RBCC ejector mode operating characteristics for single and twin thruster configurations

Cramer, John M.; Greene, M.; Pal, Snehanshu; Santoro, Robert J.

doi:10.2514/6.2001-3464

Cited by 9 publications

(3 citation statements)

References 7 publications

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“…In hybrid and pure ejector modes, the fuel-rich burned hot gas is supplied with distributed ejector, which can improve the mixing efficiency and reduce mixing length. [31][32][33] 3. Ramjet mode.…”

Section: Pure Ejector Modementioning

confidence: 99%

Conceptual study of a dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle

Zhang

Wang

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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The liquid oxygen/methane staged cycle liquid-rocket engine is one of the most potential rocket engines in the future for its higher performance, higher fuel density and reusable capacity. Two working states of this liquid-rocket engine named as full-load state and half-load state are defined in this paper. Based on this liquid-rocket engine, a dual-rocket-basedcombined-cycle propulsion system with liquid oxygen /air/methane as propellants is therefore proposed. The dualrocket-based-combined-cycle system has then five working modes: the hybrid mode, pure ejector mode, ramjet mode, scramjet mode and pure rocket mode. In hybrid mode, the booster and ejector rockets driven by the full-load liquidrocket engine work together with the purpose of reducing thrust demand on ejector rocket. In scramjet mode, the fuelrich burned hot gas generated by the half-load liquid-rocket engine is used as fuel, which is helpful to reduce the technical difficulty of scramjet in hypersonic speed. The five working modes of dual-rocket-based-combined-cycle are highly integrated based on the full-or half-load state of the liquid oxygen/methane staged cycle liquid-rocket engine, and the unified single type fuel of liquid methane is adopted for the whole modes. Then a preliminary design of a horizontal takeoff two-stage-to-orbit launch vehicle is conducted based on the dual-rocket-based-combined-cycle propulsion system. Under an averaged baseline thrust and specific impulse, the launch trajectory to reach a low Earth orbit at 100 km is optimized via the pseudo-spectral method subject to maximizing the payload mass. It is shown that the two-stage-to-orbit vehicle based on the dual-rocket-based-combined-cycle can achieve the payload mass fraction of 0.0469 and 0.0576 for polar mission and equatorial mission, respectively. Conclusively, insights gained in this paper can be usefully applied to a more detailed design of the dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle.

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Section: Pure Ejector Modementioning

confidence: 99%

Conceptual study of a dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle

Zhang

Wang

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Nagiev et al [ 10 ] and Quinn et al [ 11 ] conducted the ignition test of 90% high-concentration H 2 O 2 and hydrocarbon mixed fuel and concluded that the ignition delay reached 16 ms. Since then, a propellant named D- α code for the external 3.8 kN thrust has been developed, and its ignition delay time was shortened to 7.9 ms. H 2 O 2 was preferentially adopted by NASA as the fuel in the rocket-based combined cycle-propulsion system (RBCC) because of its high combustion propulsion efficiency and high ignition characteristic speed [ 12 , 13 ]. A three-strand injection device was adopted inside the engine to strictly control the composition and fuel ratio.…”

Section: Introductionmentioning

confidence: 99%

Atomization Characteristics of Hydrogen Peroxide Solutions in Electrostatic Field

Sheng

2022

Micromachines

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Hydrogen peroxide (H2O2) can be considered as a sterilant or a green propellant. For a common use in industrial application, spray is an effective method to form fine H2O2 droplets. In this paper, electrostatic atomization based on the configuration of needle ring electrodes is proposed to produce H2O2 spray by minimizing its effective surface tension. The breakup performances of H2O2 ligaments can be improved by increasing the electric field intensity, reducing the nozzle size, and adjusting suitable volume flow rate. The smallest average diameter of breakup droplets for 35 wt. % concentration H2O2 solution reached 92.8 μm under optimum operation conditions. The H2O2 concentration significantly influenced the breakup performance owing to the concentration effect on comprehensive physical properties such as density, surface tension, viscosity, and permittivity. The average diameters of breakup droplets decreased with decreasing H2O2 concentration. At 8 wt. % concentration, the average breakup droplet diameter was reduced to 67.4 μm. Finally, electrostatic atomization mechanism of H2O2 solution was analyzed by calculating dimensionless parameters of Re, We, and Oh numbers with the combination of the operation conditions and physical properties for in-depth understanding the breakup behaviors. The calculation showed that the minimum average diameter of breakup droplets was obtained at 8 wt. % concentration at the investigated range of H2O2 concentration, which kept in agreement with the experimental results.

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“…Their measurements showed that in the SMC mode, mixing was finished earlier in the fuel rich case as compared to stoichiometric [46] and that the DAB mode tended to mix faster [47]. The same test apparatus was later used by Cramer et at [14] to examine the effect of rocket thruster configuration in SMC mode.…”

Section: Chapter 1 Introductionmentioning

confidence: 99%

Theoretical investigation of variable area ejectors

Koupriyanov¹

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NOTICE: The author has granted a nonexclusive license allowing Library and Archives Canada to reproduce, publish, archive, preserve, conserve, communicate to the public by telecommunication or on the Internet, loan, distribute and sell theses worldwide, for commercial or noncommercial purposes, in microform, paper, electronic and/or any other formats. AVIS: L'auteur a accorde une licence non exclusive permettant a la Bibliotheque et Archives Canada de reproduire, publier, archiver, sauvegarder, conserver, transmettre au public par telecommunication ou par Plntemet, prefer, distribuer et vendre des theses partout dans le monde, a des fins commerciales ou autres, sur support microforme, papier, electronique et/ou autres formats. Canada Bien que ces formulaires aient inclus dans la pagination, il n'y aura aucun contenu manquant.

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RBCC ejector mode operating characteristics for single and twin thruster configurations

Cited by 9 publications

References 7 publications

Conceptual study of a dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle

Conceptual study of a dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle

Atomization Characteristics of Hydrogen Peroxide Solutions in Electrostatic Field

Theoretical investigation of variable area ejectors

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