A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit
A two-phased guidance problem with terminal impact angle constraints and seeker’s field-of-view limit is addressed in this paper for a missile against a nonmaneuvering incoming target. From the conventional PN guidance without any constraints, it is found that satisfying the impact angle constraint...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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Wiley
2018-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2018/7403639 |
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| _version_ | 1832545434370834432 |
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| author | Haoqiang Zhang Shengjing Tang Jie Guo Wan Zhang |
| author_facet | Haoqiang Zhang Shengjing Tang Jie Guo Wan Zhang |
| author_sort | Haoqiang Zhang |
| collection | DOAJ |
| description | A two-phased guidance problem with terminal impact angle constraints and seeker’s field-of-view limit is addressed in this paper for a missile against a nonmaneuvering incoming target. From the conventional PN guidance without any constraints, it is found that satisfying the impact angle constraint causes a more curved missile trajectory requiring a large look angle. To avoid the look angle exceeding the seeker’s physical limit, a two-phased look angle control guidance scheme with the terminal constraint is introduced. The PN-typed guidance law is designed for each guidance phase with a specific switching condition of line-of-sight. The proposed guidance law is comprised of two types of acceleration commands: the one in the initial phase which aims at controlling the missile’s look angle to reach the limit and the other for final phase which is produced by switching the navigation gain. The monotonicity of the line-of-sight angle and look angle is analyzed and proved to support the proposed method. To evaluate the specific navigation gains for both initial and final phases, the scaling coefficient between them is discussed by solving a quadratic equation with respect to the initial navigation gain. To avoid a great abrupt acceleration change at the switching instant, a minimum coefficient is chosen. Extensive simulations are performed to validate the efficiency of the proposed approach. |
| format | Article |
| id | doaj-art-5a8aad21814348b98b4fae2043e7d331 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2018-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-5a8aad21814348b98b4fae2043e7d3312025-02-03T07:25:41ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742018-01-01201810.1155/2018/74036397403639A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View LimitHaoqiang Zhang0Shengjing Tang1Jie Guo2Wan Zhang3Key Laboratory of Dynamic and Control of Flight Vehicle of the Ministry of Education, School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, ChinaKey Laboratory of Dynamic and Control of Flight Vehicle of the Ministry of Education, School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, ChinaKey Laboratory of Dynamic and Control of Flight Vehicle of the Ministry of Education, School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, ChinaBeijing Electro-Mechanical Engineering Institute, Beijing 100071, ChinaA two-phased guidance problem with terminal impact angle constraints and seeker’s field-of-view limit is addressed in this paper for a missile against a nonmaneuvering incoming target. From the conventional PN guidance without any constraints, it is found that satisfying the impact angle constraint causes a more curved missile trajectory requiring a large look angle. To avoid the look angle exceeding the seeker’s physical limit, a two-phased look angle control guidance scheme with the terminal constraint is introduced. The PN-typed guidance law is designed for each guidance phase with a specific switching condition of line-of-sight. The proposed guidance law is comprised of two types of acceleration commands: the one in the initial phase which aims at controlling the missile’s look angle to reach the limit and the other for final phase which is produced by switching the navigation gain. The monotonicity of the line-of-sight angle and look angle is analyzed and proved to support the proposed method. To evaluate the specific navigation gains for both initial and final phases, the scaling coefficient between them is discussed by solving a quadratic equation with respect to the initial navigation gain. To avoid a great abrupt acceleration change at the switching instant, a minimum coefficient is chosen. Extensive simulations are performed to validate the efficiency of the proposed approach.http://dx.doi.org/10.1155/2018/7403639 |
| spellingShingle | Haoqiang Zhang Shengjing Tang Jie Guo Wan Zhang A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit International Journal of Aerospace Engineering |
| title | A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit |
| title_full | A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit |
| title_fullStr | A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit |
| title_full_unstemmed | A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit |
| title_short | A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit |
| title_sort | two phased guidance law for impact angle control with seeker s field of view limit |
| url | http://dx.doi.org/10.1155/2018/7403639 |
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