Performance Analysis and Mass Estimation of a Small-Sized Liquid Rocket Engine with Electric-Pump Cycle
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ORIGINAL PAPER
Performance Analysis and Mass Estimation of a Small-Sized Liquid Rocket Engine with Electric-Pump Cycle Juyeon Lee1 · Tae-Seong Roh1 · Hwanil Huh2 · Hyoung Jin Lee1 Received: 7 June 2020 / Revised: 24 August 2020 / Accepted: 14 September 2020 © The Korean Society for Aeronautical & Space Sciences 2020
Abstract The propellant supply system of a liquid rocket engine using an electric pump has high reliability because of the relatively small number of components. The system also has the merit of a quick response and ease of control owing to its simple configuration. Recently, the rocket lab developed the Rutherford engine, which has an electric pump cycle, because of the improved technology in the electric motor and battery. This paper examined the development of the electric-pump cycle and compared the performance with other cycles for a small-sized low-thrust rocket engine. Performance analysis and mass estimation were conducted using the developed analysis program, in which reliability in mass estimation was improved based on the designed configuration or real performance data from commercial products. In addition, the modeling method and analysis procedure were described in detail. The results showed that it is possible to develop a small-sized engine with an electric-pump cycle when the present technologies are applied. The electric-pump cycle had a smaller dry mass than the gas-generator cycle, even at a low thrust level of 500 N, and showed higher performance in specific impulse and speed increments. Keywords Electric-pump cycle · Gas-generator cycle · Small-sized engine · Low thrust level
List of Symbols A D E H MR P K S·F V Q Re Ds Ns Isp
B
Area (m2 ) Diameter (m) Energy (J) Pump head rise (m) Mass ratio Power (W) Loss coefficient Safety factor Volume (m3 ) Volumetric flow rate (m3 /s) Reynolds number Specific diameter (m) Specific speed Specific impulse (s)
Hyoung Jin Lee [email protected]
1
Department of Aerospace Engineering, Inha University, Incheon 22212, Republic of Korea
2
Department of Aerospace Engineering, Chungnam National University, Daejeon 34134, Republic of Korea
f g l m m˙ p r t tb u v L∗ c∗ σzul θ α η ρ ε κ ω δP δE
Friction factor Gravitational acceleration (m/s2 ) Length (m) Mass (kg) Mass flow rate (kg/s) Pressure (Pa) Radius (m) Thickness (m) Burning time (s) Ullage Fluid velocity (m/s) Characteristic length (m) Characteristic velocity (m/s) Yield strength (Pa) Degree Bend angle (degree) Efficiency Density (kg/m3 ) Nozzle area ratio Margin Rotating speed Power density (W/kg) Energy density (W h/kg)
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International Journal of Aeronautical and Space Sciences
v
Velocity increment (m/s)
Subscripts P E b c e elb f gg in inv m n o out p prop pip t tk tp turb
Power Energy Battery Combustion chamber Nozzle exit Elbow Fuel Gas generator Inner, input Inverter Motor Nozzle Oxidizer Outer, output Pump Propellant Pipe Throat Tank Turbo-pump Turbine
1 Introduction Depending on the methods, the propellant supply system of a liquid rocket engine is largely clas
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