Partial Integrated Guidance and Control for Missiles with Three-Dimensional Impact Angle Constraints

Wang, Xianghua; Wang, Jinzhi

doi:10.2514/1.60133

Cited by 72 publications

(44 citation statements)

References 22 publications

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“…According to Equation (20), the rate of convergence increases with the value of β. Moreover, in practice, the absolute value of the initial angular rate of LOS |ω s (0)| must be significantly smaller than 1 rad/s.…”

Section: Theorem 1: Consider the Guidance System (15) If There Existmentioning

confidence: 99%

“…Zhou, et al [7] proposed a finite time convergence guidance law specifically designed for the interception of maneuverable targets that was able to guarantee LOS rate convergence in finite time, but required knowledge of the upper bound of the target acceleration. Wang, et al [20] proposed a partiallyintegrated sliding mode guidance law; however, the law was quite complex and required the use of higher order variables in the guidance command that proved difficult to measure, and had to be estimated by a sliding mode observer.…”

Section: Introductionmentioning

confidence: 99%

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Intelligent guidance method based on differential geometric guidance command and fuzzy self-adaptive guidance law

Zhang

Long

2015

IFS

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Abstract. Differential geometric guidance command (DGGC) is widely acknowledged as a better method of endoatmospheric interception than three-dimensional (3D) pure proportional navigation (PPN). DGGC can be regarded as an intelligent method due to its sophisticated sense of Lyapunov. However, traditional DGGC cannot guarantee line of sight (LOS) finite time convergence (FTC) to zero against maneuvering targets, particularly in regard to a stable, robust trajectory, which effectively lowers the overall intelligence of the method. This study proposes employment of the fuzzy self-adaptive guidance law to estimate target acceleration and enhance guidance intelligence, which in turn enhances the intelligence of the traditional DGGC method, making it more adaptive and applicable to practical interception scenarios. Finally, the effectiveness of this newly-proposed guidance method is demonstrated by numerical simulation.

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Section: Theorem 1: Consider the Guidance System (15) If There Existmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Intelligent guidance method based on differential geometric guidance command and fuzzy self-adaptive guidance law

Zhang

Long

2015

IFS

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“…The past few years have witnessed rapidly growing interest in the IGC design, and many approaches have been reported [6]- [13]. It is well known that sliding mode control is an effective technology to deal with system disturbance and parameter uncertainty.…”

Section: Introductionmentioning

confidence: 99%

“…Theoretical analysis shows that both the LOS angular rate and the tracking error of the attitude angle (rate) are practically stable with respect to target maneuvers and missile model uncertainties. However, most of the above design methods [6]- [13] have not considered the uncertainties and disturbances or dealt with the effect of system disturbances at the price of sacrificing the normal control performance.…”

mentioning

confidence: 99%

Integrated Guidance and Control Design for the Near Space Interceptor

Wang¹,

Liu²,

Liang³

2015

International Journal of Aeronautical and Space Sciences

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Considering the guidance and control problem of the near space interceptor (NSI) during the terminal course, this paper proposes a three-channel independent integrated guidance and control (IGC) scheme based on the backstepping sliding mode and finite time disturbance observer (FTDO). Initially, the three-channel independent IGC model is constructed based on the interceptor-target relative motion and nonlinear dynamic model of the interceptor, in which the channel coupling term and external disturbance are regarded as the total disturbances of the corresponding channel. Then, the FTDO is introduced to estimate the target acceleration and control system loop disturbances, and the feed-forward compensation term based on the estimated values is employed to effectively remove the effect of disturbances in finite time. Subsequently, the IGC algorithm based on the backstepping sliding mode is also given to obtain the virtual control moment. Furthermore, a robust least-squares weighted control allocation (RLSWCA) algorithm is employed to distribute the previous virtual control moment among the corresponding aerodynamic fins and reaction jets, which also takes into account the uncertainty in the control effectiveness matrix. Finally, simulation results show that the proposed IGC method can obtain the small miss distance and smooth interceptor trajectories.

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“…The first category method mainly focuses on the twoloop control structure in an IGC framework, and the outer loop and inner loop are separated in the guidance and control system [9][10][11][12] due to inherent time scale separation between the faster and slower dynamics. Although the outer loop takes the body rates as the virtual control input to directly yield the body rate command and the inner loop tracks the body rate commands with fin deflections as the control inputs, the settling time of response of different loops affects the performance of the whole system due to the delay problem.…”

Section: Introductionmentioning

confidence: 99%

New Integrated Guidance and Control of Homing Missiles with an Impact Angle against a Ground Target

Yang

Guo

Zhou

2018

International Journal of Aerospace Engineering

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A new integrated guidance and control (IGC) law is investigated for a homing missile with an impact angle against a ground target. Firstly, a control-oriented model with impact angle error of the IGC system in the pitch plane is formulated by linear coordinate transformation according to the motion kinematics and missile dynamics model. Secondly, an IGC law is proposed to satisfy the impact angle constraint and to improve the rapidity of the guidance and control system by combining the sliding mode control method and nonlinear extended disturbance observer technique. Thirdly, stability of the closed-loop guidance and control system is proven based on the Lyapunov stability theory, and the relationship between the accuracy of the impact angle and the estimate errors of nonlinear disturbances is derived from stability of the sliding mode. Finally, simulation results confirm that the proposed IGC law can improve the performance of the missile guidance and control system against a ground target.

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Partial Integrated Guidance and Control for Missiles with Three-Dimensional Impact Angle Constraints

Cited by 72 publications

References 22 publications

Intelligent guidance method based on differential geometric guidance command and fuzzy self-adaptive guidance law

Intelligent guidance method based on differential geometric guidance command and fuzzy self-adaptive guidance law

Integrated Guidance and Control Design for the Near Space Interceptor

New Integrated Guidance and Control of Homing Missiles with an Impact Angle against a Ground Target

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