Study of a generic SSTO vehicle using airbreathing propulsion

Bonnefond, T.; Falempin, François; Viala, P-L

doi:10.2514/6.1996-4490

Cited by 6 publications

(3 citation statements)

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“…This method was validated in particular with more detailed studies performed in the PREPHA program. 5 The orbit target is 80 £ 500 km , 28.5 deg for the PREPHA-type SSTO generic vehicle.…”

Section: Methodology and Toolsmentioning

confidence: 99%

French-Russian Partnership on Hypersonic Wide-Range Ramjets

Bouchez¹,

Falempin²,

Levine³

et al. 2001

Journal of Propulsion and Power

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France and Russia have an ongoing fruitful cooperation to jointly develop a wide-range ramjet (WRR) able to accelerate a reusable launch vehicle from » Mach 3 to Mach 12. The WRR engine has a fully variable internal geometry, which enables a high performance level over the whole Mach-number range. Propulsion-oriented system studies have been conducted both on 30-tons-class experimental ight vehicle and on 500 tons-class single-stage-toorbit (SSTO) reusable vehicles. In particular, the WRR airbreathing propulsion system has been integrated into a SSTO generic vehicle. Then, trajectory simulation, using mass, propulsion, and aerodynamic models, has allowed determining the payload as a function of total takeoff weight, con rming the utility of the variable geometry features of the WRR. Preliminary experimental and numerical studies have been conducted for several years to design the WRR prototype. The present contribution describes the synthesis of this engine and provides an overview of this common work. Consideration is given to various aspects of the project, including system studies, technology development, and analyses using contour control codes.

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“…This method was validated in particular with more detailed studies performed in the PREPHA program. 5 The orbit target is 80 £ 500 km , 28.5 deg for the PREPHA-type SSTO generic vehicle.…”

Section: Methodology and Toolsmentioning

confidence: 99%

French-Russian Partnership on Hypersonic Wide-Range Ramjets

Bouchez¹,

Falempin²,

Levine³

et al. 2001

Journal of Propulsion and Power

View full text Add to dashboard Cite

show abstract

“…Summarized in Figure 3, the iterative process is based on PROSIT computer code using a rubber SSTO vehicle. This method was validated in particular with more detailed studies performed in PREPHA program 10 . The orbit target is 80 km x 500 km (before The preliminary results presented in Figure 4 have indicated that even heavier, the variable geometry dualmode ramjet is more interesting, but its feasibility has first to be investigated by system studies and by onground technological work.…”

Section: Benefits and Challenges Of Wrrmentioning

confidence: 99%

French-Russian Cooperation in High-Speed Air Breathing Propulsion

Bouchez

Levine

2003

AIAA International Air and Space Symposium and Exposition: The Next 100 Years

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Since 1993, MBDA-F and ONERA have been working with many Russian laboratories and institutes in the topic dealing with future high speed airbreathing propulsion system. Particularly, the fruitful cooperation between Moscow Aviation Institute and MBDA France goes on to prepare together a Wide Range Ramjet able to accelerate a reusable space launcher from at least Mach 3 and up to Mach 12. This work has been realized with several cooperative contracts, funded by French Government and by MBDA-France. MBDA-France and the Moscow Aviation Institute are developing an experimental wide range dual-fuel, dual-mode ramjet. The considered engine has a fully variable internal geometry which gives it a priori a high performance level over the whole Mach number range. Technology development work led to the design and partial demonstration of materials and structures solutions to comply with the variable geometry requirements. Combustion tests and other basic research have taken place for more than 7 years at Moscow Aviation Institute. These technologies should be definitively demonstrated thanks to the test of a large scale Prototype in MBDAFrance Bourges-Subdray Center (connected pipe test up to Mach 7 -entrance of combustor 212x257 mm ² ). Specific computer codes are achieved, allowing to control the Prototype and in particular to optimize its contour in real-time during the test. Numerous subscale tests have been realized (with fixed or simply moving internal geometry) in order to better understand the combustion in the regimes that would occur in a dual-fuel dual-mode ramjet. This cooperation gives also the opportunity to work together on the development of new measurement systems and of a methodology associated with hot fuel-cooled structures for WRR. This paper gives a synthesis and an overview of this common work, with consideration to all aspects.

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“…Finally, the rocket/dual mode ramjet/rocket concept was found as more promising concept due to its better trade-off between performance, mass, complexity… (Ref [4] to [7]). …”

Section: Introductionmentioning

confidence: 99%

French Contribution Towards a Possible Fully Reusable Airbreathing Space Launcher

Falempin

2003

54th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronaut

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Development of operational, civilian or military, application of the hypersonic airbreathing propulsion depends of two key points : development of needed technologies for the propulsion system as a low weight, high robustness fuel-cooled structure for the combustor, capability to predict with a reasonnable accuracy and to optimise the aero-propulsive balance (or generalized thrust-minus-drag balance).

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Study of a generic SSTO vehicle using airbreathing propulsion

Cited by 6 publications

References 0 publications

French-Russian Partnership on Hypersonic Wide-Range Ramjets

French-Russian Partnership on Hypersonic Wide-Range Ramjets

French-Russian Cooperation in High-Speed Air Breathing Propulsion

French Contribution Towards a Possible Fully Reusable Airbreathing Space Launcher

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