Deep-cooled turbojet augmented with oxygen (cryojet) for a SSTO launch vehicle

Balepin, V.; Maita, Masataka; Tanatsugu, Nobuhiro; Murthy, S. N. B.

doi:10.2514/6.1996-3036

Cited by 6 publications

(2 citation statements)

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“…7 7, and the mass breakdown for vehicle and for the SSTO rocket with a lifting body is the same, as can be seen in Table I. The KLIN cycle vehicle provides an additional payload mass fraction of 2.49% relative to the SSTO rocket vehicle with the lifting body.…”

Section: Mass Breakdownmentioning

confidence: 96%

“…11 the circle denotes the newly chosen design point, k A = 8.0 and <I> = 10% instead of k A = 14.2 and <I> = 6% as in Ref. 7. This leads to a reduction, about 0.3%, in the payload fraction value; however, there are two advantages: (i) the reduced risk in development of such components as the inlet and the cooler, that become smaller and lighter with the reduced cooling ratio; and, rather important, (ii) the reduced heating of hydrogen in the air precooler, noting that the hydrogen is then required to be used in cooling of the rocket combustor.…”

Section: Lre Operationmentioning

confidence: 99%

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'Third Way' of development of SSTO propulsion

Balepin

Maita²,

Murthy

1996

Space Plane and Hypersonic Systems and Technology Conference

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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 LRE-based combined cycle engines, a new cycle, given the name KLIN (meaning wedge in Russian), is proposed as the 'third' way. It consists of a combination of LRE and DCTJ (with oxygen addition to atmospheric air). Currently the KLIN concept is considered for application to a VTOHL vehicle, with the DCTJ and the LRE optimized individually with a possibility for incorporating an aerospike-type nozzle. Retaining a rocket trajectory up to Mach 3 the LRE and the DCTJ are assumed to operate together from take-off with a gradual reduction in the DCTJ output, tinally terminating the DCTJ at Mach 6. It can be shown that the KLIN, although somewhat heavy, can be manufactured with available or foreseeable technology, and provides a combination of engine weight and specific impulse that yields twice the payload mass fraction, in addition to other advantages, compared to a LRE operated vehicle.

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Section: Mass Breakdownmentioning

confidence: 96%

Section: Lre Operationmentioning

confidence: 99%