect to a tumbling target.
| Original language | English (US) |
|---|---|
| Article number | 4014099 |
| Journal | Journal of Aerospace Engineering |
| Volume | 28 |
| Issue number | 4 |
| DOIs | |
| State | Published - Jan 1 2015 |
| Externally published | Yes |
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Keywords
- Coupled translational dynamics
- Feature point
- Kinematic coupling
- State-dependent Riccati equation
- Tumbling target
ASJC Scopus subject areas
- Civil and Structural Engineering
- Materials Science(all)
- Aerospace Engineering
- Mechanical Engineering
Cite this
Kinematically coupled relative spacecraft motion control using the state-dependent riccati equation method. / Lee, Daero; Bang, Hyochoong; Butcher, Eric A.; Sanyal, Amit.
In: Journal of Aerospace Engineering, Vol. 28, No. 4, 4014099, 01.01.2015.Research output: Contribution to journal › Article
}
TY - JOUR
T1 - Kinematically coupled relative spacecraft motion control using the state-dependent riccati equation method
AU - Lee, Daero
AU - Bang, Hyochoong
AU - Butcher, Eric A.
AU - Sanyal, Amit
PY - 2015/1/1
Y1 - 2015/1/1
N2 - This paper presents kinematically coupled relative spacecraft motion control in the close proximity of a tumbling target using the state-dependent Riccati equation method for proximity operation mission. In general, a rigid-body dynamics can be expressed as both translation and rotation about the center of mass. However, a kinematic coupling between the rotational and translational dynamics occurs when it is not expressed about the center of mass. Thus, kinematically coupled relative spacecraft motion model is derived to describe the relative motion about the selected arbitrary points on both the target and spacecraft. Then, spacecraft relative motion is represented by combining the relative translational and rotational dynamics of arbitrary points on the spacecraft. The spacecraft is required to achieve the desired position and attitude to track a tumbling spacecraft quickly in the effect of kinematic translation and rotation coupling. The state-dependent Riccati equation method is implemented to design a nonlinear controller in six degrees of freedom. Numerical simulation results validate kinematically coupled relative spacecraft motion control with respect to a tumbling target.
AB - This paper presents kinematically coupled relative spacecraft motion control in the close proximity of a tumbling target using the state-dependent Riccati equation method for proximity operation mission. In general, a rigid-body dynamics can be expressed as both translation and rotation about the center of mass. However, a kinematic coupling between the rotational and translational dynamics occurs when it is not expressed about the center of mass. Thus, kinematically coupled relative spacecraft motion model is derived to describe the relative motion about the selected arbitrary points on both the target and spacecraft. Then, spacecraft relative motion is represented by combining the relative translational and rotational dynamics of arbitrary points on the spacecraft. The spacecraft is required to achieve the desired position and attitude to track a tumbling spacecraft quickly in the effect of kinematic translation and rotation coupling. The state-dependent Riccati equation method is implemented to design a nonlinear controller in six degrees of freedom. Numerical simulation results validate kinematically coupled relative spacecraft motion control with respect to a tumbling target.
KW - Coupled translational dynamics
KW - Feature point
KW - Kinematic coupling
KW - State-dependent Riccati equation
KW - Tumbling target
UR - http://www.scopus.com/inward/record.url?scp=84932172864&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84932172864&partnerID=8YFLogxK
U2 - 10.1061/(ASCE)AS.1943-5525.0000436
DO - 10.1061/(ASCE)AS.1943-5525.0000436
M3 - Article
AN - SCOPUS:84932172864
VL - 28
JO - Journal of Aerospace Engineering
JF - Journal of Aerospace Engineering
SN - 0893-1321
IS - 4
M1 - 4014099
ER -