Name
Abstract | ||
|---|---|---|
A scheme for integrated guidance/autopilot design for missiles based on terminal sliding-mode control is proposed. Firstly, the terminal sliding mode control is introduced, based on which and the backstepping idea the guidance/control law is designed when an integrated guidance/autopilot model of the yaw plane is formulated. Secondly, an estimating method is given for the unavailable information of the maneuvering target, and an auxiliary control based on a sliding mode estimator is used to offset the estimation error. Finally, a simulation of some missile against high maneuvering targets on the yaw plane was made to verify the effectiveness and rightness of the scheme, and the simulation results have shown that high accuracy of hitting target can be got when the scheme is adopted. |
Year | DOI | Venue |
|---|---|---|
2005 | 10.1007/11538356_34 | ICIC (2) |
Keywords | Field | DocType |
mode control,integrated guidance,autopilot model,control law,auxiliary control,yaw plane,terminal sliding-mode control,high maneuvering target,tsm control,high accuracy,autopilot design,sliding mode control | Backstepping,Proportional navigation,Missile,Control theory,Computer science,Integrated design,Autopilot,Terminal sliding mode,Variable structure system,Missile guidance | Conference |
Volume | ISSN | ISBN |
3645 | 0302-9743 | 3-540-28227-0 |
Citations | PageRank | References |
0 | 0.34 | 1 |
Authors | ||
4 | ||
Name | Order | Citations | PageRank |
|---|---|---|---|
| Jinyong Yu | 1 | 277 | 23.41 |
| Daquan Tang | 2 | 31 | 7.70 |
| Wenjin Gu | 3 | 13 | 5.63 |
| Qingjiu Xu | 4 | 1 | 1.16 |