Multi-constrained ascent guidance for solid propellant launch vehicles-Reference-Cited by-同舟云学术

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Multi-constrained ascent guidance for solid propellant launch vehicles

Published:2018-05 Issue: Volume:76 Page:260-271
ISSN:1270-9638
Container-title:Aerospace Science and Technology
language:en
Short-container-title:Aerospace Science and Technology

Author:

Xu Zhi,Zhang Qian^ORCID

Publisher

Elsevier BV

Subject

Aerospace Engineering

Reference18 articles.

1. Solid propulsion systems for epsilon launch vehicle;Tokudome,2012

2. Ascent guidance for responsive launch: a fixed-point approach;Lu,2005

3. An optimal explicit guidance scheme for ballistic missiles with solid motor;Padhi,1999

4. Study on guidance strategy for solid propellant launcher;Pietrobom,2011

5. Closed-Loop Nominal and Abort Atmospheric Ascent Guidance for Rocket-Powered Launch Vehicles;Dukeman,2005

Cited by 16 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Approximate analytical solutions for three-dimensional ascent trajectory of a solid-fuel launch vehicle;Chinese Journal of Aeronautics;2024-06

2. Three-Dimensional Ascent Guidance Method for Two-Stage Solid Rocket Launch Vehicles under Multiple Constraints and Uncertainties;Journal of Aerospace Engineering;2024-01

3. Robust depletion shutdown guidance algorithm for long-range vehicles with a solid divert control system in large deviation conditions;Advances in Space Research;2023-11

4. Convex optimization for post-fault ascent trajectory replanning using auxiliary phases;Aerospace Science and Technology;2023-07

5. A Convex Approach for Trajectory Optimization of Super-Synchronous-Transfer-Orbit Large Launch Systems with Time-Position Constraints;International Journal of Aerospace Engineering;2022-08-10

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