Ejector mode performance improvement of rocket-based combined cycle engine designed for dual-ramjet mode

Yan, De-kun; Liu, Xiao; He, Guoqiang; Martinuzzi, Robert J.

doi:10.1016/j.ast.2022.107637

Cited by 4 publications

(1 citation statement)

References 30 publications

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“…At present, the United States, Australia, European Union, France, Russia, Germany, Japan, China and other countries or regions have been vigorously developing RBCC technology, 12–32 and the United States is the most representative country in RBCC-powered vehicles concept design. A summary of the current hypersonic vehicle conceptual design powered by RBCC engine is shown in Table 1, 33 in which ABLV-06 (RBCC Rocketdyne), ABLV-07A (RBCC Aerojet), ABLV-07c (RBCC Aerojet) and ABLV-07c-LaunchAssist (RBCC Aerojet) have the same working principle that could be described as follows: RBCC engine starts working in ejector mode, performs ramjet-scramjet mode transition at Ma 2.5+ and then operates in rocket mode.…”

Section: Introductionmentioning

confidence: 99%

A survey on the conceptual design of hypersonic aircraft powered by RBCC engine

Xue

Xia

Feixing

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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Rocket-based combined-cycle (RBCC) powered vehicles have been widely recognized as the most promising aircraft solution that could dramatically reduce the cost of space transportation. Researchers and scientists worldwide have conducted considerable overall design researches to cope with the challenges in RBCC development including mode transition, thermal protection and thrust enhancement. According to the way to orbit and the configuration characteristics, the hypersonic aircraft powered by RBCC engine are classified as four categories: single-stage-to-orbit (SSTO) two-dimensional configuration, SSTO axisymmetric configuration, two-stage-to-orbit (TSTO) two-dimensional configuration, and TSTO axisymmetric configuration. This paper systematically presents the development of the conceptual design of RBCC-powered vehicles. Both the structural and operating key parameters like the weight distribution, the RBCC propulsion performance and take-off mode, et al. are introduced in detail. On this basis, a comparative analysis of the advantages and disadvantages of the orbit model, the configuration selection and takeoff modes are conducted. In addition, the application prospect and technology development direction for hypersonic aircraft are also discussed. At the same time, the lessons that can be drew from previous hypersonic vehicle concept design are explored.

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