KLIN cycle - Combined propulsion for vertical take off launcher

Balepin, V.; Maita, Masataka

doi:10.2514/6.1997-2854

Cited by 2 publications

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“…One can visualize a ight scenario consisting of four rather different operational modes. 9 A prole of the vehicle thrust-to-weight ratio in the four modes is given in Fig. 11.…”

Section: Flight Scenario For Lifting-body Launcher With Klin Cycle Prmentioning

confidence: 99%

Third Way of Development of Single-Stage-to-Orbit Propulsion

Balepin

Maita²,

Murthy

2000

Journal of Propulsion and Power

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Considering a number of options for a space-launch vehicle-propulsion system, between advanced rocket motors and airbreathers, in particular, thermally integrated rocket-based combined-cycles, a new cycle that has been given the name KLIN (meaning wedge in Russian), is proposed as the "third way." It consists of a combination of a liquid rocket engine and a deep-cooled turbojet (with oxygen addition to atmospheric air). Currently, the KLIN concept is considered for application with a vertical takeoff horizontal landing vehicle, with the turbojet and the rocket engine optimized individually, with a possibility for incorporating an aerospike-type nozzle. Retaining a rocket trajectory up to Mach 3, the turbojet and rocket engine are assumed to operate together from takeoff with a gradual reduction in the deep-cooled turbojet output, nally terminating the turbojet at Mach 6. It can be shown that the KLIN can be manufactured with available or foreseeable technology, and provides a combination of engine weight and speci c impulse that yields twice the payload mass fraction, in addition to other advantages, compared with a rocket-engine-operated vehicle. NomenclatureC O = concentration of onboard oxygen, 100% by assumption C A O = concentration of oxygen in normal air, 23.15% C R O = concentration of oxygen in air/oxygen mixture, C A O (1 ¡ } ) + } C O F = local speci c thrust I = local speci c impulsē I A B E = average speci c impulse in the airbreathing phasē I L R E = average speci c impulse of the liquid rocket engine K A= air-to-hydrogen ratio or cooling ratio K 0 = oxygen-hydrogen stoichiometric ratio, 7.937 R T W = vehicle thrust-to-mass ratio R 0 = initial thrust-to-mass ratio of vehicle r = initial thrust-to-mass ratio of propulsion system V f = ight speed W g = exhaust gas velocity D V L R E = speed increment in rocket phase of ight d AF = airframe fraction in gross takeoff weight d EN = engine fraction in gross takeoff weight d V A B E = drag and gravity losses in airbreathing phase d V L R E = drag and gravity losses in liquid rocket phase e = equivalence ratio of combined propulsion } = mass fraction of onboard oxygen in the mixed oxidizer

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“…One can visualize a ight scenario consisting of four rather different operational modes. 9 A prole of the vehicle thrust-to-weight ratio in the four modes is given in Fig. 11.…”

Section: Flight Scenario For Lifting-body Launcher With Klin Cycle Prmentioning

confidence: 99%

Third Way of Development of Single-Stage-to-Orbit Propulsion

Balepin

Maita²,

Murthy

2000

Journal of Propulsion and Power

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“…They range from full turbojet to full rocket and various combinations of each. It has been suggested that super cooled LOX injection into the turbojet inlet while in the lower atmosphere will prevent icing and yield as much as 20% more DCTJ thrust 8 . This is yet another option available in the DCTJ + rocket combined-cycle.…”

Section: Figure 6 -Thermally Integrated Dctj + Rocketmentioning

confidence: 99%

An evaluation of two alternate propulsion concepts for Bantam-Argus - Deeply-cooled turbojet + rocket and pulsed detonation rocket + ramjet

Germain

Olds

1999

35th Joint Propulsion Conference and Exhibit

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The Bantam-Argus reusable launch vehicle concept is a smaller version of the original Argus single-stage-to-orbit launch vehicle design. Like the original Argus, Bantam-Argus uses a Maglifter launch assist system to provide an initial horizontal launch velocity. Bantam-Argus is designed to deliver 300 lb. payloads to low earth orbit and, like the full sized Argus, the baseline Bantam-Argus concept utilizes two liquid oxygen/liquid hydrogen supercharged ejector ramjets as prime motive power. This paper presents the results of an investigation of two alternate propulsion systems for the Bantam-Argus launch vehicle. First, a thermally integrated combined-cycle system consisting of two deeplycooled turbojets and two liquid rocket engines was evaluated. Second, a combination propulsion system utilizing two pulsed detonation rocket engines and two standalone ramjets was evaluated.

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KLIN cycle - Combined propulsion for vertical take off launcher

Cited by 2 publications

References 0 publications

Third Way of Development of Single-Stage-to-Orbit Propulsion

Third Way of Development of Single-Stage-to-Orbit Propulsion

An evaluation of two alternate propulsion concepts for Bantam-Argus - Deeply-cooled turbojet + rocket and pulsed detonation rocket + ramjet

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