Three‐dimensional nonlinear<i>H</i><sub>∞</sub>guidance law

Yang, Ciann-Dong; Chen, Hsin Yuan

doi:10.1002/rnc.552

Cited by 32 publications

(29 citation statements)

References 25 publications

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“…Nonetheless, the target velocity variation was not considered in [4], and the optimal guidance law from [5] can be realised only in the presence of accurate knowledge of the target manoeuvre. An H � guidance law was proposed in [6], wherein the target manoeuvre was treated as an unpredictable disturbance, and a favourable interception performance for arbitrary scenarios of target manoeuvres could be guaranteed if the target acceleration is bounded; however, the huge computational complexity is a severe constraint to the implementation of this H � method. These deficiencies limit the practical applications of the above strategies.…”

Section: Introductionmentioning

confidence: 99%

Comparative investigations of nonlinear and linear observers for a highly manoeuvrable target in sliding mode guidance

Wang¹,

Sun²,

Du³

et al. 2017

Bulletin of the Polish Academy of Sciences Technical Sciences

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Abstract. Target manoeuvre is one of the key factors affecting guidance accuracy. To intercept highly maneuverable targets, a second-order sliding-mode guidance law, which is based on the super-twisting algorithm, is designed without depending on any information about the target motion. In the designed guidance system, the target estimator plays an essential role. Besides the existing higher-order sliding-mode observer (HOSMO), a first-order linear observer (FOLO) is also proposed to estimate the target manoeuvre, and this is the major contribution of this paper. The closed-loop guidance system can be guaranteed to be uniformly ultimately bounded (UUB) in the presence of the FOLO. The comparative simulations are carried out to investigate the overall performance resulting from these two categories of observers. The results show that the guidance law with the proposed linear observer can achieve better comprehensive criteria for the amplitude of normalised acceleration and elevator deflection requirements. The reasons for the different levels of performance of these two observer-based methods are thoroughly investigated.Key words: guidance law, second-order sliding mode, super-twisting algorithm, linear observer, target manoeuvre. matched disturbances. However, the chattering phenomenon is the major obstacle for the implementation of SMC in practice, and a number of methods have been proposed to reduce the chattering. Levant first proposed the higher-order sliding mode (HOSM) control method to attenuate the chattering [9][10][11][12]. The second-order sliding mode control is the most widely used HOSM method in which the super-twisting algorithm is utilised to attenuate the differentiable disturbance and ensure the finite-time stability [13,14]. To intercept highly manoeuvrable targets, the second-order sliding mode methods were utilised in [13] and [14], based on the nonlinear observers, which are used to check the uncertainty caused by target manoeuvres. However, in many simulations, it is readily observed that the guidance commands (acceleration) generated by the proposed guidance laws of [13] and [14] exhibit the properties of oscillation with a large amplitude. Comparing the fundamental guidance component with the observer component, the latter contributes to this phenomenon much more. Hence, an effective estimation approach is urgently needed to deal with highly manoeuvrable targets.Han proposed a novel philosophy, namely the active disturbance rejection control (ADRC) algorithm [15,16], which has attracted wide attention in the past decade. The core of ADRC is an extended state observer (ESO) that can accurately observe the total disturbance. Han originally presented the ESO in a nonlinear form [15], which is too complicated to tune, and is difficult to be implemented. In [16], a linear ESO (LESO) was proposed in terms of frequency bandwidth, which provides a useful design approach in practical applications. Although this

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Section: Introductionmentioning

confidence: 99%

Comparative investigations of nonlinear and linear observers for a highly manoeuvrable target in sliding mode guidance

Wang¹,

Sun²,

Du³

et al. 2017

Bulletin of the Polish Academy of Sciences Technical Sciences

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show abstract

“…To intercept the larger maneuvering target, some advanced control methods have also been applied to the guidance law, such nonlinear H∞ guidance law [2,3], sliding mode guidance (SMG) law [4], and so on. However, the above methods dealt with the influence of the target maneuvers at the price of sacrificing the normal guidance performance.…”

Section: Introductionmentioning

confidence: 99%

“…In particular, the nonlinear H∞ control problem relies on the solution of the Hamilton-Jacobi-Isaacs (HJI) equation, which is a partial differential equation (PDE) and notoriously difficult to solve both numerically and analytically. SMG is an efficient method to deal with the influence of the target maneuver and parameter uncertainties, but chattering is an unavoidable problem of engineering application [4]. The saturation function and boundary layer method are often used to alleviate the chattering at the price of the disturbance rejection performance.…”

Section: Introductionmentioning

confidence: 99%

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A Sliding Mode Guidance Law with ESO for Near Space Interceptor

Wang¹,

Jia²,

Li³

et al. 2017

dtcse

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Abstract. Considering the autopilot dynamic characteristics of the near space interceptor and the target maneuver, a novel sliding mode guidance law is proposed based on the extended state observer (ESO). Firstly, the ESO is constructed to estimate the target acceleration of the disturbances for the guidance system, and the disturbance estimated values are employed as the feed-forward compensation term to obtain the robustness of the target maneuver and system disturbances. Then, a novel sliding mode guidance law based on the ESO is given. Finally, simulation results for the near space interceptor guidance system show that the proposed guidance law can not only overcome the effect of the autopilot dynamic delay and target maneuver, but also ensure the accurate guidance results.

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“…For highly maneuvering targets, robust guidance laws can be effective. Recently, many approaches have been presented to achieve robust guidance laws, such as H  guidance law [3][4], first-order sliding mode guidance laws [5][6][7] and Lyapunov-based nonlinear guidance laws [8][9][10].…”

Section: Introductionmentioning

confidence: 99%