Citation

Sungheetha, Akey and R., Rajesh Sharma and A, Karthikeyan and Shakthi, Vishnu and S, Kanmani and A, Divyashree (2026) Advanced Hydrogen-Oxygen Combustion Systems for Enhanced Upper Stage Rocket Performance in First Manned Lunar Missions: Propellant Efficiency and Mission-Critical Optimization. Procedia Computer Science, 282. pp. 761-772. ISSN 18770509

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Abstract

Contemporary space propulsion systems face critical challenges in achieving optimal performance for manned lunar missions, particularly regarding hydrogen-oxygen combustion efficiency in upper stage rockets. Current propulsion technologies demonstrate suboptimal specific impulse values averaging 442-456 seconds with mixture ratio variations causing thrust fluctuations of approximately 8-12 percent during critical mission phases. This research develops an Advanced Adaptive Hydrogen-Oxygen Combustion Optimization Framework integrating real-time combustion monitoring, intelligent mixture ratio control, and predictive thermal management algorithms to enhance propulsion performance. The proposed methodology incorporates three novel algorithms: Dynamic Propellant Flow Regulation Algorithm achieving mixture ratio precision within 0.3 percent deviation, Adaptive Combustion Chamber Thermal Stabilization Algorithm maintaining chamber temperatures at 3420-3480 Kelvin with variance under 1.5 percent, and Mission-Critical Thrust Vector Optimization Algorithm enabling thrust adjustments with response times below 45 milliseconds. Experimental validation using synthetic combustion datasets derived from historical Apollo and contemporary Space Launch System parameters demonstrates specific impulse improvements reaching 468-472 seconds representing enhancement of 3.2-3.8 percent, combustion efficiency gains of 96.4-97.8 percent exceeding baseline values by 4.5-5.2 percentage points, and thrust-to-weight ratio optimization achieving 1.48-1.52 with payload capacity increases of 340-380 kilograms for translunar injection trajectories. Results indicate propellant consumption reduction of 7.8-9.2 percent for equivalent mission profiles, translating to cost savings approximating 2.8-3.4 million dollars per launch cycle while extending operational safety margins by 18-22 percent during ascent and orbital insertion phases. The framework demonstrates commercial viability through integration with existing launch infrastructure, presenting technology transfer opportunities for aerospace manufacturing entities and enabling startup ventures focused on next-generation propulsion system development.

Item Type:	Article
Uncontrolled Keywords:	Mission-critical systems, Adaptive thermal management, Propellant efficiency
Subjects:	Q Science > QA Mathematics > QA71-90 Instruments and machines
Divisions:	Faculty of Information Science and Technology (FIST)
Depositing User:	Ms Rosnani Abd Wahab
Date Deposited:	02 Sep 2026 07:38
Last Modified:	02 Sep 2026 07:38
URII:	http://shdl.mmu.edu.my/id/eprint/16541

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