Vent Valve for Test Launch Vehicle of Korea Space Launch Vehicle II

Oh, Taek Hyun; Ko, Ju Yong; Kim, Young-Hoon; Lee, Woo Jung; Ok, Honam

doi:10.2514/1.a33950

Cited by 4 publications

(1 citation statement)

References 17 publications

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“…The characteristics of the structural and propulsion systems for Korean Space Launch Vehicle II (KSLV-II, Nuri) are used for this case study (e.g., structural mass fraction, specific impulse, and thrust). Table 2 summarizes the specifications of the KSLV-II vehicle used for this case study [32]. Note that the nozzle exit area was estimated based on the expressed differences between the vacuum and sea level thrust of the engine, and the reference area was utilized by the reported diameter of KSLV-II [33].…”

Section: Case Studymentioning

confidence: 99%

Simultaneous Optimization of Launch Vehicle Stage and Trajectory Considering Flight-Requirement Constraints

Ko,

Kim,

Choi

et al. 2024

Int. J. Aeronaut. Space Sci.

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A conceptual design of a launch vehicle encompasses various disciplines, such as structural design, aerodynamics, propulsion systems, flight control, and stage sizing. This paper focuses on optimizing trajectory and stage size. Traditional approaches used for the conceptual design of a launch vehicle conduct the stage and trajectory designs sequentially, often leading to high computational complexity and suboptimal results. This paper presents an optimization framework that addresses both trajectory optimization and staging in an integrated way. The proposed framework aims to minimize the lift-off mass while satisfying the constraints on flight requirements (e.g., maximum dynamic pressure and the impact points of separated parts). A case study demonstrates the advantage of the proposed framework compared to the traditional sequential optimization approach.

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Section: Case Studymentioning

confidence: 99%