A hydrogen peroxide electric pump for throttleable hybrid rocket motor

Liang, Ted; Cai, Guobiao; Gu, Xiaoming; Liu, Zhuo; Li, Cao

doi:10.1016/j.actaastro.2021.12.050

Cited by 24 publications

(8 citation statements)

References 27 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The first firing test of hydrogen peroxide rocket engine with an electric pump is conducted by Beihang University in 2021. The power of electric pump has reached 75kW, the rocket motor thrust is over 16 kN, and the large range thrust throttling technology is verified [15].…”

Section: Introductionmentioning

confidence: 97%

The effect of reflux schemes in hydrogen peroxide electric pump on anti-cavitation of inducer

Tian

et al. 2023

J. Phys.: Conf. Ser.

Self Cite

View full text Add to dashboard Cite

Hydrogen peroxide electric pump supply system can provide an improvement to hybrid rocket motor performance. Due to the physical and chemical properties of hydrogen peroxide, a canned pump scheme is more suitable to be used in hybrid rocket motor. The high-temperature liquid between the rotor and stator of the electric pump, returning to the inlet of the inducer, has a considerable influence on the anti-cavitation performance. The numerical simulation results show that the optimal reflux scheme is different when the inlet pressure range of the inducer is different. When the inlet pressure of the inducer is 0.4 MPa, the performance of the inducer is less affected by the reflux schemes, and the optimal scheme is the axial scheme in the simulation. When the inlet pressure is 0.12 MPa and there is a large cavitation area in the inducer, the radial reflux scheme is better than the axial and mixed reflux. When the inlet pressure is 0.1 MPa and the cavitation areas almost extend to the whole blade passage, the radial reflux scheme is much better than the axial and mixed reflux.

show abstract

Section: Introductionmentioning

confidence: 97%

The effect of reflux schemes in hydrogen peroxide electric pump on anti-cavitation of inducer

Tian

et al. 2023

J. Phys.: Conf. Ser.

Self Cite

View full text Add to dashboard Cite

show abstract

“…Each propellant pump is individually driven by a brushless DC motor featuring a speed of 40000 r/min and power of 37 kW. Since 2020, Beihang University, together with Guizhou Aerospace Linquan Motor, has developed several canned motor pumps for hydrogen peroxide and kerosene, with speeds up to 36000 r/min and power up to 75 kW [6][7][8][9][10]. The pumps were applied to feed systems for both liquid rocket engines and hybrid rocket motors, and firing tests have been successfully performed.…”

Section: Introductionmentioning

confidence: 99%

“…Among the above application of electric pumps, canned motor pumps were adopted in some of the cases, i.e., in ref. [3,4,[6][7][8][9][10]. Owing to elimination of dynamic seals, canned motor pumps are more reliable and compact and thus suitable for delivering risky or hazardous propellants in rocket engines.…”

Section: Introductionmentioning

confidence: 99%

Experimental study on the internal temperature rise of a high-speed canned motor pump for liquid rocket engines

Wang,

Cai,

et al. 2024

J. Phys.: Conf. Ser.

Self Cite

View full text Add to dashboard Cite

High-speed electric pumps are now gradually applied in liquid rocket engines. Compared with the pumps with dynamic seals, the canned motor pumps are more reliable, and thus suitable for delivering risky propellants. However, the partial flow diverted to the air-gap for cooling and lubrication faces the risk of overheating caused by its friction against the rotor. This paper performed an experiment on this issue with a high-speed canned motor pump for a notional rocket engine. Impellers with and without balance holes, as well as different configurations of jet holes, were adopted and their effects were analysed. Results showed that the internal temperature rise decreased by up to 78% when the balance holes were removed, and decreased by up to 40% when the jet hole configuration was modified. Both factors influenced the internal temperature rise by varying the flow rate of the cooling recirculation. The study suggested that the high-speed canned motor pump should be designed with an appropriate flow rate of the cooling recirculation, so as to control the temperature rise of the propellant and ensure safe operation of the rocket engine.

show abstract

“…A high-speed and high-performance motor can replace the traditional turbine as the driving machine of a pump in an electric pump feed system [10][11][12]. Previously limited by miniaturized high-energy power supply, accurate propellant control, light highspeed motor, and other technologies, it was once less used in the aerospace field.…”

Section: Introductionmentioning

confidence: 99%

Starting and Regulating Characteristics of Electric Pump Feed System for LRE under Different Schemes

Zhou

Wang

et al. 2022

Applied Sciences

Self Cite

View full text Add to dashboard Cite

Liquid rocket engines (LREs) are essential power sources for access to space. Electric pump feed systems have received noteworthy attention because of their high efficiency, convenient regulation, and simple structure. In this study, an oxidant feed system with two pumps in parallel was established. The centralized parameter method and the distributed parameter method were used for modeling. The dynamic characteristics of different starting schemes and regulating schemes were obtained. The results show that the asynchronous opening of two pumps led to a pressure peak from the second stage to the third stage. Under the low operating conditions, the pump speed of the asynchronous scheme was about 13,300 r/min, the pump speed of the synchronous scheme was about 12,100 r/min, and the pump speed of the joint adjustment scheme was about 24,800 r/min. The joint adjustment of pump speed and valve opening could increase the pump speed by a factor of one-third, while maintaining the efficiency at a high level. The optimal scheme could be selected according to a genetic algorithm-based calculation process, together with the curves of the flow rate and pressure with pump speed and valve opening. This study can contribute to the application of electric pumps for liquid rocket propulsion.

show abstract

A hydrogen peroxide electric pump for throttleable hybrid rocket motor

Cited by 24 publications

References 27 publications

The effect of reflux schemes in hydrogen peroxide electric pump on anti-cavitation of inducer

The effect of reflux schemes in hydrogen peroxide electric pump on anti-cavitation of inducer

Experimental study on the internal temperature rise of a high-speed canned motor pump for liquid rocket engines

Starting and Regulating Characteristics of Electric Pump Feed System for LRE under Different Schemes

Contact Info

Product

Resources

About