Practical Solution to Efficient Flight Path Control for Hypersonic Vehicles

Wu, Qi; Sun, Mingwei; Wang, Zenghui; Chen, Zengqiang

doi:10.2322/tjsass.59.195

Cited by 9 publications

(7 citation statements)

References 33 publications

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“…This can provide a practical guidance law for a hypersonic vehicle to achieve periodic cruise; otherwise, it is difficult to implement accurate tracking of the altitude, as shown in Equation (10), due to the slow altitude response [37][38][39][40]. According to Equation (10), the cycle range is…”

Section: Augmented States Based Periodic Cruise Optimizationmentioning

confidence: 99%

General Periodic Cruise Guidance Optimization for Hypersonic Vehicles

Gao

Chen²,

Sun

et al. 2020

Applied Sciences

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Periodic cruise has the potential to improve the fuel efficiency of a hypersonic vehicle. However, the optimization of periodic cruise is very difficult and can only be performed inefficiently through trial-and-error due to the parameterized form. In this paper, we systematically optimized the hypersonic periodic cruise using the pseudo-spectral method (PSM) scheme. We specify the main variables as the given forms of periodic functions and parameterize the periodic guidance. The characteristic parameters can then be considered as augmented states to generate augmented dynamics. Therefore, periodic cruise optimization can be directly obtained by using GPOPS (Gauss Pseudo-spectral OPtimization Software). The numerical results demonstrate the effectiveness of the proposed method. The approach in this case study can be generalized to solve similar trajectory optimization problems that can be parameterized in a unified manner.

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Section: Augmented States Based Periodic Cruise Optimizationmentioning

confidence: 99%

General Periodic Cruise Guidance Optimization for Hypersonic Vehicles

Gao

Chen²,

Sun

et al. 2020

Applied Sciences

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“…Regarding the aforementioned challenges, many control methods have been employed. Fixed-order robust control, 4 linear quadratic regulator (LQR) [5][6][7] and linear active disturbance rejection control (LADRC) 8,9 have been investigated within the linear control framework. As for the nonlinear control methods, adaptive control, 10,11 nonlinear predictive control, 12,13 sliding mode control, [14][15][16][17] neural network control 18 and trajectory linearization control 19 have been applied.…”

Section: Introductionmentioning

confidence: 99%

“…Among these methods, the concentration was mainly on the robust tracking control of the longitudinal dynamics under diverse uncertainties. The uncertainty and disturbance estimation and attenuation (DUEA) technique termed by Chen et al 20 has been incorporated into different control methods mentioned above 8,9,12,[15][16][17]19 to enhance the performance robustness to uncertainties. In this two degree-of-freedom (DOF) control paradigm, uncertainty attenuation and tracking are handled separately by the disturbance observer (DOB) and the normal feedback controller, respectively.…”

Section: Introductionmentioning

confidence: 99%

“…[29][30][31][32] Motivated by the advantages of ADRC mentioned above, a practical three-channel attitude control scheme is proposed for the HSV to handle the strong uncertainties, nonlinearities and coupling effects in this paper. In the most of the published papers on HSV control, [4][5][6][7][8][10][11][12][13][14][15][16][17][18][19] only the pitch channel was concentrated on and the designed flight envelopes of the altitude and velocity were relatively small. One previous work of three-channel LADRC design for the HSV only considered one characteristic point under the weak coupling case.…”

Section: Introductionmentioning

confidence: 99%

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A practical attitude control scheme for hypersonic vehicle based on disturbance observer

Piao

Zhihong²,

Sun

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper proposes a practical three-channel attitude control scheme for hypersonic vehicle based on the linear active disturbance rejection control. The control scheme considers the weak and strong coupling scenarios separately due to the dynamic characteristics. For the weak coupling case, three linear active disturbance rejection controllers are designed for the Euler angles of the three channels, respectively, to deal with the strong uncertainties. The expected stability margin and dynamic performance can be guaranteed through the stability margin tester tuning method. Moreover, the control scheme for the pitch, yaw, and roll angles can be applied to the control of the angle of attack, the sideslip angle and the bank angle directly according to the flight dynamics of the hypersonic vehicle, thus realizing a unified control framework for all the attitude angles. For the strong coupling scenario like the fast reversal maneuver, the inner-loop angular rate feedback is performed first in this paper to enhance the damping characteristics, and then linear active disturbance rejection control is designed for the augmented plant to eliminate the strong coupling effects. Simulation results demonstrate the satisfactory tracking and disturbance rejection ability of the proposed methods.

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“…Since the sliding mode control (SMC) method was firstly proposed, it has attracted a lot of researchers worldwide [7,8] due to its robustness to parameter perturbations and external Y. Wang, M. Sun, S. Du, and Z. Chen linear observer is simple and there is only one tunable parameter, it has demonstrated its effectiveness when applied to control diverse nonlinear systems [17][18][19][20][21]. In addition, a binary distillation column can be controlled by using a linear proportional-integral observer in [22].…”

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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Practical Solution to Efficient Flight Path Control for Hypersonic Vehicles

Cited by 9 publications

References 33 publications

General Periodic Cruise Guidance Optimization for Hypersonic Vehicles

General Periodic Cruise Guidance Optimization for Hypersonic Vehicles

A practical attitude control scheme for hypersonic vehicle based on disturbance observer

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

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