A Survey on Recovery Technology for Reusable Space Launch Vehicle

Choo, Kyoseung; Mun, Hokyun; Nam, Seunghoon; Cha, Jihyoung; Ko, Sangho

doi:10.6108/kspe.2018.22.2.138

Cited by 7 publications

(3 citation statements)

References 17 publications

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“…Although a pintle injector was developed in advance, a fixed injector was mainly used because most LPREs were disposable almost for delivering satellites to space, so only a maximum thrust was required, not an extensive throttle range. However, as the reusable launch vehicle (RLV) is one of the critical technologies in the new space age (sometimes space 2.0), a variable area injector has recently become essential as a next-generation injector because deep throttling is needed in a new LPRE for RLVs [4][5][6][7]. A pintle injector is an excellent option for a variable area injector required in a deep-throttling LPRE due to its relatively simple design, potential for high performance, and a high range of throttle.…”

Section: Introductionmentioning

confidence: 99%

A Numerical Approach to Optimize the Design of a Pintle Injector for LOX/GCH4 Liquid-Propellant Rocket Engine

2023

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This study presents an optimal design approach of a pintle injector for a deep throttlable liquid-propellant rocket engine (LPRE). Even though the pintle injector is used in rocket engines, it has become more important since reusable launch vehicles (RLVs) recently became a trend due to their economic and environmental benefits. However, since many variables must be determined to design a pintle injector, optimizing the pintle injector design is complicated. For this, we design a pintle injector to optimize the performance parameters; the spray angle, vaporization distance, and Sauter mean diameter (SMD). To confirm the approach, we design a pintle injector using an optimization method based on convex quadratic programming (CQP) for a 1000 N thrust and a throttle ability of 5 to 1 LPRE with liquid oxygen and gaseous methane. Then, we verify the performance using a numerical simulation. Through this work, we check the effectiveness of the optimization method for a pintle injector design.

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Section: Introductionmentioning

confidence: 99%

A Numerical Approach to Optimize the Design of a Pintle Injector for LOX/GCH4 Liquid-Propellant Rocket Engine

2023

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“…As a result, new technology encourages change in how the space industry operates, and the market for commercial launch services has expanded to put satellites into orbit. Therefore, one of the primary concerns is the low-cost commercialization and management of space launch vehicles (SLVs) to strengthen the competitiveness of the new space age [4][5][6][7][8][9][10]. However, the development cost for a new propulsion system is expensive, and there is a risk of accidents in development and tests.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

Cha

2023

Aerospace

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This study deals with the mathematical modeling and numerical simulation of chemical propulsion systems (CPSs). For this, we investigate and summarize a comprehensive collection of the simulation modeling developments of CPSs in academic works, applications, and industrial fields. Then, we organize and analyze the simulation modeling approaches in several ways. After that, we organize differential-algebraic Equations (DAEs) for fundamental mathematical modeling consisting of the governing Equations (ordinary differential equations, ODEs) for the components and other equations derived from several physical rules or characteristics (algebraic equations or phenomenological equations, AEs) and then synthesize and summarize the fundamental structures of analytic mathematical modeling by types (liquid-propellant rocket engines, solid-propellant rocket motors, and hybrid-propellant rocket motors) of CPSs.

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“…As reaching a certain altitude is crucial to a sounding rocket's operations, which provides test environments with micro gravity, low air density, and sufficient descending velocity with an adequate flight time, the final altitude is one of the most critical parameters of such a rocket's performance and is among the principal design objectives. Not only from this perspective, but also concerning operational efficiency, in light of a new aspect of cost-sensitive space technology emerging recently represented by such as low-cost and reusable launch vehicles [6][7][8][9][10][11][12], there is a greater need today for the maximisation of final altitudes and the minimisation of propellant masses of vertically launched flight vehicles.…”

Section: Introductionmentioning

confidence: 99%

A practical design approach for a single-stage sounding rocket to reach a target altitude

Huh

Kwon

2022

Aeronaut. j.

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A new type of design domain for a sounding rocket is suggested in this study, which is more intuitive, simplified, and conducive to a single-stage sounding rocket development process. Among the various operation parameters, this study identifies several effective variables, which are also among the most practical in a sounding rocket design process. Of the many design variables considered for peak altitude optimisation, arguably the three most effective in shaping the whole system and conferring the most practicality in the design process of a sounding rocket were determined. A simulation-based study was conducted to establish: the effect of the selected parameters on flight performance, and the optimum design conditions of a single-stage sounding rocket in terms of its peak altitude. The simulation result was compared with randomly chosen experimentally tested flight data and validated. With the clear performance curves varying depending on the variables, the combination of the considered design inputs was effective. The new type of design domain and design procedure proposed is expected to constitute a useful reference and deliver practical benefits to the development process for a target-altitude-optimised single-stage sounding rocket.

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A Survey on Recovery Technology for Reusable Space Launch Vehicle

Cited by 7 publications

References 17 publications

A Numerical Approach to Optimize the Design of a Pintle Injector for LOX/GCH4 Liquid-Propellant Rocket Engine

A Numerical Approach to Optimize the Design of a Pintle Injector for LOX/GCH4 Liquid-Propellant Rocket Engine

Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

A practical design approach for a single-stage sounding rocket to reach a target altitude

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