Study of thermal throat of RBCC combustor based on one-dimensional analysis

Wang, Yajun; Li, Jiang; Qin, Fei; He, Guoqiang; Shi, Longxing

doi:10.1016/j.actaastro.2015.07.034

Cited by 24 publications

(2 citation statements)

References 21 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Pan and Lin 69,70 have realized the thrust enhancement in the ejector mode through the study of the primary rocket pressure and mixing ratio. Wang [71][72][73] have investigated the control of thermal throat of RBCC combustor. Tang 74 have studied the combustion organization in RBCC combustor of which the performance in scramjet mode have been optimized.…”

Section: Rbcc Power System Research In Chinamentioning

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:

View full text Add to dashboard Cite

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.

show abstract

Section: Rbcc Power System Research In Chinamentioning

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:

View full text Add to dashboard Cite

show abstract

“…for enhanced performance at high temperatures [6,7]. These works have built on the know-how accumulated on studying traditional C/C nozzles Other significant activities related to C/C nozzle design have considered various aspects of heat transfer [8][9][10]. The analysis of the reliability of C/C composite nozzle exit cone structures is however scarcely represented in open literature [11,12].…”

Section: Introductionmentioning

confidence: 99%