System scheme design of electric expander cycle for LOX/LCH4 variable thrust liquid rocket engine

Liang, Tao; Song, Jie; Li, Qinglian; Cui, Peng; Cheng, Peng; Chen, Lanwei

doi:10.1016/j.actaastro.2021.06.015

Cited by 28 publications

(9 citation statements)

References 24 publications

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“…According to the nozzle flow separation standard in the literature [16], the separation position is calculated to improve the accuracy of thrust calculation. In the cooling jacket part, the Bartz method [15] is used to calculate the heat transfer problem on the gas side, and the heat transfer tube flow [17] model is used to calculate the heat transfer on the wall of the thrust chamber and the heat transfer problem with the cooling water. The radiative cooling expansion section is calculated based on the heat conduction and radiative heat transfer models in the literature [18].…”

Section: Combustor and Nozzle Modelsmentioning

confidence: 99%

The dynamic model of the high-thrust orbital maneuvering engine with storable propellant

Wang

Yan

et al. 2022

J. Phys.: Conf. Ser.

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The storable propellant rocket engine has the advantages of long-term storage and rapid use. A new design of a large-thrust orbital maneuvering engine is proposed for the first time and the dynamic model for working process is established by the multi-disciplinary dynamics simulation software AMEsim. The accurate model parameters of hydraulic and combustion components are obtained through actual unit tests. The dynamic characteristics of the engine are calculated and evaluated in detail, and the results show that the system has good robustness to disturbance parameters. The fluctuation of the propellant tank pressure has little influence on operating parameters. The peak pressure of the water hammer, especially at the tank outlet pipe, is about 17 times higher than the stable state. The starting sequence influences working conditions of the mixing ratio regulator and the thrust chamber for less than 0.1s, and has no influence on the stable working state of the engine. The research provides an effective method for designing a high-thrust orbital maneuvering engine system, which has broad prospects in low-Earth orbit transportation and military missions.

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Section: Combustor and Nozzle Modelsmentioning

confidence: 99%

The dynamic model of the high-thrust orbital maneuvering engine with storable propellant

Wang

Yan

et al. 2022

J. Phys.: Conf. Ser.

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“…1,2 Liquid methane presents several opportunities for launchers, such as less-constrained design thanks to the soft-cryo temperature, easier safety conditions for reusable trajectories, and better operability. 3 The electric pump gained more attention in recent years with the development of batteries and electric motors, 4,5 especially after the launch of the Electron rocket with the Rutherford engine pressurized by an electric pump. The electric pump system is easy to control and can respond quickly due to its simple configuration 6 ; thus, it is easier to control the mixture ratio and thrust when throttling.…”

Section: Introductionmentioning

confidence: 99%

Pipeline fault simulation and control of a liquid rocket engine

Cheng

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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The feedback control system was designed to control the pipeline blockage and leakage fault. Based on the open-loop engine system, different degrees of faults were simulated, and the changes in system parameters when faults occur were analyzed. Then, the faults were injected into the engine system with feedback control, and the effects of the controller to different degrees of faults and the changes of the parameters of the electric pump with the controller were studied. The simulation results showed that under the action of the feedback control system, the deviation of the engine system parameters caused by these faults can recover to the set value within a few seconds. When the fault disappears, the system parameters can be still within the normal operating range.

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“…With the developm ent of space technology, liquid oxygen/ m ethane rocket engines have gradually becom e a research hotspot due to their wide fuel source, excellent specific im pulse perform ance, green and non-toxic characteristics, and less carbon accum ulation [1][2][3].Because the boiling point of m ethane m olecules is close to that of the space environm ent, it is easy to store in the deep space environm ent and has a sim ple and easily synthesized structure that can be prepared in situ in extraterrestrial celestial environm ents such as the M oon and M ars, relying on solar energy and easily accessible C O2 and H 2O [4,5], so m ethane is also an ideal fuel for spacecraft attitude orbit controlled rocket engines and deep space exploration engines.…”

Section: Introductionmentioning

confidence: 99%

Effect of dielectric barrier discharge methane reforming products on the combustion performance of rocket engine

Deng

Wei

Zhu

et al. 2023

J. Phys.: Conf. Ser.

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Although the low-thrust liquid oxygen/methane rocket engine has broad application prospects, the low flame propagation speed and low combustion rate of methane fuel make the liquid oxygen/methane engine still face key technical challenges. Methane fuel is partially converted into hydrogen and ethane with higher combustion rate before being injected into the combustion chamber, which is positive for the use of dielectric barrier to improve the combustion performance of the engine. Therefore, this paper studies the effect of the main four products of dielectric barrier discharge reforming with methane conversion rate of 10%, on the flow field of the combustion chamber. The results show that the addition of reforming products can effectively improve the combustion efficiency of the engine. H2 in the reforming product can also improve the specific impulse performance of the engine by increasing the total pressure of the engine chamber. C2H4 will not affect the maximum temperature of the engine, However, it can expand the medium-high temperature range of engine temperature to different degrees. The addition of H2 accelerates the oxygen consumption rate, which provides a feasible way to reduce the design size of the engine and improve the combustion efficiency of the low-thrust engine.

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System scheme design of electric expander cycle for LOX/LCH4 variable thrust liquid rocket engine

Cited by 28 publications

References 24 publications

The dynamic model of the high-thrust orbital maneuvering engine with storable propellant

The dynamic model of the high-thrust orbital maneuvering engine with storable propellant

Pipeline fault simulation and control of a liquid rocket engine

Effect of dielectric barrier discharge methane reforming products on the combustion performance of rocket engine

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