Optimal terminal guidance for exoatmospheric interception

Yu, Wenbin; Chen, Wanchun; Yang, Liang; Liu, Xiaoming; Zhang, Hao

doi:10.1016/j.cja.2016.04.019

Cited by 10 publications

(8 citation statements)

References 25 publications

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“…Substituting equation (36) into equation (35) and comparing with equation (30), the KKT conditions can be denoted by a system of transcendental equations as follows:…”

Section: Derivation Of the Kkt Conditionsmentioning

confidence: 99%

“…In order to demonstrate its superb performance, several typical guidance laws, which have been widely implemented for exoatmospheric interception, are also applied for comparison. Those guidance laws include proportional navigation (PN) [34], augmented proportional navigation (APN) [35], and optimal terminal guidance (OTG) [36]. It should be noted that these three methods are different from their gravity models.…”

Section: Application In the Midcourse Guidancementioning

confidence: 99%

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Optimal Midcourse Guidance Algorithm for Exoatmospheric Interception Using Analytical Gradients

Chen

Yang

et al. 2019

International Journal of Aerospace Engineering

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This paper is aimed at providing a semianalytical method to solve the optimal exoatmospheric interception problem with the minimum fuel consumption. A nonlinear programming (NLP) problem with the minimum velocity increment, which involves Lambert’s problem with unspecified time-of-flight, is firstly formulated. Then, a set of Karush-Kuhn-Tucker conditions and the Jacobian matrix corresponding to those conditions are derived in an analytical manner, even though the derivatives are mathematically complicated and computationally onerous. Therefore, the Newton-Raphson method can be used to efficiently solve this problem. To further decrease computational cost, a near-optimal initialization method reducing the dimension of the search space is presented to provide a better initial guess. The performance of the proposed method is assessed by numerical experiments and comparison with other methods. The results show that this method is not only of high computational efficiency and accuracy but also applicable to onboard guidance.

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“…Substituting equation (36) into equation (35) and comparing with equation (30), the KKT conditions can be denoted by a system of transcendental equations as follows:…”

Section: Derivation Of the Kkt Conditionsmentioning

confidence: 99%

Section: Application In the Midcourse Guidancementioning

confidence: 99%

Optimal Midcourse Guidance Algorithm for Exoatmospheric Interception Using Analytical Gradients

Chen

Yang

et al. 2019

International Journal of Aerospace Engineering

Self Cite

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“…(1) If̂2 − 2 = 0, compare the first formula in (8) with that in (28) to get̂− = 0. Thus, Theorem 3 is established (2) If̂2− 2 ̸ = 0, due to → +∞, then tanh(̂/ ) → 0; it can be obtained that…”

Section: Fcdo Designed Based On Fcdmentioning

confidence: 99%

“…Bardhan and Ghose designed a differential game guidance law to meet the angle constraint for maneuvering targets [7]. Yu et al designed an optimal guidance law, which can satisfy the terminal angle constraint based on the principle of the most fuel-saving [8]. However, the guidance laws mentioned above are of poor anti-interference performance and cannot effectively intercept the low-altitude target in the clutter background.…”

Section: Introductionmentioning

confidence: 99%

A Composite Guidance Law for Suppressing Measurement Noise of LOS Angular Rate

Feng

2019

Mathematical Problems in Engineering

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To effectively intercept a low-altitude target in clutter background, a nonsingular fast terminal sliding mode guidance law is designed. The designed guidance law can fully exploit the fast convergence characteristics of linear sliding mode control and the finite-time-convergent characteristics of terminal sliding mode control to ensure that the line-of-sight (LOS) angle converges to a desired angle in a limited time at a faster rate. Utilizing the smooth switching characteristics of the hyperbolic tangent function similar to the saturation function, a finite-time-convergent differentiator is designed. Meanwhile, a new finite-time-convergent disturbance observer designed on the tracking differentiator can effectively track the ideal LOS angular rate, suppress the measurement noise, and make a smooth estimation of the target maneuvering acceleration in clutter background. Combining the estimated value of the disturbance observer, the sign function with switch coefficient is introduced to design a composite nonsingular fast terminal sliding mode guidance law. The simulation results show that the composite guidance law can not only effectively suppress the measurement noise of the LOS angular rate and improve the accuracy of low-altitude target intercepting, but also greatly reduce the energy consumption in the interception process.

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“…Optimal control and estimation theory have been commonly used in the design of advanced guidance systems from the late 1960s [2][3][4][5][6][7][13][14][15][16]. Such approaches have been used to develop tracking algorithms that extract the maximum amount of information about a target trajectory.…”

Section: Introductionmentioning

confidence: 99%

An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance

Nguyen¹,

Nguyen²

2020

AJAE

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The guidance laws are commonly designed to yield as small a miss distance as possible, harmonious with the missile's acceleration capability. In recent decades, the concept of optimized guidance law is well understood in applications where information concerning the target range and line-of-sight angle is available. Researchers' efforts have been continually made to apply modern control theory to conventional and adaptive autopilot designs, even though the classical theory is still applicable to autopilots. It can be noted that it is desirable to perform a detailed computer-aided feasibility study within the context of a realistic missile-target engagement model. Development and evaluation of guidance and control laws for simplified missile-target engagement scenarios are extended and adapted to the air-to-air missile situation and implemented in a complete three-dimensional engagement model. Thus, this study proposed a computational method for constructing an optimal midcourse guidance law, which is based on the optimal control theory and initial boundary conditions. This proposed guidance law is derived from an optimal control theory with the boundary conditions such as allowed relative distance between missile and target at the final time, low line-of-sight rate. A numerical simulation verifies the performance of this guidance law with the impact of harmonic wind. The simulation results demonstrate that the quality of effectiveness as well as the applicability of this proposed algorithm.

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Optimal terminal guidance for exoatmospheric interception

Cited by 10 publications

References 25 publications

Optimal Midcourse Guidance Algorithm for Exoatmospheric Interception Using Analytical Gradients

Optimal Midcourse Guidance Algorithm for Exoatmospheric Interception Using Analytical Gradients

A Composite Guidance Law for Suppressing Measurement Noise of LOS Angular Rate

An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance

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