Combined engine for a reusable launch vehicle (KLIN cycle)

Balepin, V.; Czysz, Paul A.; Moszee, Raymond

doi:10.2514/6.2001-1911

Cited by 3 publications

(3 citation statements)

References 1 publication

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“…But the designs proposed have flow-to-weight ratio below 0.03 s −1 for 5.5 Mach speed, so the maximal thrust to weight of the heat exchanger is less than 10 for an exhaust speed of 3 km/s. In [43], a heat exchanger for the air precooler was designed using stainless steel tubes with 2 mm outer diameter and 0.1 mm wall thickness. These pipes will break in the 5.5-Mach airflow if made more than 12 cm long.…”

Section: Overview Of Previously Proposed Lasmentioning

confidence: 99%

“…These pipes will break in the 5.5-Mach airflow if made more than 12 cm long. Furthermore, [43] assumes very light, advanced air-breathing engines. If a thrust to weight similar to the Pratt & Whitney J58 engine can be achieved (which was designed for similar airspeed, but without precooler), the total engine's mass will be the 45% of the vehicle's 12 ton dry mass.…”

Section: Overview Of Previously Proposed Lasmentioning

confidence: 99%

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A Low-Cost Launch Assistance System for Orbital Launch Vehicles

Nizhnik¹

2012

International Journal of Aerospace Engineering

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The author reviews the state of art of nonrocket launch assistance systems (LASs) for spaceflight focusing on air launch options. The author proposes an alternative technologically feasible LAS based on a combination of approaches: air launch, high-altitude balloon, and tethered LAS. Proposed LAS can be implemented with the existing off-the-shelf hardware delivering 7 kg to low-earth orbit for the 5200 USD per kg. Proposed design can deliver larger reduction in price and larger orbital payloads with the future advances in the aerostats, ropes, electrical motors, and terrestrial power networks.

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Section: Overview Of Previously Proposed Lasmentioning

confidence: 99%

Section: Overview Of Previously Proposed Lasmentioning

confidence: 99%

A Low-Cost Launch Assistance System for Orbital Launch Vehicles

Nizhnik¹

2012

International Journal of Aerospace Engineering

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“…Though the turbojet offers superior specific impulse below M ∞ ≈ 3, it also adds extra weight and moving parts, which are unused during later flight modes. Other concepts such as the turbojet-rocket hybrid system KLIN T M have been explored as well [16].The focus of this work, however, is on the RBCC concept, which is described in the next section.…”

Section: Combined Cycle Enginesmentioning

confidence: 99%

Supersonic Multi-Objective Optimization of a Rocket Based Combined Cycle Inlet by Differential Evolution

Jee¹

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The use of differential evolution (DE) is investigated for the optimization of a novel rocket based combined cycle (RBCC) engine inlet, over the supersonic flight regime.An RBCC engine is designed to incorporate the advantages of both rocket propulsion and airbreathing engines. This novel design is the result of ongoing research, at Carleton University, to improve the efficiency of future single stage to orbit engine designs. This novel inlet design, referred to as the exchange inlet, is designed to entrain air using a semi-annular rocket-ejector exhaust profile. The purpose of the exchange inlet is to increase the air mass flow and air/fuel mixing over existing rocket ejector/RBCC designs. In addition, by using a single circular rocket throat the exchange inlet is designed to be compatible with existing rockets.

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Liquid air augmented rocket engine for a small reusable SSTO launcher (more rocket than any rocket-based combined cycle)

Balepin

2001

37th Joint Propulsion Conference and Exhibit

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Combined engine for a reusable launch vehicle (KLIN cycle)

Cited by 3 publications

References 1 publication

A Low-Cost Launch Assistance System for Orbital Launch Vehicles

A Low-Cost Launch Assistance System for Orbital Launch Vehicles

Supersonic Multi-Objective Optimization of a Rocket Based Combined Cycle Inlet by Differential Evolution

Liquid air augmented rocket engine for a small reusable SSTO launcher (more rocket than any rocket-based combined cycle)

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