Development of a 1D dual mode scramjet model for a hypersonic civil aircraft

Ispir, Ali Can; Saracoglu, Bayindir H.

doi:10.2514/6.2019-3842

Cited by 3 publications

(3 citation statements)

References 10 publications

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“…During the next phase, the vehicle performs a second climb, until reaching Mach 4 (supersonic climb). At the end of this phase, the ATR engines are turned off and the Dual Mode Ramjet (DMR) [24] is activated to accelerate up to Mach 8, reaching an altitude of 32-33 km (hypersonic climb). Here, the cruise starts at Mach 8, with a total thrust of 664 kN available for the DMR.…”

Section: Stratofly Mr3 Vehicle and Mission Conceptsmentioning

confidence: 99%

Integrated Flight Control System Characterization Approach for Civil High-Speed Vehicles in Conceptual Design

et al. 2023

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Recent studies have revealed that control surface deflection can cause a reduction in the aerodynamic efficiency of a hypersonic aircraft of up to 30%. In fact, the characterization of the Flight Control System is essential for the estimation of the consistent aerodynamic characteristics of the vehicle in different phases, considering the contribution of control surfaces to stability and trim. In terms of the sizing process, traditional methodologies have been demonstrated to be no longer applicable to estimations of the actuation power required for the control surfaces of a high-speed aircraft, due to their peculiar working conditions and to the characteristics of the flow to which they are exposed. In turn, numerical simulation approaches based on computational fluid dynamics or panel methods may require considerable time resources, which do not fit with the needs of the quick and reliable estimates that are typical of the early design phases. Therefore, this paper is aimed at describing a methodology to show how to anticipate the Flight Control System design for high-speed vehicles at the conceptual design stage, properly considering the interactions at vehicle level and predicting the behavior of the system throughout an entire mission. It is also a core part of the work to provide designers with an example of how neglecting the effect of trim drag can be detrimental to a reliable estimation of overall aircraft performance. The analysis, mainly focused on the longitudinal plane of the vehicle, is presented step-by-step on a specific case study, namely the STRATOFLY MR3 vehicle, a Mach 8 waverider concept for civil antipodal flights. The application of the methodology, conceived as an initial step towards an iterative Flight Control System design process, also shows that the most power-demanding phases are take-off, low supersonic acceleration, and approach, where peaks of over 130 kW are reached, while an average of 20 kW is sufficient to support deflections in a hypersonic cruise.

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Section: Stratofly Mr3 Vehicle and Mission Conceptsmentioning

confidence: 99%

Integrated Flight Control System Characterization Approach for Civil High-Speed Vehicles in Conceptual Design

et al. 2023

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“…In order to assess combined cycle propulsion plant performance along the hypersonic regime of the trajectory, a 1D propulsion tool was developed [16] and inviscid steady flow transport equations and combustion chemistry were embedded to the tool [9]. Three main governing equations (mass, momentum and energy) are implemented by imposing perfect gas assumption.…”

Section: Hypersonic Cruisementioning

confidence: 99%

Analysis of a combined cycle propulsion system for STRATOFLY hypersonic vehicle over an extended trajectory

2019

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Hypersonic civil aviation is an important enabler for extremely shorter flight durations for long-haul routes and using unexploited flight altitudes. Combined cycle engine concepts providing extended flight capabilities, i.e. propelling the aircraft from take-off to hypersonic speeds, are proposed to achieve high-speed civil air transportation. STRATOFLY project is a continuation of former European efforts in hypersonic research and aims at developing a commercial reusablevehicle for cruise speed of Mach 8 at stratospheric altitudes as high as 35 km above ground level. The propulsion plant of STRATOFLY aircraft consists of combination of two different type of engines: an array of air turbo rockets and a dualmode ramjet/scramjet. In the present study, 1D transient thermodynamic simulations for this combined cycle propulsion plant have been conducted between Mach 0 to 8 by utilizing 1D inviscid flow transport relations, numerical tools availablein EcosimPro software platform and the European Space Propulsion System Simulation libraries. The optimized engine parameters are achieved by coupling EcosimPro software with Computer Aided Design Optimization which is a differential evolution algorithm developed at the von Karman Institute.

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“…The fuel is injected into the air stream in parallel direction from struts located at the entrance to the combustor. Auto-ignition and combustion of the mixture are expected to take place in a time scale of the order of milliseconds in the burner part of the propulsion system [6,7]. The operation loop is closed by accelerating the burnt gases along a diverged nozzle to gain momentum for thrust production.…”

Section: Introductionmentioning

confidence: 99%

Reduced-order modeling of supersonic fuel–air mixing in a multi-strut injection scramjet engine using machine learning techniques

et al. 2023

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Development of a 1D dual mode scramjet model for a hypersonic civil aircraft

Cited by 3 publications

References 10 publications

Integrated Flight Control System Characterization Approach for Civil High-Speed Vehicles in Conceptual Design

Integrated Flight Control System Characterization Approach for Civil High-Speed Vehicles in Conceptual Design

Analysis of a combined cycle propulsion system for STRATOFLY hypersonic vehicle over an extended trajectory

Reduced-order modeling of supersonic fuel–air mixing in a multi-strut injection scramjet engine using machine learning techniques

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