Experimental Investigation of an Alternative Rocket Configuration for Rocket-Based Combined Cycle Engines

Etele, Jason; Hasegawa, Susumu; Ueda, Shuichi

doi:10.2514/1.b35080

Cited by 28 publications

(6 citation statements)

References 27 publications

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“…The takeoff-mass m 0 of the two-stage-to-orbit spacecraft includes the first stage of launch vehicle mass m 01 , and the second-stage RKT rocket mass m 02 includes the payload. m 01 includes the fuel mass, m 01p , and the fuselage structure mass, m 01s (5) , namely,…”

Section: Calculation Of Thrustmentioning

confidence: 99%

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Integral performance optimization for the two-stage-to-orbit RBCC-RKT launch vehicle based on GPM

Zhang¹,

Sun²,

Cheng³

et al. 2019

Aeronaut. j.

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The takeoff-mass of a two-stage-to-orbit Rocket-Based Combined Cycle Engine-Rocket (RBCC-RKT) launch vehicle is a crucial factor in its comprehensive performance. This paper optimizes the takeoff-mass together with the trajectory by reformulating it to a nonlinear optimal control problem. The range of the second stage rocket mass is considered as a process constraint. When the scopes of initial and terminal states are specified, the problem can be solved by using the Gauss pseudo-spectral method (GPM). In order to reduce the convergent difficulty caused by using table data, the data in different stages are utilized by employing an integrated interpolation strategy through the optimization. Simulation results show that the mass can be effectively optimized to meet the inertia mass ratio constraint of the first-stage, and the separation of Mach number and altitude can be optimized at the same time.

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Section: Calculation Of Thrustmentioning

confidence: 99%

“…RBCC is typified by Marquardt's Mach 8 Supercharged Ejector Ramjet (SERJ) as shown in Fig. 1 (4) and works mainly in three modes: ejector mode, ramjet mode and scramjet mode (5)(6)(7)(8)(9) . The ejector mode ends, and the ramjet mode starts when the Mach number reaches 2.5.…”

Section: Introductionmentioning

confidence: 99%

Integral performance optimization for the two-stage-to-orbit RBCC-RKT launch vehicle based on GPM

Zhang¹,

Sun²,

Cheng³

et al. 2019

Aeronaut. j.

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“…A rocket-based combined-cycle (RBCC) engine exploits the synergistic interactions between a rocket and an airbreathing engine, effectively integrating a high thrust-toweight ratio with a high specific impulse that can function over an extensive Mach number range, providing better performance than any single existing engine class [1][2][3][4][5]. This lightweight, safe, and fully reusable propulsion system is expected to be the most efficient propulsion system for reusable launch vehicles and hypersonic cruise vehicles [6,7].…”

Section: Introductionmentioning

confidence: 98%

Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime

Shi¹,

Liu²,

He³

et al. 2016

International Journal of Turbo &Amp; Jet-Engines

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Numerical integration simulations were performed on a ready-made central strut-based rocket-based combined-cycle (RBCC) engine operating in the ejector mode during the takeoff regime. The effective principles of various cowl lip positions and shapes on the inlet operation and the overall performance of the entire engine were investigated in detail. Under the static condition, reverse cowl lip rotation in a certain range was found to contribute comprehensive improvement to the RBCC inlet and the entire engine. However, the reverse rotation of the cowl lip contributed very little enhancement of the RBCC inlet under the low subsonic flight regime and induced extremely negative impacts in the high subsonic flight regime, especially in terms of a significant increase in the drag of the inlet. Changes to the cowl lip shape provided little improvement to the overall performance of the RBCC engine, merely shifting the location of the leeward area inside the RBCC inlet, as well as the flow separation and eddy, but not relieving or eliminating those phenomena. The results of this study indicate that proper cowl lip rotation offers an efficient variable geometry scheme for a RBCC inlet in the takeoff regime.

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“…In the development of hypersonic flight systems, several types of air-breathing engines for different application layers, such as scramjets [1,2], dual-mode scramjets [3,4], and combined-cycle engines [5,6], have long been studied.…”

Section: Introductionmentioning

confidence: 99%

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

Wang

Qin

et al. 2015

Acta Astronautica

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Experimental Investigation of an Alternative Rocket Configuration for Rocket-Based Combined Cycle Engines

Cited by 28 publications

References 27 publications

Integral performance optimization for the two-stage-to-orbit RBCC-RKT launch vehicle based on GPM

Integral performance optimization for the two-stage-to-orbit RBCC-RKT launch vehicle based on GPM

Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime

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

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