Propulsion Systems with Air Precooling for Aerospaceplane

Rudakov, A.S.; Balepin, V.

doi:10.4271/911182

Cited by 14 publications

(3 citation statements)

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“…A rocket is still needed for operations above 160 000 ft and in space, as pointed out by Czysz and co-workers (Czysz 1995;, so each of the propulsion configurations depicted in figure 6 is either a rocket or an airbreather system thermally and physically integrated with a rocket. The latter is very important as demonstrated by Rudakov & Balepin (1991).…”

Section: Aces (2)mentioning

confidence: 92%

“…all of the hydrogen flows through the heat exchanger, rocket and ram-scramjet before being burned. Deeply cooled after Rudakov & Balepin (1991). LACE after Miki et al .…”

Section: Rocket Cyclesmentioning

confidence: 99%

“…KLIN = an air heat exchanger cooling almost to saturation upstream of a turbofan engine, resulting in constant corrected speed turbomachinery with increased airflow and negligible thermal Mach number effects. The air heat exchanger is thermally coupled to an expander rocket as discussed by Rudakov & Balepin (1991).…”

Section: Aces (2)mentioning

confidence: 99%

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A demonstrator for the SSTO launcher with combined cycle propulsion

Czysz

1999

Philosophical Transactions of the Royal Society of London. Seri

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Space launch systems of the 20th century are still regarded as both costly and unsafe. They have never acquired the reliability of commercial aircraft and they cannot abort from lift-off to mid-mission without massive losses. Most types of launchers are sacrificed after launch, and both hardware and environmental costs are significant. The cost of the launcher itself dominates this operation as it is the first, last and only time it flies. The user pays for the entire vehicle. For commercial aircraft operations, the frequency of flight and the lifespan of the aircraft means that the individual passenger pays about £6 for the cost of the aircraft per flight and the remainder is for fuel and operations. For commercial space launch to become both routine and economic, the need is to achieve the reliability, the sustained operation over a long lifespan, and the easy refurbishment of commercial aircraft. In seeking this solution, design studies have accepted that the ballistic missile launch may give way to either vertical or horizontal take-off aircraft using airbreathing propulsion up to a high flight Mach number and rockets thereafter. This paper examines the factors that shape the choice of airbreathing engines and airframe characteristics for SSTO space launchers, transatmospheric vehicles, boost-glide intercontinental range vehicles, and an associated demonstrator vehicle.

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Section: Aces (2)mentioning

confidence: 92%

“…all of the hydrogen flows through the heat exchanger, rocket and ram-scramjet before being burned. Deeply cooled after Rudakov & Balepin (1991). LACE after Miki et al .…”

Section: Rocket Cyclesmentioning

confidence: 99%