Three-dimensional numerical and experimental studies on transient ignition of hybrid rocket motor

Tian, Hui; Yu, Ronghai; Zhu, Hao; Wu, Jerry J.; Cai, Guobiao

doi:10.1016/j.actaastro.2017.08.022

Cited by 30 publications

(7 citation statements)

References 11 publications

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“…Note that the design of dualthrust hybrid rocket motors entails a proper understanding of the physical phenomena that control the boundary layer combustion and the core reacting flow dynamic processes. [43][44][45] Though numerous analytical, in vitro, and in silico studies have been carried out comprehensively over the decades for exploring the boundary layer displacement thickness and the flow features of HVT chemical rockets, there were no unique model available until the discovery of the Sanal flow choking phenomenon (2018) for estimating the 3D blockage factors of such chemical rockets. [46] Henceforth, after invoking the Sanal flow choking condition, all the dual-thrust chemical rockets can be designed with the maximum propellant-loading-density with the highest payload capability within the given envelope without inviting any catastrophic failures, which often experienced by the space agency.…”

Section: The Sanal Flow Choking In Chemical Rocketsmentioning

confidence: 99%

RETRACTED: Sanal Flow Choking: A Paradigm Shift in Computational Fluid Dynamics Code Verification and Diagnosing Detonation and Hemorrhage in Real‐World Fluid‐Flow Systems

et al. 2020

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The discovery of Sanal flow choking is a scientific breakthrough and a paradigm shift in the diagnostics of the detonation/hemorrhage in real‐world fluid flow systems. The closed‐form analytical models capable of predicting the boundary‐layer blockage factor for both 2D and 3D cases at the Sanal flow choking for adiabatic and diabatic fluid flow conditions are critically reviewed here. The beauty and novelty of these models stem from the veracity that at the Sanal flow choking condition for diabatic flows all the conservation laws of nature are satisfied at a unique location, which allows for computational fluid dynamics (CFD) code verification. At the Sanal flow choking condition both the thermal choking and the wall‐friction‐induced flow choking occur at a single sonic fluid throat location. The blockage factor predicted at the Sanal flow choking condition can be taken as an infallible data for various in silico model verification, validation, and calibration. The 3D blockage factor at the Sanal flow choking is found to be 45.12% lower than the 2D case of a wall‐bounded diabatic fluid flow system with air as the working fluid. The physical insight of Sanal flow choking presented in this review article sheds light on finding solutions, through in silico experiments in base flow and nanoflows, for numerous unresolved problems carried forward over the centuries in physical, chemical, and biological sciences for humankind.

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Section: The Sanal Flow Choking In Chemical Rocketsmentioning

confidence: 99%

RETRACTED: Sanal Flow Choking: A Paradigm Shift in Computational Fluid Dynamics Code Verification and Diagnosing Detonation and Hemorrhage in Real‐World Fluid‐Flow Systems

et al. 2020

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“…The average regression rate predicted by simulation was 2.64% higher than the test data [28], which indicates that the accuracy of the simulation model is acceptable. The prediction model in the form of the Arrhenius formula is used to solve the regression rate of solid fuel, which can be given as follows [29,30]: . r = A exp(−E a /RT) (6) where A represents the pre-exponential constant, E a is the activation energy, R is the universal gas constant.…”

Section: Solid Fuel Pyrolysis Modelmentioning

confidence: 99%

Long-Duration Dynamic Numerical Simulation of Combustion and Flow in Hybrid Rocket Motors Considering Nozzle Erosion

Meng,

Tian,

Niu

et al. 2024

Aerospace

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Hybrid rocket motors have great development potential due to their outstanding thrust adjustment flexibility and long-term operation ability. However, nozzle erosion during the motor operation can cause an increase in the throat area of the nozzle, which leads to a decrease in combustion chamber pressure and nozzle efficiency. Therefore, a performance prediction model for hybrid rocket motors considering nozzle erosion has become a key technology that must be addressed when developing hybrid rocket motors. This study uses dynamic grid technology to simulate the regression of the combustion surface and nozzle erosion, which fits well with experimental values. The behavior of high-energy particles in the combustion chamber is simulated through a discrete phase model. Notably, distinctive behavior is observed in Al and Mg droplets, with Al droplets exhibiting incomplete vaporization in the combustion chamber while Mg droplets completely vaporize. A ground firing test using the Φ336 mm hybrid rocket motor lasting 200 s is conducted. The results show that the dynamic numerical simulation, accounting for nozzle erosion, substantially enhances performance prediction accuracy. The average deviation in motor thrust remains below 1.8%, and the combustion chamber pressure deviation stays under 2.6%, confirming the precision of the model. Ultimately, both simulation and experimental outcomes indicate a gradual decrease in specific impulse and characteristic velocity over the long-term operation, attributed to the gradual deviation of the oxygen-fuel ratio. This research provides valuable insights for guiding hybrid rocket motor design and optimizing design parameters to improve overall performance. This model can achieve long-duration and high-precision performance predictions for hybrid rocket motors.

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“…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.

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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.

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Three-dimensional numerical and experimental studies on transient ignition of hybrid rocket motor

Cited by 30 publications

References 11 publications

RETRACTED: Sanal Flow Choking: A Paradigm Shift in Computational Fluid Dynamics Code Verification and Diagnosing Detonation and Hemorrhage in Real‐World Fluid‐Flow Systems

RETRACTED: Sanal Flow Choking: A Paradigm Shift in Computational Fluid Dynamics Code Verification and Diagnosing Detonation and Hemorrhage in Real‐World Fluid‐Flow Systems

Long-Duration Dynamic Numerical Simulation of Combustion and Flow in Hybrid Rocket Motors Considering Nozzle Erosion

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

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