Integrated guidance and control of guided projectile with multiple constraints based on fuzzy adaptive and dynamic surface

Jiang, Shimei; Tian, Fuqing; Sun, Shiyan; Liang, Wei-ge

doi:10.1016/j.dt.2019.12.003

Cited by 24 publications

(14 citation statements)

References 19 publications

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“…It should be noted that the inverse of matrix AB and the generalized inverse of matrix C are included in equation (23).…”

Section: Mathematical Problems In Engineeringmentioning

confidence: 99%

“…In recent years, most studies on the design of the G&C system for air vehicles to impact maneuver target are based on the full-state coupled high-order IGC design model, which contains angles of line-of-sight (LOS), rotational Euler angles of the air vehicle, three-channel body rates, and other motion state variables. e IGC system design is accomplished through the backstepping control method or dynamic surface control method, and the uncertainties containing acceleration components of the target are estimated through some techniques, such as ESO [18][19][20][21][22][23][24], sliding mode observer [25,26], and adaptive law [27]. e effectiveness of this kind of design method has been verified by nonlinear simulation results in the published literatures.…”

Section: Introductionmentioning

confidence: 99%

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A Low-Order Partial Integrated Guidance and Control Scheme for Diving Hypersonic Vehicles to Impact Ground Maneuver Target

Tong¹,

Wang

Pan³

et al. 2021

Mathematical Problems in Engineering

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In this article, a low-order partial integrated guidance and control (PIGC) design method is proposed for diving hypersonic vehicles to impact ground maneuver target. A three-channel analytical model of body rates is deduced based on acceleration components of the hypersonic vehicle. By combining the analytical model of body rates and relative dynamic model between the hypersonic vehicle and target, three-channel commands of body rates are directly generated based on the extended state observer (ESO) technique, sliding mode control approach, and dynamic surface control theory in the guidance subsystem. In the attitude control subsystem, a sliding mode controller is designed to track the commands of body rates and generate commands of control surface fin deflections. By making full use of acceleration information of the hypersonic vehicle measured by the mounted accelerometer, the proposed PIGC design method provides a novel solution to compensate the unknown acceleration of the ground maneuver target. Besides, the order of design model is also reduced, and the design process is simplified. The effectiveness and robustness of the PIGC design method are verified and discussed by 6DOF simulation studies.

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“…It should be noted that the inverse of matrix AB and the generalized inverse of matrix C are included in equation (23).…”

Section: Mathematical Problems In Engineeringmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A Low-Order Partial Integrated Guidance and Control Scheme for Diving Hypersonic Vehicles to Impact Ground Maneuver Target

Tong¹,

Wang

Pan³

et al. 2021

Mathematical Problems in Engineering

View full text Add to dashboard Cite

show abstract

“…[7][8][9] introduced a backstepping guidance law for exoatmospheric missiles with impact angle constraints, while [10] proposed a guidance law based on computational geometry for three-dimensional stationary target interception.Ref. [11] presented an integrated guidance and control approach for naval gun projectiles, which was robust to various constraints, with finite-time convergence proven using Lyapunov stability theory. Ref.…”

Section: Introductionmentioning

confidence: 99%

Adaptive Terminal Time and Impact Angle Constraint Cooperative Guidance Strategy for Multiple Vehicles

Li,

Hu,

Yang

et al. 2024

Drones

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This paper addresses the guidance of various flight vehicles under multiple constraints in three-dimensional space. A cooperative guidance strategy that satisfies both time and angle constraints is designed to reach a moving target. The strategy is organized into two parts: modeling and programming calculations. First, a nonlinear motion model for guidance is established and normalized, including both the vehicle and the target. Later, the arrival method is automatically determined according to the strategy and depending on the type of target. The cooperative terminal time is determined based on an augmented proportional navigation method. An improved model predictive static programming (MPSP) algorithm was designed as a means of adjusting the adaptive terminal time. Then, the algorithm was used to update the control quantity iteratively until the off-target quantity and the angle of constraints were satisfied. The simulation results showed that the strategy could enable multiple flight vehicles at different initial positions to reach the target accurately at the same time and with the ideal impact angle. The strategy boasts a high computational efficiency and is capable of being implemented in real time.

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“…Among these works, the guidance and control schemes regarding sensor and actuator constraints are also suggested [26]. The fuzzy logicbased integrated guidance and control schemes constitutes another class of the projectile guidance [27]. One of the consequences of the inclusion of the unmanned air vehicles into the defence scheme appears as the need of lighter but effective munitions.…”

Section: Introductionmentioning

confidence: 99%

Performance Comparison of Guided Mortar Projectiles with Fixed and Moving Fins

Özkan

Gökçe

2023

Journal of Polytechnic

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Guidance munition has become one of the popular subjects in both the theoretical and applicable studies since they could find a wide field of use in recent years because of their high performance and lower collateral damage capabilities as per the improving defence concept. The use of smaller and lighter guided munition makes the stated advantages increase without relinquishing the effectiveness. In this study, the design of a guidance kit which makes the mortar projectiles become guided when released from aerial platforms and the relevant computer simulations performed upon a selected projectile model are investigated. Here, two different configurations are considered based on the rotational degree of freedom of a pair of fins mounted on a rotary ring. In the simulations in which it is assumed that the guided projectile is released from an unmanned aerial vehicle, the different values of the fin deflection, autopilot switching duration, and side wind are considered for both of the mentioned geometries. Finally, the final miss distance and time of flight values obtained for all the designated cases are compared.

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Integrated guidance and control of guided projectile with multiple constraints based on fuzzy adaptive and dynamic surface

Cited by 24 publications

References 19 publications

A Low-Order Partial Integrated Guidance and Control Scheme for Diving Hypersonic Vehicles to Impact Ground Maneuver Target

A Low-Order Partial Integrated Guidance and Control Scheme for Diving Hypersonic Vehicles to Impact Ground Maneuver Target

Adaptive Terminal Time and Impact Angle Constraint Cooperative Guidance Strategy for Multiple Vehicles

Performance Comparison of Guided Mortar Projectiles with Fixed and Moving Fins

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