Performance assessment of electrically driven pump-fed LOX/kerosene cycle rocket engine: Comparison with gas generator cycle

Kwak, Hyun-Duck; Kwon, Sejin; Choi, Changho

doi:10.1016/j.ast.2018.02.033

Cited by 44 publications

(13 citation statements)

References 15 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Compared with a pressure-fed system, EPPS used on a communication satellite makes the weight and volume of the propellant system reduced. Beyond its application to aircraft and satellites, several studies in the early 2000s used electrically driven pump-fed cycle engines for launch vehicles [11]. Besides, the propellant electric pump designed for delivering liquid hydrogen or methane to the rocket engine was one of the core project topics [12].…”

Section: Nomenclaturementioning

confidence: 99%

System analysis and controller design for the electric pump of a deep-throttling rocket engine

Ferrari

Chen

et al. 2021

Aerospace Science and Technology

View full text Add to dashboard Cite

This paper proposes a controller design for the electric pump of a deep-throttling rocket engine. The nonlinearity of the system is taken into consideration by analyzing the gap metric. Then, proportionalintegral-derivative controller and gain-scheduling linear quadratic regulator are designed. Analyzing the amplitude-and phase-frequency characteristics as well as the pole-zero distribution of the system, the results show that the designed controllers can stabilize the linearized equations in incremental form at different operating points. This indicates that these two controllers are available for the original system in the whole range of working conditions and this is verified in the simulation. Meanwhile, the comparison between proportional-integral-derivative controller and gain-scheduling linear quadratic regulator is presented. It demonstrates that the proportional-integral-derivative controller is better at tracking both step and ramp signals but with worse control signals. It means that the proportionalintegral-derivative controller seems less suitable for real use due to severe oscillations. Meanwhile, the parameter tuning of a proportional-integral-derivative controller depends on more extensive manual tuning. Therefore, the gain-scheduling linear quadratic regulator is preferred.

show abstract

Section: Nomenclaturementioning

confidence: 99%

System analysis and controller design for the electric pump of a deep-throttling rocket engine

Ferrari

Chen

et al. 2021

Aerospace Science and Technology

View full text Add to dashboard Cite

show abstract

“…Set A has already been employed by the authors, back in 2010, for the deterministic optimization of a HP/PE powered HRE [20]. Set B, instead, is taken from the most recent literature available [19].…”

Section: Feed Systemsmentioning

confidence: 99%

“…where P e,max is the maximum electrical power required. In the following, two values for the power density δ ep has been assumed for the electric drive system plus pump: (δ ep ) A = 1.25 kW/kg represents current technology [13,33] and (δ ep ) B = 3.92 kW/kg for advances designs [19]. The electrical power required by the motor to drive the pump is:…”

Section: Epfsmentioning

confidence: 99%

“…Due to their small size and light weight compared to all other technologies, Lithium batteries, are considered for the present application. The authors considered two couples of densities to evaluate battery pack mass: (δ bp ) A = 3.0 kW/kg and (δ be ) A = 90 Wh/kg, based on Ragone plots [34], and (δ bp ) B = 6.95 kW/kg and (δ be ) B = 198.5 Wh/kg, based on state of the art Lithium-Polymer batteries [19]. These kinds of batteries are suitable for HRE applications because they require high power levels for a relatively short time, so that high rate capability is required.…”

Section: Epfsmentioning

confidence: 99%

“…Recently, Ref. [19] assessed the viability of an EPFS LOX/kerosene upper stage for the Korean Space Launch Vehicle-II, which is designed to insert 1500 kg into a 700 km Single Stage to Orbit (SSO) orbit.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Viability of an Electrically Driven Pump-Fed Hybrid Rocket for Small Launcher Upper Stages

2019

View full text Add to dashboard Cite

An electrically driven pump-fed cycle for a hybrid rocket engine is proposed and compared to a simpler gas-pressurized feed system. A liquid-oxygen/paraffin-based fuel hybrid rocket engine which powers the third stage of a Vega-like launcher is considered. Third-stage ignition conditions are assigned, and engine design and payload mass are defined by a proper set of parameters. Uncertainties in the classical regression rate correlation coefficients are taken into account and robust design optimization is carried out with an approach based on an epsilon-constrained evolutionary algorithm. A mission-specific objective function, which takes into account both the payload mass and the ability of the rocket to reach the required final orbit despite uncertainties, is determined by an indirect trajectory optimization approach. The target orbit is a 700 km altitude polar orbit. Results show that electrically driven pump-fed cycle is a viable option for the replacement of the conventional gas-pressurized feed system. Robustness in the design is granted and a remarkable payload gain is achieved, using both present and advanced technologies for electrical systems.

show abstract

Low-Cost Catalysts for Hydrogen Peroxide (H2O2) Thermal Decomposition

Remissa,

Baragh,

Mabrouk

et al. 2024

Space Technology Library

View full text Add to dashboard Cite

Performance assessment of electrically driven pump-fed LOX/kerosene cycle rocket engine: Comparison with gas generator cycle

Cited by 44 publications

References 15 publications

System analysis and controller design for the electric pump of a deep-throttling rocket engine

System analysis and controller design for the electric pump of a deep-throttling rocket engine

Viability of an Electrically Driven Pump-Fed Hybrid Rocket for Small Launcher Upper Stages

Low-Cost Catalysts for Hydrogen Peroxide (H2O2) Thermal Decomposition

Contact Info

Product

Resources

About