LEA Flight Test Program: Status in 2006

Falempin, François; Serre, Laurent

doi:10.2514/6.2006-7925

Cited by 6 publications

(6 citation statements)

References 30 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The Series application (real time acquisition) of OMNIC software is used to obtain the evolution of the molar rate of these gases during an experiment with the COMPARER bench. It must be noted that the optical cell (with a volume of 100 cm 3 ) is connected to the reactor outlet thanks to a sampling line of 2 m long. Thus, a time delay exists between the process outlet and the measurement.…”

Section: The Comparer Test Benchmentioning

confidence: 99%

“…Furthermore, the time allocated for the combustion in SCRamjet mode is about 1 ms [2]. The thermal management of the overall vehicle and more specifically of the combustion chamber (CC) is thus an important focus for the aerospace research [3]. In this framework, the COMPARER program (COntrol and Measure of PArameters in a REacting stReam) has been settled by MBDA-France and by the University of Orléans (France).…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Synthetic and jet fuels pyrolysis for cooling and combustion applications

Gascoin

Abraham

Gillard

2010

Journal of Analytical and Applied Pyrolysis

View full text Add to dashboard Cite

Large heat load are encountered in hypersonic flight applications due to the high vehicle speed (over Mach 5, i.e. 5000 km.h-1) and to the combustion heat release. If passive and ablative protections are a way to ensure the thermal management, the regenerative cooling is probably the most efficient one to enable the structures withstanding (notably for reusable structures). The present study is a part of COMPARER project (COntrol and Measure of PArameters in a REacting stReam) which aims at investigating the highly coupled phenomenon (heat and mass transfers, pyrolysis, combustion) in a cooling channel surrounding a SCRamjet combustion chamber and at proposing some parameters to enable the control of such a complex technology. In this paper, we present the comparative numerical pyrolysis study of some selected synthetic and jet fuels (heptane, decane, dodecane, kerosene surrogate). The fluid pyrolysis has been studied experimentally and the results of RESPIRE numerical simulation under lab and in-flight conditions are given with validation to provide a deep understanding of phenomenon. The impact of the density, of the critical parameters, of the viscosity and of the chemistry is investigated to analyze their effect on the cooling efficiency of the engine. That also enables to estimate which properties the best cooling fuel should have. Furthermore, a combustion study is conducted because the cooling fuel is the one that ensure the thrust. The RESPIRE code enables to conduct both coupled pyrolysis and combustion studies. A first approach of the dynamic regeneratively cooled SCRamjet is provided to get a large vision of the fuel nature impact on the system.

show abstract

Section: The Comparer Test Benchmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Synthetic and jet fuels pyrolysis for cooling and combustion applications

Gascoin

Abraham

Gillard

2010

Journal of Analytical and Applied Pyrolysis

View full text Add to dashboard Cite

show abstract

“…At least, taking into account corresponding background and associated working partnership, it should be possible to define the most efficient flight test program (in term of scientific and technological return to financial investment). But, considering the limited budget which could be potentially available in Europe within the next years for such a flight test program, a preliminary and less ambitious flight test program, called EAST for European Advanced Scramjet Test, has been proposed with, unfortunately, no success up to now (Ref 34 ). Such a program, dealing with an integrated propulsion system, would allow extending the already defined development methodology by taking into account new ground test possibilities as, for example, high enthalpy short time wind tunnels F4 at ONERA Fauga or HEG at DLR Göttingen and to acquire a first flight validation.…”

Section: -Conclusion and Perspectivesmentioning

confidence: 99%

French Flight Testing Program LEA Status in 2009

Falempin

Serre²

2009

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

Self Cite

View full text Add to dashboard Cite

French R&T effort for hypersonic airbreathing propulsion is focusing on needed technologies for the propulsion system and acquisition of aero-propulsive balance prediction capability. A large part of technology development effort can be led on ground and is currently dedicated to combustion chamber to ensure its performance and thermomechanical strength. On the contrary, it is mandatory to flight demonstrate capability to predict the aero-propulsive balance. In that view, MBDA and ONERA are leading the flight testing LEA program. Started in January 2003, the program will end in 2015 after 4 autonomous flight tests of an experimental vehicle in Mach number range 4 to 8. Guidelines for LEA vehicle and its propulsion system design have been validated in 2006 by a Preliminary Design Review. The running Phase 2 aims at getting a detailed design while validating the aero-propulsive configuration by a first free jet test series to be performed early in 2011.

show abstract

“…Furthermore, the time allocated for the combustion in SCRamjet mode is about 1 ms. The thermal management of the overall vehicle and more specifically of the combustion chamber is thus an important focus for the aerospace research [2]. In this framework, the COMPARER program (COntrol and Measure of PArameters in a REacting stReam) has been settled by the MBDA-France company and by the Orléans University.…”

Section: Introductionmentioning

confidence: 99%

Characterization of supercritical reactive flow for hypersonic real-time application

Gascoin

Gillard

Bouchez

2009

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

View full text Add to dashboard Cite

In the framework of the hypersonic propulsion, with cooled engine by endothermic hydrocarbon fuel, it is necessary to provide adapted measurement methods for the cooling regulation as for the control of the engine thrust. The sensors should be robust because of the extreme in-flight conditions, of vehicle acceleration and vibration, of the fluid temperature (1500 K) and pressure (3.5 MPa) and of the multi-component supercritical mixture. Their response time should be lower than one second. Therefore, a large range of real time and on line measurement methods has been tested and some of these methods among the most promising are presented in this paper. The aim is not to necessarily develop a new technology but to evaluate the feasibility and the adaptability of existing ones for our purpose, even if those are not especially dedicated for it. Numerical evaluation is firstly conducted then some of the techniques are experimentally tested. Two of them, the sonic throat and the Fourier Transform Infra Red spectroscopy (FTIR), appear to be particularly promising and allow uncertainties of few percents. The first one allows evaluating the mass flow rate of a supercritical reactive mixture. The second one characterizes the chemical composition before injection in the combustion chamber, for mole fraction greater than 5 %.

show abstract

LEA Flight Test Program: Status in 2006

Cited by 6 publications

References 30 publications

Synthetic and jet fuels pyrolysis for cooling and combustion applications

Synthetic and jet fuels pyrolysis for cooling and combustion applications

French Flight Testing Program LEA Status in 2009

Characterization of supercritical reactive flow for hypersonic real-time application

Contact Info

Product

Resources

About