A Fundamental Study on the Hybrid Rocket Clustering for the Rocket Sled Propulsion System

Nakata, Daisuke; Yasuda, Kazuki; Horio, S. P.; Higashino, Kazuyuki

doi:10.2514/6.2016-4868

Cited by 2 publications

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“…The main conclusion that can be drawn from this figure is that N2O can be self-pressurized as a liquid with densities ranging from 700 kg/m 3 to 900 kg/m 3 Many noteworthy hybrid rocket demonstrations in recent years have been achieved in part by taking advantage of the self-pressurizing ability of N2O. These include the aforementioned SpaceShipTwo, as well as its predecessor vehicle, SpaceShipOne [10], the highly successful Stuttgart University student-based hybrid sounding rocket, HEROS 3, reported by Kobald et al [11], the rocket test sled trials of Muroran Institute of Technology reported by Nakata et al [12], the small launch vehicles of TiSPACE Inc. reported by Chen and Wu [13], as well as the sounding rockets of Space Forest Ltd. reported by Gamal et al [14]. However, it is also important to point out that N2O can be pressurized above its vapor pressure to increase the flow rate capability of, and prevent two-phase flow within, the feed system.…”

Section: Introductionmentioning

confidence: 99%

Comprehensive Data Reduction for N2O/HDPE Hybrid Rocket Motor Performance Evaluation

et al. 2019

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Static firing tests of a hybrid rocket motor using liquid nitrous oxide (N2O) as the oxidizer and high-density polyethylene (HPDE) as the fuel are analyzed using a novel approach to data reduction that allows histories for fuel mass consumption, nozzle throat erosion, characteristic exhaust velocity (c*) efficiency, and nozzle throat wall temperature to be determined experimentally. This is done by firing a motor under the same conditions six times, varying only the burn time. Results show that fuel mass consumption was nearly perfectly repeatable, whereas the magnitude and timing of nozzle throat erosion was not. Correlations of the fuel regression rate result in oxidizer port mass flux exponents of 0.62 and 0.76. There is a transient time in the c* efficiency histories of around 2.5 s, after which c* efficiency remains relatively constant, even in the case of excessive nozzle throat erosion. Although nozzle erosion was not repeatable, the erosion onset factors were similar between tests, and greater than values in previous research in which oxygen was used as the oxidizer. Lastly, nozzle erosion rates exceed 0.15 mm/s for chamber pressures of 4 to 5 MPa.

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Section: Introductionmentioning

confidence: 99%

Comprehensive Data Reduction for N2O/HDPE Hybrid Rocket Motor Performance Evaluation

et al. 2019

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Numerical Simulation of Unsteady Fluid Parameters for Maglev Flight Wind Tunnel Design

Gao

Sun

et al. 2022

Aerospace

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The maglev flight tunnel is a novel conceptual aerodynamics test facility, in which the complicated aerodynamic characteristics caused by the high-speed translation of a moving model in a long, straight, closed tunnel, and wave propagation and aero-structure single-way coupling problems can be investigated. The unsteady characteristics originating from a high-speed model in the maglev flight tunnel were investigated and evaluated with regard to aero–structure coupling. The new conservation element and solution element method was used to solve the 3-D compressible fluid surrounding a moving model in a tunnel, and the variations in the aerodynamic parameters, wave propagation characteristics, and pressure distribution in the tunnel were obtained. The results provide support for key technical problems, such as a wave-absorbing construction design of the maglev flight wind tunnel.

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A Fundamental Study on the Hybrid Rocket Clustering for the Rocket Sled Propulsion System

Cited by 2 publications

References 1 publication

Comprehensive Data Reduction for N2O/HDPE Hybrid Rocket Motor Performance Evaluation

Comprehensive Data Reduction for N2O/HDPE Hybrid Rocket Motor Performance Evaluation

Numerical Simulation of Unsteady Fluid Parameters for Maglev Flight Wind Tunnel Design

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