Stability analysis of explicit guidance laws for space launch vehicles with varying thrust integrals

Song, Eun-Jung; Cho, Sangbum; Park, Chang-Su; Roh, Woong-Rae; Joh, Miok

doi:10.1016/j.asr.2011.02.014

Cited by 3 publications

(1 citation statement)

References 9 publications

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“…However, the degree of polynomials in defining thrust profile is not the same as direction angles since the variation of thrust magnitude is more restricted. Based on different thrust profiles in researches [19] including neutral, regressive and progressive thrust profiles [20], linear and cubic functions can also be considered for this variable in order to have producible thrust profile at the end of optimization. Regarding this method, the actual optimal control problem will turn into a parameter optimization problem which can be solved using ICA.…”

Section: Optimization Approachmentioning

confidence: 99%

Multi-objective optimization of orbit transfer trajectory using imperialist competitive algorithm

Shirazi

2017

2017 IEEE Aerospace Conference

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Section: Optimization Approachmentioning

confidence: 99%

Multi-objective optimization of orbit transfer trajectory using imperialist competitive algorithm

Shirazi

2017

2017 IEEE Aerospace Conference

View full text Add to dashboard Cite

Asymmetric BLOS constraint-involved intelligent integrated guidance and control approach for flight vehicle equipped with strapdown seeker

Lu,

Guo,

Guo

et al. 2023

Advances in Space Research

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Composite Zero-Effort-Miss Guidance with Predictor–Corrector Steps for Ballistic Interception

Jung,

Lee,

Lee

et al. 2024

Journal of Guidance, Control, and Dynamics

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In this paper, a midcourse guidance law for exoatmospheric interception using a solid-propellant rocket is presented. Existing guidance laws based on the zero-effort-miss concept lack consideration for remaining thrust, potentially resulting in the excessive magnitude and rate of the thrust direction command. To address this issue, the zero-effort-miss concept is combined with an iterative predictor–corrector-based guidance law that is adapted for solid-propellant rockets. To apply the iterative predictor–corrector-based guidance law to the interception problem with a solid-propellant rocket, a composite zero-effort-miss concept is introduced, and the correction step is formulated as an online convex optimization problem. The composite zero-effort-miss consists of two zero-effort-misses. One miss is obtained from current state and the other miss is obtained from predicted state at burnout. Those render the proposed guidance law robust to thrust uncertainty allow for a noniterative approach and eliminate the singularity problem. Also, the proposed guidance law reduces maneuvering during the early part of the midcourse phase, leading to less velocity loss, and resolves intercept performance degradation due to the rate limit of thrust vectoring. Numerical simulations comparing the proposed method with the modified zero-effort-miss guidance demonstrate its effectiveness and robustness.

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Stability analysis of explicit guidance laws for space launch vehicles with varying thrust integrals

Cited by 3 publications

References 9 publications

Multi-objective optimization of orbit transfer trajectory using imperialist competitive algorithm

Multi-objective optimization of orbit transfer trajectory using imperialist competitive algorithm

Asymmetric BLOS constraint-involved intelligent integrated guidance and control approach for flight vehicle equipped with strapdown seeker

Composite Zero-Effort-Miss Guidance with Predictor–Corrector Steps for Ballistic Interception

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