Transient investigation of nozzle erosion in a long-time working hybrid rocket motor

Tian, Hui; He, Lingfei; Yu, Ronghai; Zhao, Shujian; Wang, Pengfei; Cai, Guobiao; Zhang, Yuanjun

doi:10.1016/j.ast.2021.106978

Cited by 32 publications

(9 citation statements)

References 39 publications

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“…Although Song et al [8] focused on calculating the transient flow characteristics within a solid rocket motor having a pintle nozzle, which has highly unsteady features, they used a common thrust force formula based on exit momentum and pressure in their studies, too. Other researches have been done in the field of transient phenomena in rocket engines [9][10][11][12][13].…”

Section: Introductionmentioning

confidence: 99%

Transient thrust behavior of low‐aspect‐ratio rocket propulsion systems**

Zanjani

Tahsini

2023

Propellants Explo Pyrotec

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In this work, the transient thrust force of the solid propellant rocket motor is numerically computed to illustrate the shortcomings of the common thrust formula in transient periods of operation. The internal ballistics of the solid rocket motor is simulated using the quasi one‐dimensional governing equations in which the finite volume method and the Roe′s scheme are utilized in calculation procedure. This is demonstrated that in transient operation of the propulsion systems, the common thrust formula may ignore some parts of physical phenomena because it has been derived based on steady state assumption, but there are some moving waves in transient operation in the combustion chamber which induce the fluctuations on the thrust force. So, the thrust‐time history must be computed by pressure force integration over the whole solid boundaries of the motor at any instant. The results show that such transient thrust behavior is more intense in low aspect ratio propulsion systems like small space thrusters.

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Section: Introductionmentioning

confidence: 99%

Transient thrust behavior of low‐aspect‐ratio rocket propulsion systems**

Zanjani

Tahsini

2023

Propellants Explo Pyrotec

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“…9,10 Molecular oxygen, as a common oxidizer for rockets, is an important oxidative component in the rocket propellant gas. 6 During the working process of rockets, molecular oxygen reacts with CFs within the throat inserts and is responsible for throat inserts' chemical erosion. Therefore, a precise CF/O 2 kinetic model depicting the C/C material ablation behavior under high temperature is essential for throat insert ablation prediction.…”

Section: Introductionmentioning

confidence: 99%

“…Therefore, a precise CF/O 2 kinetic model depicting the C/C material ablation behavior under high temperature is essential for throat insert ablation prediction. 6,11 The experimental ways to obtain the oxidation rate of graphite or CF networks include flow-tube experiments 12−19 and molecular beam experiments. 20−23 Flow-tube experiments place the heated carbon material specimens inside the oxidative component gas flow to inspect their oxidation rate.…”

Section: Introductionmentioning

confidence: 99%

“…Carbon–carbon (C/C) materials, composed of a network of carbon fibers (CFs) infused with a carbon matrix, have been adopted as low-ablation materials in the aerospace industry due to their high mechanical strength and low ablation rate. – Two typical thermal protection applications for C/C material include reentry ablators and rocket throat inserts. – In the reentry scenario, C/C material acts as a heat shield preventing spacecraft from overheating and, consequently, structural failure . Similarly, for rocket nozzle applications, C/C material throat inserts withstand the erosion caused by high-temperature oxidative propellant gases alleviating thrust drop or thrust deviation. , Molecular oxygen, as a common oxidizer for rockets, is an important oxidative component in the rocket propellant gas . During the working process of rockets, molecular oxygen reacts with CFs within the throat inserts and is responsible for throat inserts’ chemical erosion.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Multiscale Investigation of Carbon Fiber Oxidation Kinetics: Bridging Atomistic Simulation and a Finite-Rate Reaction Model

Tian,

Niu,

Jiang

et al. 2023

J. Phys. Chem. C

Self Cite

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Carbon fibers (CFs) have wide applications in spacecraft thermal protection systems because of their high mechanical strength and low ablation rate. As a thermally resistant material, obtaining carbon fiber’s oxidation kinetics under extreme temperatures is crucial for predicting its ablation behavior. However, the CF oxidation kinetics under extreme temperatures are still unclear. Here, we propose an approach for building a macroscale applicable finite-rate CF oxidation model based on atomistic simulations. In the microscale, the carbines on the CF surface are discovered to serve as active sites that adsorb O atoms while determining the overall oxidation rate. The capital reaction paths including O2 adsorption, surface complex transformation, and CO and CO2 desorption are revealed by tracking atoms’ states. With reaction paths and reaction coefficients determined from atomistic simulations, a finite-rate model is established at temperatures ranging from 2750 to 3750 K. This model is capable of illustrating the high-temperature CO-predominant phenomenon. Also, its steady-state output is applied to predict the graphite ablation rate, which shows excellent agreement with previous flow-tube experiment results. This CF/O2 finite-rate model is applicable to high-temperature scenarios, and this research provides a new guideline for building CF/oxidative-component surface chemistry models from atomistic simulations..

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“…Lots of investigations of nozzle ablation in HRM have been performed. Transient investigations of nozzle erosion were conducted in [7]. The movement of nozzle wall was calculated through dynamic mesh method, and nozzle throat history in the numerical simulation and firing test was obtained.…”

mentioning

confidence: 99%

Transient numerical investigation on thermochemical erosion of C/C nozzles in hybrid rocket motors

Jiang,

Tian,

2024

J. Phys.: Conf. Ser.

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Nozzle erosion is a vital important issue that impacts the performance of hybrid rocket motors. Serious nozzle erosion may significantly decrease the combustion chamber pressure and thrust, which increases the difficulty in designing flight control systems. This paper aims to reveal erosion mechanism systematically. In this paper, transient numerical simulations of thermochemical erosion in hybrid rocket motors are conducted, and combustion flow and thermochemical erosion are coupled calculated. The numerical computation of combustion flow is based on the chemical reactions of propellants and regression rate model, and that of thermochemical erosion is based on the surface reactions between oxidizing species and carbon. The movement of burning surface and nozzle inner surface is simulated through dynamic mesh method. The hybrid rocket motor adopts 90% hydrogen peroxide and hydroxyl-terminated polybutadiene. Distributions of flow field parameters and fuel regression rate are given. The spatial developing process of nozzle surface is presented, and it is found that the roughness of nozzle profile increases with time. The nozzle wall temperature and wall pressure decline with time. Erosion by different species is calculated. OH and H2O make a major contribution to the nozzle thermochemical erosion, while nozzle erosion contributed by CO2 and O2 are quite low. Time-varying characteristics of the erosion rate are unveiled. At the first 1.5 s, the total erosion rate remains almost constant, and then it reduces over time.

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Transient investigation of nozzle erosion in a long-time working hybrid rocket motor

Cited by 32 publications

References 39 publications

Transient thrust behavior of low‐aspect‐ratio rocket propulsion systems**

Transient thrust behavior of low‐aspect‐ratio rocket propulsion systems**

Multiscale Investigation of Carbon Fiber Oxidation Kinetics: Bridging Atomistic Simulation and a Finite-Rate Reaction Model

Transient numerical investigation on thermochemical erosion of C/C nozzles in hybrid rocket motors

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