Development Status of Le-7a and Le-5b Engines for H-Iia Family

Fukushima, Yo; Nakatsuzi, Hiroyuki; Nagao, Ryuji; Kishimoto, Kenji; Hasegawa, Keiichi; Koganezawa, Takashi; Warashina, Shogo

doi:10.1016/s0094-5765(01)00165-5

Cited by 9 publications

(4 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In addition, the engine lowered the temperature of the fuel passing the turbine and increased the pump's speed to reduce the length of the cooling channel in the combustion chamber. The injector structure was simplified, its parts were reduced from 208 to 127 to reduce production costs, and a spark igniter was used to enable multiple restarts [ 20 ]. The LE-5B-2 engine was developed to suppress low-frequency instability in 2003.…”

Section: Performance and Operation Trend Of Hydrogen-fueled Rocket En...mentioning

confidence: 99%

Development Trend of Liquid Hydrogen-Fueled Rocket Engines (Part 1: Performance and Operation)

Roh

Huh

et al. 2022

Int. J. Aeronaut. Space Sci.

View full text Add to dashboard Cite

SpaceX's successful development of reusable rockets and the realization of low-cost operations have significantly impacted the space industry, institutions, and companies. Price competitiveness has become a hot topic for launch vehicle development. A hydrogen-fueled rocket engine can be its solution. The developed countries are attempting to improve the performance and reliability of engines using a hydrogen-fuel. This paper summarizes the development and operation trends of hydrogen-fueled rocket engines of developed countries. It provides fundamental data for hydrogen-fueled rocket engine development, which is expected to be helpful in its future development.

show abstract

Section: Performance and Operation Trend Of Hydrogen-fueled Rocket En...mentioning

confidence: 99%

Development Trend of Liquid Hydrogen-Fueled Rocket Engines (Part 1: Performance and Operation)

Roh

Huh

et al. 2022

Int. J. Aeronaut. Space Sci.

View full text Add to dashboard Cite

show abstract

“…The LE-7A liquid rocket engine architecture (see [2]) is used to explain a possible fundamental hot fire test strategy. The main components of the LE-7A, which are most likely pertinent to main failure modes, are the turbomachinery on fuel and oxidizer side, the preburner, the thrust chamber assembly, the two ignition systems, the control valve on the fuel side (MFV), the control valves on the oxidizer side (MOV and POV), the mixture ratio setting device, and the heat exchanger.…”

Section: Functional Node Representationmentioning

confidence: 99%

“…The number of hot fire tests in each hot fire test group is defined by k. The total number of equivalent missions in each hot fire test group i is given in Eq. (2).…”

Section: Node 11mentioning

confidence: 99%

A reliability as an independent variable (RAIV) methodology for optimizing test planning for liquid rocket engines

Strunz¹,

Herrmann

2011

CEAS Space J

View full text Add to dashboard Cite

The hot fire test strategy for liquid rocket engines has always been a concern of space industry and agency alike because no recognized standard exists. Previous hot fire test plans focused on the verification of performance requirements but did not explicitly include reliability as a dimensioning variable. The stakeholders are, however, concerned about a hot fire test strategy that balances reliability, schedule, and affordability. A multiple criteria test planning model is presented that provides a framework to optimize the hot fire test strategy with respect to stakeholder concerns. The Staged Combustion Rocket Engine Demonstrator, a program of the European Space Agency, is used as example to provide the quantitative answer to the claim that a reduced thrust scale demonstrator is cost beneficial for a subsequent flight engine development. Scalability aspects of major subsystems are considered in the prior information definition inside the Bayesian framework. The model is also applied to assess the impact of an increase of the demonstrated reliability level on schedule and affordability.

show abstract

“…Taking advantage of no-propellant consumption flight in a dense atmosphere, replacement of the first stage of the Japanese conventional launcher H-IIB [12][13][14][15] with Microwave Rocket is proposed. Millimeter waves have poorer directionality than lasers, so long-distance beam transmission on the order of tens of kilometers remains as a challenge.…”

Section: Introductionmentioning

confidence: 99%

Replacement of chemical rocket launchers by beamed energy propulsion

et al. 2014

View full text Add to dashboard Cite

Microwave Rocket is a beamed energy propulsion system that is expected to reach space at drastically lower cost. This cost reduction is estimated by replacing the first-stage engine and solid rocket boosters of the Japanese H-IIB rocket with Microwave Rocket, using a recently developed thrust model in which thrust is generated through repetitively pulsed microwave detonation with a reed-valve air-breathing system. Results show that Microwave Rocket trajectory, in terms of velocity versus altitude, can be designed similarly to the current H-IIB first stage trajectory. Moreover, the payload ratio can be increased by 450%, resulting in launch-cost reduction of 74%.

show abstract

Development Status of Le-7a and Le-5b Engines for H-Iia Family

Cited by 9 publications

References 1 publication

Development Trend of Liquid Hydrogen-Fueled Rocket Engines (Part 1: Performance and Operation)

Development Trend of Liquid Hydrogen-Fueled Rocket Engines (Part 1: Performance and Operation)

A reliability as an independent variable (RAIV) methodology for optimizing test planning for liquid rocket engines

Replacement of chemical rocket launchers by beamed energy propulsion

Contact Info

Product

Resources

About