Hyperion - An SSTO vision vehicle concept utilizing rocket-based combined cycle propulsion

Olds, John R.; Bradford, John; Charania, A.C.; Ledsinger, Laura Anne; McCormick, David; Sorensen, Kirk

doi:10.2514/6.1999-4944

Cited by 14 publications

(13 citation statements)

References 7 publications

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“…The main results are 1) general assumptions of the present method are close to current literature, in particular Ref. 11; 2) big interest of the variable WRR concept; 3) potential interest of ODWE mode; and 4) no major interest, with these assumptions, for using cryogenic hydrocarbonsinstead of hydrogen, or for integratingthe rocket in the main airbreathingpropulsion system. The present parametric system study gives interesting guidelines for the use of a variable geometry propulsion system for future airbreathing launchers (SSTO or TSTO).…”

Section: Conclusion On System Studiesmentioning

confidence: 91%

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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Section: Conclusion On System Studiesmentioning

confidence: 91%

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

“…• General assumptions of the present method are close to the current literature, for example 14 , and belong to the «pessimistic assumptions» : for several tons of payload, the computed TOW is about 500 tons and inert mass close to 100 tons. • Big interest of the variable WRR concept • Potential interest of the ODWE mode (computed payload increase of 10 tons) • No major interest, with these assumptions, for using cryogenic hydrocarbons instead of hydrogen, or for integrating the rocket in the main airbreathing propulsion system (RBCC).…”

Section: Rubber Ssto Modelmentioning

confidence: 97%

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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“…A conceptual design of an advanced RLV is Hyperion in the vehicle vision class. It utilizes LOX/LH2 ejector scramjet Rocket-Based Combined Cycle (RBCC) propulsion and it is a horizontal takeoff and horizontal landing SSTO vehicle [17]. Delta clipper SSTO vehicle implements the SSTO VSM functions in a reliable, cost effective, supportable method [18].…”

Section: Single-stage-to-orbit (Ssto)mentioning

confidence: 99%

Reusable Launch Vehicles: Evolution Redefined

Bhavana¹

2013

J Aeronaut Aerospace Eng

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Conserve, Reuse, Reproduce these are the words using which the present day society is trying to make an impact in reducing the excessive usage of the depleting resources and decreasing time as well as in bringing down the cost and in increasing the efficiency of the products. One of the technology's biggest inventions rather innovation at work is the development of The Reusable Launch Vehicle, in short known as the RLV. Reusability is the main criteria behind this vehicle. The vehicle will return back to earth after its task is completed, and is used for further missions. This invention mainly reduces the cost, time and the specified targets can be achieved with the use of fewer resources. The idea of RLV made its foundation in the minds of the scientists in the 1950's but bringing that idea into a real launch vehicle took many years as this idea was beyond the hands of the technology of that time. As the technology developed the path for the successful making of this launch vehicle was getting cleared. There were many factors that were to be considered like the low weight structure, heat shield, the propellants needed to be used, the engines etc. but the main aim was to bring out the concept behind its working and building a proper design which are discussed in this paper. With the ever-growing technology RLV's with improved mechanisms like SSTO, TSTO were developed which are also mentioned below. In near future these RLV's would completely bridge the gap between the earth and the sky.

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Hyperion - An SSTO vision vehicle concept utilizing rocket-based combined cycle propulsion

Cited by 14 publications

References 7 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

Reusable Launch Vehicles: Evolution Redefined

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