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<p>This research is dedicated to the analysis of the launch capabilities of a two-stage small launch vehicle (SLV), utilizing the second and third stages of the Korean Space Launch Vehicle-II (KSLV-II), while investigating the effects of various design parameters. The parameters under consideration encompass the structural coefficient, the performance characteristics of the first-stage and second-stage engines and the stage-to-stage mass ratio. The performance assessment of the launch vehicle is executed through algebraic modeling, with validation achieved by comprehensive comparisons with detailed trajectory calculations. The research findings reveal that, through staging calculations, enhancements in the structural coefficient and stage-to-stage mass ratio can facilitate the launch of payloads weighing approximately 580&#xa0;kg into a 500&#xa0;km orbit. Furthermore, improvements in the thrust of the first-stage engine are projected to accommodate payloads of around 830&#xa0;kg into the desired orbit. Additionally, the enhancements in the specific impulse of the second-stage engine have the potential to increase the maximum payload capacity to 1463&#xa0;kg, thereby rendering it competitive with the capabilities of the three-stage KSLV-II.</p>

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Performance Analysis of Small Launch Vehicles Using Algebraic Model: Case Studies Based on KSLV-II 2nd and 3rd Stage

  • 期刊论文

  • 发表日期：

    2025年4月7日

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  • Min-Seon Jo,
  • Donghyun Cho,
  • Jeong-Yeol Choi

摘要

This research is dedicated to the analysis of the launch capabilities of a two-stage small launch vehicle (SLV), utilizing the second and third stages of the Korean Space Launch Vehicle-II (KSLV-II), while investigating the effects of various design parameters. The parameters under consideration encompass the structural coefficient, the performance characteristics of the first-stage and second-stage engines and the stage-to-stage mass ratio. The performance assessment of the launch vehicle is executed through algebraic modeling, with validation achieved by comprehensive comparisons with detailed trajectory calculations. The research findings reveal that, through staging calculations, enhancements in the structural coefficient and stage-to-stage mass ratio can facilitate the launch of payloads weighing approximately 580 kg into a 500 km orbit. Furthermore, improvements in the thrust of the first-stage engine are projected to accommodate payloads of around 830 kg into the desired orbit. Additionally, the enhancements in the specific impulse of the second-stage engine have the potential to increase the maximum payload capacity to 1463 kg, thereby rendering it competitive with the capabilities of the three-stage KSLV-II.