Adaptive backstepping impact angle control with autopilot dynamics and acceleration saturation consideration

He, Shaoming; Wang, Wei; Wang, Jiang

doi:10.1002/rnc.3763

Cited by 21 publications

(10 citation statements)

References 37 publications

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“…(12) where t f is the interception time. As indicated in (35) that for a perfect interception (e.g., λ = V λ = 0) with an expected impact angle, there always exists a unique desired LOS angle λ d , which can be obtained by (35)…”

Section: Problem Formulationmentioning

confidence: 99%

Adaptive integrated guidance and control for impact angle constrained interception with actuator saturation

Shen²,

Wang

2019

Aeronaut. j.

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This paper considers the integrated guidance and control (IGC) problem for impact angle constrained interception against manoeuvring targets with actuator saturation constraint. Based on the backstepping technique, an adaptive IGC law is presented to address this problem, where a fixed-time differentiator is proposed to estimate the derivatives of virtual control inputs to avoid the inherent problem of “explosion of complexity” suffered by the typical backstepping. Furthermore, an auxiliary first-order filter is introduced into the IGC law to cope with the actuator saturation constraint. The stability of the closed-loop system is strictly proved. Finally, the superiority of the proposed IGC law is verified by comparison simulations.

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Section: Problem Formulationmentioning

confidence: 99%

Adaptive integrated guidance and control for impact angle constrained interception with actuator saturation

Shen²,

Wang

2019

Aeronaut. j.

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“…e purpose of the AFCBDSM design is to generate an appropriate control law u for equation (14) that can allow x 1 and x 2 to converge to any small neighborhood of zero in finite time and guarantee the closed-loop system is UUB [19], and the system states converge to a small neighborhood of the origin, with limited measurements of x 2 , the control saturation of x 5 , and the unknown bounded disturbances d i .…”

Section: Afcbdsm Designmentioning

confidence: 99%

Integrated Guidance and Control Design of Rolling‐Guided Projectile Based on Adaptive Fuzzy Control with Multiple Constraints

Jiang

Tian

Sun

2019

Mathematical Problems in Engineering

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In the terminal guidance section of large caliber naval gun-guided projectile while striking nearshore maneuvering target, an integrated guidance and control (IGC) method based on an adaptive fuzzy and block dynamic surface sliding mode (AFCBDSM) was proposed with multiple constraints, including the impact angle, control limitations, and limited measurement of the line of sight (LOS) angle rate. The strict feedback cascade model of rolling-guided projectile IGC in space was constructed, and the extended state observer (ESO) was used to estimate the LOS angle rate and uncertain disturbances inside and outside the system, such as target maneuvering, model errors, and wind. A nonsingular terminal sliding mode (NTSM) was designed to zero the LOS angle tracking errors and LOS angle rate in finite time, with the adaptive exponential reaching law. The cascade system was effectively stabilized by the block dynamic surface sliding mode, which prevented differential explosions. To compensate for the saturated nonlinearity of canard control constraints, an adaptive Nussbaum gain function was adopted. The switching chatter of the block dynamic surface sliding mode was reduced through adaptive fuzzy control. Proven by Lyapunov theory, the LOS angle tracking error and LOS angle rate were convergent in finite time, the closed-loop system was uniformly ultimately bounded (UUB), and the system states could be made arbitrarily small at the steady state. Hardware-in-the-loop simulation (HILS) experiments showed that the AFCBDSM provided the guided projectile with good guidance performance while striking targets with different maneuvering forms.

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“…e original control constraint on α becomes a boundary condition on the new state variable. e angle of attack rate is introduced as a new control variable into equation (9) and as a constraint on the angle of attack rate in equation (10). us, the set of feasible controls for Problem 2 are strictly constrained in the set of feasible controls for Problem 1.…”

Section: Lemma 1 If There Exists An Optimization Solution To Problemmentioning

confidence: 99%

“…Li et al [5] used graph theory to derive the impact angle and time constraint guidance law. Sliding mode theory [6][7][8][9] and proportional navigation [10][11][12] have been introduced to achieve the desired impact angle. Optimal control theory has also been implemented to solve optimal guidance law problems under an impact angle constraint [13][14][15][16][17][18], but a limit has not been set on the terminal velocity owing to the complicated form of the aerodynamic coefficients.…”

Section: Introductionmentioning

confidence: 99%

Near‐Optimal Guidance with Impact Angle and Velocity Constraints Using Sequential Convex Programming

Pei

Wang

2019

Mathematical Problems in Engineering

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This paper proposes a near-optimal air-to-ground missile guidance law with impact angle and impact velocity constraints based on sequential convex programming. A realistic aerodynamic model is introduced into the problem formulation, such that traditional optimization theory cannot obtain an analytical solution to the optimization problem under state constraints. The original problem is considered as an optimization problem, and the angle of attack is replaced with the angle of attack rate as a new control variable to reconstruct the problem and simplify the solving process. Next, the independent variable is changed in the differential equations to linearize and discretize the problem such that the reconstructed problem can be solved using sequential convex programming. The results obtained by numerical simulations confirmed that the proposed algorithm is valid and faster than the general-purpose nonlinear optimal control problem solver. Finally, it was verified that different impact angles and impact velocities were achieved.

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Adaptive backstepping impact angle control with autopilot dynamics and acceleration saturation consideration

Cited by 21 publications

References 37 publications

Adaptive integrated guidance and control for impact angle constrained interception with actuator saturation

Adaptive integrated guidance and control for impact angle constrained interception with actuator saturation

Integrated Guidance and Control Design of Rolling‐Guided Projectile Based on Adaptive Fuzzy Control with Multiple Constraints

Near‐Optimal Guidance with Impact Angle and Velocity Constraints Using Sequential Convex Programming

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