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| Title: | Integrated guidance and control of missiles with θ-D method | |
| Alternate Title: | Integrated guidance and control of missiles with theta-D method | |
| Author (s): | Xin, M. Balakrishnan, S. N. Ohlmeyer, E.J. | |
| Department/Lab Affiliations: | Mechanical & Aerospace Engineering | |
| Keywords: | Missile integrated guidance and control nonlinear systems optimal control theta - D technique | |
| Issue Date: | 2006 | |
| Publisher: | Institute of Electrical and Electronics Engineers | |
| Citation: | Xin, M.; Balakrishnan, S. N.; Ohlmeyer, E.J. "Integrated Guidance and Control of Missiles With θ-D Method" IEEE Transactions on Control Systems Technology, Vol.14, Iss.6, Nov. 2006 Pages: 981- 992 | |
| Abstract: | A new suboptimal control method is proposed in this study to effectively design an integrated guidance and control system for missiles. Optimal formulations allow designers to bring together concerns about guidance law performance and autopilot responses under one unified framework. They lead to a natural integration of these different functions. By modifying the appropriate cost functions, different responses, control saturations (autopilot related), miss distance (guidance related), etc., which are of primary concern to a missile system designer, can be easily studied. A new suboptimal control method, called the θ-D method, is employed to obtain an approximate closed-form solution to this nonlinear guidance problem based on approximations to the Hamilton-Jacobi-Bellman equation. Missile guidance law and autopilot design are formulated into a single unified state space framework. The cost function is chosen to reflect both guidance and control concerns. The ultimate control input is the missile fin deflections. A nonlinear six-degree-of-freedom (6-DOF) missile simulation is used to demonstrate the potential of this new integrated guidance and control approach. | |
| Type: | Article - Journal text | |
| Copyright Notice: | This material is presented to ensure timely dissemination of scholarly and technical work. Copyright and all rights therein are retained by authors or by other copyright holders. All persons copying this information are expected to adhere to the terms and constraints invoked by each author's copyright. In most cases, these works may not be reposted without the explicit permission of the copyright holder. FULL COPYRIGHT INFORMATION: | |
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| title | Integrated guidance and control of missiles with θ-D method | |
| title.alternative | Integrated guidance and control of missiles with theta-D method | |
| contributor.author | Xin, M. | |
| contributor.author | Balakrishnan, S. N. | |
| contributor.author | Ohlmeyer, E.J. | |
| contributor.deptlab | Mechanical & Aerospace Engineering | |
| subject | Missile integrated guidance and control | |
| subject | nonlinear systems | |
| subject | optimal control | |
| subject | theta - D technique | |
| date.issued | 2006 | |
| date.submitted | 2007 | |
| publisher | Institute of Electrical and Electronics Engineers | |
| identifier.citation | Xin, M.; Balakrishnan, S. N.; Ohlmeyer, E.J. "Integrated Guidance and Control of Missiles With θ-D Method" IEEE Transactions on Control Systems Technology, Vol.14, Iss.6, Nov. 2006 Pages: 981- 992 | |
| identifier.issn | 1063-6536 | |
| identifier.pub.URI | ||
| description.abstract | A new suboptimal control method is proposed in this study to effectively design an integrated guidance and control system for missiles. Optimal formulations allow designers to bring together concerns about guidance law performance and autopilot responses under one unified framework. They lead to a natural integration of these different functions. By modifying the appropriate cost functions, different responses, control saturations (autopilot related), miss distance (guidance related), etc., which are of primary concern to a missile system designer, can be easily studied. A new suboptimal control method, called the θ-D method, is employed to obtain an approximate closed-form solution to this nonlinear guidance problem based on approximations to the Hamilton-Jacobi-Bellman equation. Missile guidance law and autopilot design are formulated into a single unified state space framework. The cost function is chosen to reflect both guidance and control concerns. The ultimate control input is the missile fin deflections. A nonlinear six-degree-of-freedom (6-DOF) missile simulation is used to demonstrate the potential of this new integrated guidance and control approach. | |
| type | Article - Journal | |
| type.DCMIType | text | |
| type.status | Final version | |
| type.status | Final version | |
| rights | This material is presented to ensure timely dissemination of scholarly and technical work. Copyright and all rights therein are retained by authors or by other copyright holders. All persons copying this information are expected to adhere to the terms and constraints invoked by each author's copyright. In most cases, these works may not be reposted without the explicit permission of the copyright holder. | |
| rights.URI | ||
| date.accessioned | 2007-04-05T14:28:06Z | |
| date.available | 2007-04-05T14:28:05Z | |
| identifier.persist.URI | ||
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