New Formulation for Time Derivatives of Instantaneous Impact Point Based on Geometric Decomposition

Jo, Byeong-Un; Ahn, Ji-Whan

doi:10.1061/(asce)as.1943-5525.0000865

Cited by 5 publications

(1 citation statement)

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“…The orbital elements needed for setting boundary conditions on orbit insertion in the optimization module are calculated by transforming the inertial position/velocity into six parameters [29]. The flight-safety related variables (e.g., IIP) are computed based on the procedures presented in reference [25,30,31]. Table 1 outlines the selected output variables (notations, descriptions, and units) computed in the second module.…”

Section: Output Generation Modulementioning

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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