Space Launch Vehicle Design with Simultaneous Optimization of Thrust Profile and Trajectory-Reference-Cited by-同舟云学术

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Space Launch Vehicle Design with Simultaneous Optimization of Thrust Profile and Trajectory

Published:2017-09-12 Issue: Volume: Page:
ISSN:
Container-title:AIAA SPACE and Astronautics Forum and Exposition
language:
Short-container-title:

Author:

Civek Ezgi¹,Özgören M. Kemal²

Affiliation:

1. Roketsan Inc.

2. Middle East Technical University

Publisher

American Institute of Aeronautics and Astronautics

Link

https://arc.aiaa.org/doi/pdf/10.2514/6.2017-5333

Reference29 articles.

1. Vega (m/s) Ideal (m/s) Difference (%) 1ststage 2779.5 3217.6 13.62 2ndstage 2401.5 2746.7 12.57 3rdstage 3684.4 2901.1 -27.00

2. Optimal (m/s) Ideal (m/s) Difference (%) 1ststage 2904.0 3165.8 8.27 2ndstage 2841.9 2698.1 -5.33 3rdstage 2973.5 2855.5 -4.13

3. Vega (kg) Ideal (kg) Difference (%) 1ststage 96243 102645 6.24 2ndstage 26300 23136.4 -13.67

4. Survey of Numerical Methods for Trajectory Optimization

Cited by 2 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. Coupled Vehicle and Trajectory Design Optimization for Boost-Glide Hypersonic Systems;AIAA SCITECH 2024 Forum;2024-01-04

2. Integrated Optimization of First-Stage SRM and Ascent Trajectory of Multistage Launch Vehicles;Journal of Spacecraft and Rockets;2021-05

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