Integrated guidance and control design for the hypersonic interceptor based on adaptive incremental backstepping technique

Chang, Jing; Guo, Zongyi; Cieslak, Jérôme; Chen, Weisheng

doi:10.1016/j.ast.2019.03.058

Cited by 29 publications

(11 citation statements)

References 27 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Theorem 2. For system (15), which satisfies Assumptions 1-3, the closed-loop system is UUB, and the system states could be made arbitrarily small at the steady state, with the application of the ESO given by equations (16) and (17), the block dynamic surface sliding mode given by equations (18) and (26), the control law given by equations (22) and (37), and the appropriate parameter selections.…”

Section: System Stability Analysismentioning

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

View full text Add to dashboard Cite

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.

show abstract

Section: System Stability Analysismentioning

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

View full text Add to dashboard Cite

show abstract

“…As a matter of fact, the HFV dynamic is six-degrees-of-freedom (six-DOF) model, including three translational DOF and three rotational DOF. 23 For convenience, the influence of lateral force on the HFV is neglected when we analyze some specific problems. As a result, a longitudinal model of the HFV is constructed.…”

Section: Introductionmentioning

confidence: 99%

Integrated design of adaptive fault-tolerant control for non-minimum phase hypersonic flight vehicle system with input saturation and state constraints

Wang

Peng

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

In this paper, for the six-degree-of-freedom (six-DOF) model of hypersonic flight vehicle (HFV) subject to actuator faults, state constraints, parametric uncertainties, and external disturbances, an adaptive fault tolerant control (FTC) scheme is proposed based on barrier Lyapunov functions (BLFs). The study is begun with a series of control-oriented manipulations: at first, due to the high complexity of the six-DOF model, the corresponding simplified model is proposed under reasonable assumptions; then, through the stability analysis of the internal dynamics, we can conclude that the vehicle model is a non-minimum phase system, namely, having unacceptable zero-dynamics. In order to solve the non-minimum phase problem, the elevator-to-lift coupling term is regarded as uncertainty of the model. Subsequently, in consideration of the insufficient control torque caused by the fault of the rudder or elevators, an adaptive fault-tolerant controller is designed based on BLFs, backstepping method, and Nussbaum gains. In the control law, the uncertain parameters are replaced by their estimates updated by adaptive laws. And the angle of attack and the roll angle of the aircraft are constrained in the preset range. Additionally, the convergence of the proposed FTC algorithm and the boundedness of all the signals of the closed system is proved by Lyapunov stability theory. At last, the numerical simulation results of the six-DOF model are carried out to manifest the effective tracking performance of the proposed FTC scheme.

show abstract

“…Therefore, near-zero miss distance is necessary for successful interception. [1][2][3][4] In order to accomplish hit-to-kill, the missiles' controller can be designed under the classic frame 5 or the integrated guidance and control (IGC) frame. [6][7][8] Different from the classic frame in which the guidance loop and the control loop are analyzed and designed independently, the IGC frame enables the two circuits to work synergistically.…”

Section: Introductionmentioning

confidence: 99%

“…is named "DSC-NNs", where only the tracking error is considered in the neural design.The parameters of missile are given as follows: m = 144 kg, S = 0.0286m 2 , l = 0.1888m, I yy = 136 kg⋅m 2 , g = 9.81 m∕s 2 , 𝜌 = 0.2641 kg∕m3 , 𝜃 0 = 0.315 rad, 𝛾 M0 = 0.215 rad, 𝛾 T0 = 𝜋 rad. The wind speed is assumed asV W = 12m∕s.The limits of the normal acceleration and elevator deflection of the missile are given as |n L | ≤ 500 m∕s2 and |𝛿 e | ≤ 30 deg.…”

mentioning

confidence: 99%

Neural learning control of missile interception against dynamics uncertainty and target evasive maneuver

Yan

Guo

et al. 2022

Intl J Robust & Nonlinear

View full text Add to dashboard Cite

The integrated guidance and control (IGC) design for the advanced interceptors against targets in progress of implementing evasive maneuvers is investigated. During interception, the target's unknown maneuver accelerations, and the extra angle of attack (AOA) caused by wind effects, are considered as disturbances. For the sake of enough hit‐to‐kill accuracy under multisource disturbances, the neural networks (NNs) and disturbance observer (DOB) are applied to solve the model inaccuracy and external disturbance. As a result, a novel DOB‐based neural controller can accomplish high tracking accuracy and hit‐to‐kill interception performance can be accomplished. Simulations studies demonstrate the validity and advantage bring by the DOB‐based neural control.

show abstract

Integrated guidance and control design for the hypersonic interceptor based on adaptive incremental backstepping technique

Cited by 29 publications

References 27 publications

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

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

Integrated design of adaptive fault-tolerant control for non-minimum phase hypersonic flight vehicle system with input saturation and state constraints

Neural learning control of missile interception against dynamics uncertainty and target evasive maneuver

Contact Info

Product

Resources

About