Abstract
This study presents a comprehensive mission analysis and control framework for reusable launch vehicles (RLVs) employing retropropulsion-assisted vertical takeoff and landing (VTVL) configurations. The focus is on a two-stage RLV optimized for Low Earth Orbit (LEO) missions, with the first stage designed for reusability. Inspired by proven systems such as SpaceX's Falcon 9 and DLR's RETALT-2, the vehicle incorporates a nine-engine cluster and retropropulsion for booster recovery. The ascent phase is modeled using point mass and three-degrees-of-freedom (3-DOF) simulations, while the descent is evaluated through a six-degrees-of-freedom (6-DOF) dynamic model integrated with a neural network-based NARMA-L2 controller to optimize fuel consumption during landing. A conceptual second stage is proposed to complete orbital insertion and deliver payloads of up to 22,800 kg to LEO. Aerodynamic data generated using USAF DATCOM support trajectory modeling, with future enhancements planned using high-fidelity CFD analysis and grid fin control. This framework establishes a foundation for the design and optimization of RLV systems, supporting the development of cost-effective and reliable access to space for emerging national and international programs.
First Page
98
Last Page
111
Recommended Citation
Juhany, Khalid A
(2025)
"Mission Analysis and Control Optimization of Reusable Rockets with Retropropulsion for Low Earth Orbit Missions,"
Journal of King Abdulaziz University: Engineering Sciences: Vol. 1:
Iss.
1, Article 9.
DOI: https://doi.org/10.64064/1658-4260.1009
Creative Commons License
This work is licensed under a Creative Commons Attribution 4.0 International License.
Submit Article