Switched-Gain Guidance for Impact Angle Control Under Physical Constraints

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.

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“…Obviously, B r is a compact set. Consider the definition of x 2c given by equation (11). A direct calculation gives…”

Section: Appendixmentioning

confidence: 99%

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

Zhang

Wang

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…In recent years, studies on homing guidance have dealt with constraints in the angle of impact [3], mostly through the employment of optimal control theory [4][5][6][7][8][9][10][11][12][13]. Moreover, constraints on the maximum acceleration command are also commonly considered [14,15]. As is wellknown, a seeker is essential to homing guidance systems, which is, however, very expensive.…”

Section: Introductionmentioning

confidence: 99%

Cooperative Guidance of Seeker-Less Missiles for Precise Hit

Zhao

Xiong

2019

International Journal of Aerospace Engineering

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A novel cooperative guidance scenario is proposed that implements fire-and-forget attacks for seeker-less missiles with a cheap finder for stationary targets and without requiring real-time communication among missiles or precise position information. Within the proposed cooperative scenario, the classic leader-follower framework is utilized, and a two-stage cooperative guidance law is derived for the seeker-less missile. Linear-quadratic optimal control and biased proportional navigation guidance (PNG) are employed to develop this two-stage cooperative guidance law to minimize the control cost in the first stage and to reduce the maximum acceleration command in the second stage when the acceleration command is continuous. Simulations and comparisons are conducted that demonstrate the effectiveness and advantages of the proposed guidance law.

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“…The integral value was calculated from initial engagement conditions and desired impact angle. Based on the same strategy of [19], a few of two-phased BPN (TPBPN) guidance laws were proposed in [20][21][22][23][24][25] for attacking a stationary target. A TPBPN was proposed in [20] based on the bias-shaping method, which can satisfy both the terminal-angle constraint and the FOV limitation to maintain the seeker's lock-on condition.…”

Section: Introductionmentioning

confidence: 99%

“…Two time-varying biases were adopted in [22] to keep the seeker's look angle and to ensure the terminal impact angle, respectively. Along with the thoughts of TPBPN and composite guidance law, Tekin and Erer [23] proposed the PN-gain-switched strategy, which can admit the allowed look angle and acceleration values to meet the demand of impact angle and at the same time, have a relative simple structure for implementation because of the PN form. Based on a two-stage PN guidance law, Ratnoo [24] derived a closed-form solution for the choice of navigation gains to satisfy the look angle and impact angle limit.…”

Section: Introductionmentioning

confidence: 99%

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A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit

Zhang

Tang

Guo

et al. 2018

International Journal of Aerospace Engineering

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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.

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Switched-Gain Guidance for Impact Angle Control Under Physical Constraints

Cited by 131 publications

References 28 publications

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

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

Cooperative Guidance of Seeker-Less Missiles for Precise Hit

A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit

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