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

Ispir, Ali Can; Goncalves, Pedro M.; Saracoglu, Bayindir H.

doi:10.1051/matecconf/201930403001

Cited by 3 publications

(3 citation statements)

References 12 publications

(11 reference statements)

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“…A first mission analysis was carried out to identify a draft trajectory and profile (Figure 2), connecting Brussels to Sydney, as described here. During the first part of the mission, six Air Turbo Rocket (ATR) engines are used [22], with an available thrust at sea level of about 233 kN per engine. The vehicle flies at subsonic speeds during the subsonic climb.…”

Section: Stratofly Mr3 Vehicle and Mission Conceptsmentioning

confidence: 99%

“…A total time of 55 min is needed to reach the beginning of cruise conditions, while the cruise phase lasts 1 h 29 min. The highest propellant consumption rate is experienced at the beginning of the mission, while the vehicle performs the climb phases [22]. During cruise the propellant mass consumption is instead reduced.…”

Section: Step 3: Aerodynamic Characterization Of Control Surfaces And...mentioning

confidence: 99%

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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 In terms of the sizing process, traditional methodologies have been demonstrated to be no longer applicable to estimations of the actuation power required for the control surfaces of a high-speed aircraft, due to their peculiar working conditions and to the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%

Section: Step 3: Aerodynamic Characterization Of Control Surfaces And...mentioning

confidence: 99%

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

et al. 2023

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“…Существует схемы ВРД, сочетающие в едином агрегате турбореактивный и прямоточный двигатель турбопрямоточные двигатели (ТПД) [1][2][3][4]. Одна из таких схем показана на рисунке 1, где представлен ТПД по схеме турбореактивного двухконтурного двигателя с форсажной камерой в наружном контуре.…”

Section: введение и постановка проблемыunclassified

Особенности Расчета И Регулирования Двухконтурного Турбореактивного Двигателя С Форсажной Камерой Сгорания В Наружном Контуре На Прямоточных Режимах Работы

Кислов¹,

Shevchenko²

2020

aktt

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A promising direction in aviation is the creation of anaircraft for supersonic cruise speeds (Mach 3...4). It is known that ramjet engines are more preferable for Mach numbers larger 3. However, they do not have starting thrust and uneconomical at subsonic flight speeds. At the same time, at subsonic flight speeds, turbofan engines are the most expedient. The combination of the positive properties of turbofan engines at subsonic speeds and a ramjet engines at supersonic speeds is possible by using duct-burning turbofan engine, which can operate at the ramjet mode with the blocked gas turbine duct at supersonic flight conditions. At this mode, duct-burning turbofan engine turns into ramjet engine, which, however, has special features due to the presence of fan in front of the combustion chamber, which operates in turbine mode or in zero power mode and also because of the outlet jet, which has annular shape, flows out from the duct causes the appearance of bottom drag. The presence of bottom drag requires both the development of a mathematical model for its calculation and taking into account its influence on the choice of the control law for the nozzle outlet area. The article presents a mathematical model of the working process of duct-burning turbofan engine at ramjet mode, taking into account the presence of fan in the flow path and bottom drug. Using the developed mathematical model, the regularities of changes in the internal and effective thrust, as well as the specific fuel consumption, depending on the relative fuel consumption and the critical section of the nozzle at a given altitude and flight speed are established. The critical section of the nozzle is the main regulating factor, and the relative fuel consumption is related to the main regulating factor - the fuel consumption. These patterns are useful for choosing a control program.There is such a combination of regulating factors whichprovides two extremes in the regularities of trust and specific fuel consumption changes: the mode of minimum specific fuel consumption and the mode of maximum thrust. In addition, the influence of gas underexpansion in the nozzle on the thrust-economic parameters of the engine and the required area of the nozzle outlet section were estimated. The obtained regularities are advisable to use when engine control program is chosen.

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STRATOFLY MR3 – how to reduce the environmental impact of high-speed transportation

Viola

Fusaro

Gori

et al. 2021

AIAA Scitech 2021 Forum

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

Cited by 3 publications

References 12 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

Особенности Расчета И Регулирования Двухконтурного Турбореактивного Двигателя С Форсажной Камерой Сгорания В Наружном Контуре На Прямоточных Режимах Работы

STRATOFLY MR3 – how to reduce the environmental impact of high-speed transportation

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