Impact Time and Angle Control Guidance

Kumar, Shashi Ranjan; Ghose, Debasish

doi:10.2514/6.2015-0616

Cited by 43 publications

(49 citation statements)

References 25 publications

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“…In [20], Harrison proposed a new method to derive the optimal missile guidance law and proposed a threedimensional hybrid guidance law that constrains the impact angle and time. Kumar and Ghose proposed a guidance strategy based on impact angle control to meet the impact time constraint in [21].…”

Section: Introductionmentioning

confidence: 99%

Three-Dimensional Impact Time and Angle Control Guidance Based on MPSP

Zhang

Chen

2019

International Journal of Aerospace Engineering

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A new nonlinear guidance law for air-to-ground missile cooperation attacks is proposed in this paper. This guidance law enables missiles with different initial conditions to attack targets simultaneously, and it can also precisely satisfy the terminal impact angle conditions in both flight-path angle and heading angle. The guidance law is devised using the model predictive static programming (MPSP) method, and the control saturation constraint is incorporated in the MPSP algorithm. The first-order-lag acceleration of the missile is taken as the state variable to realize the convergence of the terminal acceleration to zero. Moreover, a collision avoidance strategy for three-dimensional missile cooperative flight is proposed. The simulation results show that the guidance law can make the missiles hit the target accurately at the same time with the ideal impact angles and can realize the control saturation constraints of the missiles. This can increase the attack effects and is significant for collaborative attacks.

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Section: Introductionmentioning

confidence: 99%

Three-Dimensional Impact Time and Angle Control Guidance Based on MPSP

Zhang

Chen

2019

International Journal of Aerospace Engineering

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“…However, an approximate path integrand is obtained by Taylor series approximation. Kumar and Ghose [11,12] proposed sliding mode control-based guidance laws for impact time control. Approximate methods were used to obtain the time-to-go estimate for proportional navigation guidance law using a formula in terms of heading error [11] and by using the curvature of the trajectory toward the interception point [12].…”

Section: Introductionmentioning

confidence: 99%

“…Kumar and Ghose [11,12] proposed sliding mode control-based guidance laws for impact time control. Approximate methods were used to obtain the time-to-go estimate for proportional navigation guidance law using a formula in terms of heading error [11] and by using the curvature of the trajectory toward the interception point [12]. Kim et al [13] presented a polynomial guidance command with constraints on impact time, impact angle, and zero miss distance.…”

Section: Introductionmentioning

confidence: 99%

Lyapunov-Based Guidance Law for Impact Time Control and Simultaneous Arrival

Saleem

Ratnoo

2016

Journal of Guidance, Control, and Dynamics

124

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“…However, the impact time control parameters had to be calculated using an offline complex algorithm for each engagement scenario. Recently, a new strategy was presented based on switching between an impact time control guidance law and an impact angle guidance law [19]. In this scheme, the guidance law corrected the impact time in its first step and then switched to an anglecontrol guidance law when the time error was reduced to an acceptable value.…”

Section: Introductionmentioning

confidence: 99%

“…Simulations highlight the viability and robustness of the guidance law. Compared with other methods in the literatures [18,19], the proposed guidance law does not require the offline algorithm to calculate the impact time parameter and there is no abrupt jump in the acceleration command during the engagement.…”

Section: Introductionmentioning

confidence: 99%

A New Impact Time and Angle Control Guidance Law for Stationary and Nonmaneuvering Targets

Yang

Wang

Lin

et al. 2016

International Journal of Aerospace Engineering

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A guidance problem for impact time and angle control applicable to cooperative attack is considered based on the sliding mode control. In order to satisfy the impact angle constraint, a line-of-sight rate polynomial function is introduced with four tuning parameters. And the time-to-go derivative with respect to a downrange orientation is derived to minimize the impact time error. Then the sliding mode control surface with impact time and angle constraints is constructed using nonlinear engagement dynamics to provide an accurate solution. The proposed guidance law is easily extended to a nonmaneuvering target using the predicted interception point. Numerical simulations are performed to verify the effectiveness of the proposed guidance law for different engagement scenarios.

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Impact Time and Angle Control Guidance

Cited by 43 publications

References 25 publications

Three-Dimensional Impact Time and Angle Control Guidance Based on MPSP

Three-Dimensional Impact Time and Angle Control Guidance Based on MPSP

Lyapunov-Based Guidance Law for Impact Time Control and Simultaneous Arrival

A New Impact Time and Angle Control Guidance Law for Stationary and Nonmaneuvering Targets

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