Trajectory-Shaping Guidance with final speed and load factor constraints

Yu, Wenbin; Chen, Wanchun

doi:10.1016/j.isatra.2014.11.017

Cited by 17 publications

(8 citation statements)

References 18 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Finally, the proposed method is compared with the existing guidance laws 18,19 that consider the missile's velocity variation. First, the authors in Xiong et al.…”

Section: Numerical Simulationsmentioning

confidence: 99%

“…Second, in Yu and Chen, 18 the trajectory shaping guidance (TSG) law has been developed by utilizing a form of the generalized vector explicit (GENEX) guidance 3 as where the parameters C'1 and C'2 represent the guidance gains of the GENEX. In Yu and Chen, 18 the guidance gains of the GENEX that ensure the stability under the velocity variation were determined. As provided in Yu and Chen, 18 the guidance gains are chosen as C'1=10.5 and C'2=-5 in this simulation.…”

Section: Numerical Simulationsmentioning

confidence: 99%

“…In Yu and Chen, 18 the guidance gains of the GENEX that ensure the stability under the velocity variation were determined. As provided in Yu and Chen, 18 the guidance gains are chosen as C'1=10.5 and C'2=-5 in this simulation. For the sake of a fair comparison, the weighting function is selected as W(t)=tgo N in the proposed method because the GENEX can be obtained by assuming no dynamic lag effect and constant velocity with W(t)=tgo N.…”

Section: Numerical Simulationsmentioning

confidence: 99%

“…The performance degradation becomes more severe when a missile is subject to a large velocity variation. 14,15 Therefore, as reported in the literature, 16–19 when designing a guidance law, the missile velocity variation needs to be considered to improve the guidance performance.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Practical generalized optimal guidance law with impact angle constraint

Lee

Ryu

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

In this paper, we provide a practical solution to the generalized optimal guidance problem with an impact angle constraint. The optimal guidance problem with arbitrary weighting functions is extended to explicitly consider a missile dynamic lag effect as well as a missile velocity variation. Therefore, compared to existing results, the proposed result can prevent performance degradation due to the dynamic lag effect and the velocity variation, which is an essential issue in practice. Besides, since the proposed guidance law is formulated from the generalized optimal control framework, it can directly inherit a vital feature of the framework: providing an additional degree of freedom in shaping a guidance command for achieving a specific guidance operational goal. An illustrative example is provided in order to validate this property. In this study, the proposed solution is also compared with the existing solutions. The comparison results indicate that the proposed result is a more general and practical solution. Finally, numerical simulations are also conducted to demonstrate the practical significance of the proposed method.

show abstract

“…Finally, the proposed method is compared with the existing guidance laws 18,19 that consider the missile's velocity variation. First, the authors in Xiong et al.…”

Section: Numerical Simulationsmentioning

confidence: 99%

Section: Numerical Simulationsmentioning

confidence: 99%

Section: Numerical Simulationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Practical generalized optimal guidance law with impact angle constraint

Lee

Ryu

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…Yu et al. 14 obtained the generalized closed-form solutions of the explicit guidance and got the stability domain of the guidance coefficients by analyzing the generalized solutions. By considering the impact angle and AOA constraints successively, Xing et al.…”

Section: Introductionmentioning

confidence: 99%

Optimal perturbation guidance with constraints on terminal flight-path angle and angle of attack

Zhao

Chen

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

Self Cite

View full text Add to dashboard Cite

This paper presents the design of a singular-perturbation-based optimal guidance with constraints on terminal flight-path angle and angle of attack. By modeling the flight-control system dynamics as a first-order system, the angle of attack is introduced into the performance index as a state variable. To solve the resulting high-order optimal guidance problem analytically, the posed optimal guidance problem is divided into two sub-problems by utilizing the singular perturbation method according to two time scales: range, altitude, and flight-path angle are the slow time-scale variables while the angle of attack is the fast time-scale variable. The outer solutions are the optimal control of the slow-scale subsystem. Thereafter, by applying the stretching transformation, the fast-scale subsystem establishes the relationships between the outer solutions and acceleration command. Then, the optimal command can be obtained by solving the fast-scale subsystem also using the optimal control theory. The proposed guidance can achieve a near-zero terminal acceleration as well as a small miss distance. The superior performance of the guidance is demonstrated by adequate trajectory simulations.

show abstract

Omnidirectional Autonomous Reentry Guidance Based on 3-D Analytical Glide Formulae Considering Influence of Earth’s Rotation

Chen

Zhang

et al. 2020

Steady Glide Dynamics and Guidance of Hypersonic Vehicle

View full text Add to dashboard Cite

Trajectory-Shaping Guidance with final speed and load factor constraints

Cited by 17 publications

References 18 publications

Practical generalized optimal guidance law with impact angle constraint

Practical generalized optimal guidance law with impact angle constraint

Optimal perturbation guidance with constraints on terminal flight-path angle and angle of attack

Omnidirectional Autonomous Reentry Guidance Based on 3-D Analytical Glide Formulae Considering Influence of Earth’s Rotation

Contact Info

Product

Resources

About