Bias-Shaping Method for Biased Proportional Navigation with Terminal-Angle Constraint

Aerospace Science and Technology

2015

Section: Proof See Appendix Cmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

Aerospace Science and Technology

2015

“…Under the assumption that the angle of sideslip is small, one can use the lead angle limitation for handling the seeker's FOV constraint. 7,8 Hence, the FOV constraint can be represented by ' 4' max , where ' max 2 ð0, =2Þ is a constant determined by the seeker's FOV limitation. An assumption about the initial lead angle is given as follows for further analysis.…”

Section: Problem Formulationmentioning

confidence: 99%

Impact time control guidance with field-of-view constraint accounting for uncertain system lag

Proceedings of the Institution of Mechanical Engineers, Part G:

2015

The problem of impact time control guidance with seeker's field-of-view constraint in the presence of uncertain system lag is addressed. A novel two-step control approach based impact time control guidance law with seeker's field-of-view constraint is proposed. Specifically, in the first step, a state constrained robust adaptive control law, using the dynamic surface control method combining with the control integral barrier Lyapunov function technique, is synthesized to achieve the required robust tracking performance with respect to the desired trajectory of lead angle in the presence of uncertain system lag and other uncertainties. In the second step, the desired trajectory of lead angle is generated online to guarantee target interception at the designated impact time under the assumption of ideal autopilot dynamics while not violating the seeker' field-of-view constraint. The proposed guidance law ensures the seeker's field-of-view constraint does not be violated in the presence of uncertain system lag and other uncertainties. Numerical simulations are provided to illustrate the effectiveness of the proposed guidance law.

show abstract

“…To cope with this challenge, two methods can be used. One is the active method, in which a proper designated impact time is selected within some interval determined by the missile's maneuvering capacity and the FOV, see [10]; the other is the passive method, in which a switching logic is used to keep the target within the missile's FOV, see [10] and [6]. The active method cannot utilize the maneuvering capacity of the missile sufficiently since it just simply ensures the maximum look angle does not exceed the FOV limit.…”

Section: Introductionmentioning

confidence: 99%

“…In [13], a biased PNG (BPNG) law is designed to control the impact time and impact angle. In [7], sliding mode impact time guidance laws are designed based on the conventional and improved formulas for time-to-go estimation. However, both the time-to-go formulas used are not derived under the proposed guidance law.…”

Section: Introductionmentioning

confidence: 99%

Impact time control guidance law with field of view constraint

Aerospace Science and Technology

2014

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