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Experimental Investigation on Performance of Pulse Detonation Rocket Engine Model 被引量:2
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作者 LI Qiang FAN Wei YAN Chuan-jun HU Cheng-qi YE Bin 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2007年第1期9-14,共6页
The PDRE test model used in these experiments utilized kerosene as the fuel, oxygen as oxidizer, and nitrogen as purge gas. The solenoid valves were employed to control intermittent supplies of kerosene, oxygen and pu... The PDRE test model used in these experiments utilized kerosene as the fuel, oxygen as oxidizer, and nitrogen as purge gas. The solenoid valves were employed to control intermittent supplies of kerosene, oxygen and purge gas. PDRE test model was 50 mm in inner diameter by 1.2 m long. The DDT (deflagration to detonation transition) enhancement device Shchelkin spiral was used in the test model. The effects of detonation frequency on its time-averaged thrust and specific impulse were experimentally investigated. The obtained results showes that the time-averaged thrust of PDRE test model was approximately proportional to the detonation frequency. For the detonation frequency 20 Hz, the time-averaged thrust was around 107 N, and the specific impulse was around 125 s. The nozzle experiments were conducted using PDRE test model with three traditional nozzles. The experimental results obtained demonstrated that all of those nozzles could augment the thrust and specific impulse. Among those three nozzles, the convergent nozzle had the largest increased augmentation, which was approximately 18%, under the specific condition of the experiment. 展开更多
关键词 pulse detonation rocket engine IMPULSE NOZZLE experimental investigation
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An Experiment on Cavitating Flow in Rocket Engine Inducer 被引量:1
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作者 LI Longxian DING Zhenxiao +1 位作者 ZHOU Liang WU Yuzhen 《Transactions of Nanjing University of Aeronautics and Astronautics》 EI CSCD 2019年第2期306-312,共7页
An experiment for rocket engine inducer cavitating flow is conducted on a new experimental platform.The experiment platform,using water as working medium,can be used to investigate the steady and unsteady flows of cav... An experiment for rocket engine inducer cavitating flow is conducted on a new experimental platform.The experiment platform,using water as working medium,can be used to investigate the steady and unsteady flows of cavitating and noncavitating turbopumps.The experimental platform is designed as a flexible and versatile apparatus for any kind of fluid dynamic phenomena relating to high performance liquid rocket engine turbopumps.Design details for the platform is introduced.Various extend of cavitation images and dynamic pressure impulse are obtained,which provides a reference for cavitating flow study in rocket engine inducer. 展开更多
关键词 rocket engine TURBOPUMP INDUCER EXPERIMENT research apparatus CAVITATION images dynamic pressure
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Ignition characteristics and combustion performances of a LO_2/GCH_4 small thrust rocket engine 被引量:2
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作者 ZHANG Jia-qi LI Qing-lian SHEN Chi-bing 《Journal of Central South University》 SCIE EI CAS CSCD 2018年第3期646-652,共7页
A 500 N model engine filled with LO2/GCH4 was designed and manufactured.A series of ignition attempts were performed in it by both head spark plug and body spark plug.Results show that the engine can be ignited but th... A 500 N model engine filled with LO2/GCH4 was designed and manufactured.A series of ignition attempts were performed in it by both head spark plug and body spark plug.Results show that the engine can be ignited but the combustion cannot be sustained when head spark plug applied as the plug tip was set in the gaseous low-velocity zone with thin spray.This is mainly because flame from this zone cannot supply enough ignition energy for the whole chamber.However,reliable ignition and stable combustion can be achieved by body spark plug.As the O/F ratio increases from 2.61 to 3.49,chamber pressure increases from 0.474 to 0.925 MPa and combustion efficiency increases from 57.8%to 95.1%.This is determined by the injector configuration,which cannot produce the sufficiently breakup of the liquid oxygen on the low flow rate case. 展开更多
关键词 LO2/GCH4 small thrust rocket engine ignition characteristic combustion performance
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Technical Innovation of LH2/LOX Rocket Engines in China 被引量:3
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作者 LI Chengzhi MA Bingtao 《Chinese Annals of History of Science and Technology》 2020年第2期160-182,共23页
This paper provides a detailed introduction to and analysis of the course of China's technological innovation in liquid hydrogen/liquid oxygen(LH2/LOX)rocket engines from a historical point of view.It starts with ... This paper provides a detailed introduction to and analysis of the course of China's technological innovation in liquid hydrogen/liquid oxygen(LH2/LOX)rocket engines from a historical point of view.It starts with the investigation of LH2/LOX rocket engines by relevant departments of the Chinese Academy of Sciences in the 1960s and their preliminary achievements.Then,the policy decision concerning LH2/LOX engine development,the project approval of the Long March-3(Chang Zheng-3,CZ-3)rocket,and the process of developing LH2/LOX engines are analyzed in detail,followed by an introduction to and summary of the development situation and technical innovation characteristics of China's LH2/LOX engines as they grew from 4 tons to 8 tons,and finally to 50 tons.Finally,the paper briefly analyzes the innovation experience connected with China's LH2/LOX engines. 展开更多
关键词 LH2/LOX rocket engines technological innovation historical process China
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Based on Fluent Numerical Calculation of Refractive Index on Rocket Engine Nozzle Plume 被引量:1
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作者 Qiangfeng Huang Xiong Wan +3 位作者 Zhimin Zhang Huaming Zhang Hengyang Shen Tingting Du 《Optics and Photonics Journal》 2013年第2期90-93,共4页
Numerical 2D simulation and research on internal flow field and external flow field of rocket motor nozzle using FLUENT software. Analyze the flow condition of internal flow field and external flow field, and accordin... Numerical 2D simulation and research on internal flow field and external flow field of rocket motor nozzle using FLUENT software. Analyze the flow condition of internal flow field and external flow field, and according to add in the amount of the different gas components, obtain the clear distribution of contour of density flow field, pressure flow field and various material components and so on. Simulation results agree with the results observed from the test on the ground, and provide reference for solid rocket motor development. 展开更多
关键词 rocket engine NOZZLE NOZZLE PLUME FLUENT NUMERICAL Simulation
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Progress in Technology of Main Liquid Rocket Engines of Launch Vehicles in China 被引量:8
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作者 TAN Yonghua ZHAO Jian +1 位作者 CHEN Jianhua XU Zhiyu 《Aerospace China》 2020年第2期23-30,共8页
Liquid propellant rocket engines for a launch vehicle are an essential aerospace technology, representing the advanced level of hi-tech in a country. In recent years, China’s aerospace industry has made remarkable ac... Liquid propellant rocket engines for a launch vehicle are an essential aerospace technology, representing the advanced level of hi-tech in a country. In recent years, China’s aerospace industry has made remarkable achievements, and liquid rocket engine technology has also been effectively developed. In this article, the development processes of China’s liquid rocket engines are discussed. Then, the performance features of China’s new generation liquid rocket engines as well as the flight tests of the new-generation launch vehicles are introduced. Finally, the development direction and the most recent progress of the next generation large-thrust liquid rocket engine is presented. 展开更多
关键词 China’s aerospace industry liquid rocket engine technology progress
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Safety Analysis of Liquid Rocket Engine Using Bayesian Networks 被引量:1
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作者 王华伟 严志强 《Defence Technology(防务技术)》 SCIE EI CAS 2007年第1期59-63,共5页
Safety analysis for liquid rocket engine has a great meaning for shortening development cycle, saving development expenditure and reducing development risk. The relationship between the structure and component of liqu... Safety analysis for liquid rocket engine has a great meaning for shortening development cycle, saving development expenditure and reducing development risk. The relationship between the structure and component of liquid rocket engine is much more complex, furthermore test data are absent in development phase. Thereby, the uncertainties exist in safety analysis for liquid rocket engine. A safety analysis model integrated with FMEA(failure mode and effect analysis) based on Bayesian networks (BN) is brought forward for liquid rocket engine, which can combine qualitative analysis with quantitative decision. The method has the advantages of fusing multi-information, saving sample amount and having high veracity. An example shows that the method is efficient. 展开更多
关键词 液体火箭发动机 安全分析 FMEA 贝叶斯网络 不确定信息
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Research on Key Technologies for Reusable Liquid Rocket Engines 被引量:4
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作者 LI Bin 《Aerospace China》 2022年第4期24-34,共11页
Based on current research,the development trend of reusable liquid rocket engines was analyzed.Key technologies and research focuses of the reusable liquid rocket engine have been analyzed and summarized,and then sugg... Based on current research,the development trend of reusable liquid rocket engines was analyzed.Key technologies and research focuses of the reusable liquid rocket engine have been analyzed and summarized,and then suggestions on the development of future key technologies are proposed. 展开更多
关键词 REUSABLE liquid rocket engine development trend key technology
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Numerical and Experimental Characterizations of SiFRP Ablator for the Application to Liquid Rocket Engine Combustors
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作者 Kenichi Hirai Kiyoshi Kinefuchi Toru Kamita 《Journal of Energy and Power Engineering》 2013年第3期440-464,共25页
The ablative material is supposed to be one of good candidates for LRE (liquid rocket engine) combustion chamber to achieve both high reliability and low cost and a numerical analysis for the ablator is considered t... The ablative material is supposed to be one of good candidates for LRE (liquid rocket engine) combustion chamber to achieve both high reliability and low cost and a numerical analysis for the ablator is considered to be a potentially efficient tool to reduce cost as well. So far, ablators have been successfully applied for many SRM (solid rocket motors), but the application to LRE is still quite limited in Japan. The authors believe that this is primarily because of the unpredictable nature of the heat load from combustion gases to the combustor wall. Indeed, reliable thermal design of ablative combustion chamber, namely reliable prediction of thermal performance, needs both reliable heat load model and reliable ablator response model. This paper elaborates our research activities and our recent research findings. 展开更多
关键词 Ablation heat shield liquid rocket engine surface recession silica phenolic.
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An Electro-Hydraulic Actuator for the TVC of a Throttlable Kerolox Rocket Engine
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作者 LIU Hong CHEN Keqin +3 位作者 LAN Tian WANG Yuhao ZHAO Yingxin ZHAO Shoujun 《Aerospace China》 2021年第2期53-58,共6页
An electro-hydraulic actuator for the thrust vector control(TVC)of a throttlable kerolox rocket engine is introduced in this paper.The creative feature is an integrated hydraulic power drive unit,where a constant spee... An electro-hydraulic actuator for the thrust vector control(TVC)of a throttlable kerolox rocket engine is introduced in this paper.The creative feature is an integrated hydraulic power drive unit,where a constant speed kerosene motor is used to draw high pressure kerosene from the engine and to drive a constant pressure variable displacement piston pump,acting as the power supply for the actuator.Its operational mechanism,to accommodate the varying pressure from the turbo-pump of a throttling engine,lies in a pressure-reducing flow regulator inserted at the motor inlet.Another key point is that the displacement of the motor is reasonably bigger than the pump so that a sufficiently wide range of pressures can be adapted.Modeling analysis and flight test results were well matched,which show the outstanding performance of this novel type actuator. 展开更多
关键词 kerolox rocket engine thrust adjusting electro-hydraulic actuator
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Gas film/regenerative composite cooling characteristics of the liquid oxygen/liquid methane (LOX/LCH4) rocket engine
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作者 Xinlin LIU Jun SUN +3 位作者 Zhuohang JIANG Qinglian LI Peng CHENG Jie SONG 《Journal of Zhejiang University-Science A(Applied Physics & Engineering)》 SCIE EI CAS CSCD 2024年第8期631-649,共19页
The thermal protection of rocket engines is a crucial aspect of rocket engine design.In this paper,the gas film/regenerative composite cooling of the liquid oxygen/liquid methane(LOX/LCH4)rocket engine thrust chamber ... The thermal protection of rocket engines is a crucial aspect of rocket engine design.In this paper,the gas film/regenerative composite cooling of the liquid oxygen/liquid methane(LOX/LCH4)rocket engine thrust chamber was investigated.A gas film/regenerative composite cooling model was developed based on the Grisson gas film cooling efficiency formula and the one-dimensional regenerative cooling model.The accuracy of the model was validated through experiments conducted on a 6 kg/s level gas film/regenerative composite cooling thrust chamber.Additionally,key parameters related to heat transfer performance were calculated.The results demonstrate that the model is sufficiently accurate to be used as a preliminary design tool.The temperature rise error of the coolant,when compared with the experimental results,was found to be less than 10%.Although the pressure drop error is relatively large,the calculated results still provide valuable guidance for heat transfer analysis.In addition,the performance of composite cooling is observed to be superior to regenerative cooling.Increasing the gas film flow rate results in higher cooling efficiency and a lower gas-side wall temperature.Furthermore,the position at which the gas film is introduced greatly impacts the cooling performance.The optimal introduction position for the gas film is determined when the film is introduced from a single row of holes.This optimal introduction position results in a more uniform wall temperature distribution and reduces the peak temperature.Lastly,it is observed that a double row of holes,when compared to a single row of holes,enhances the cooling effect in the superposition area of the gas film and further lowers the gas-side wall temperature.These results provide a basis for the design of gas film/regenerative composite cooling systems. 展开更多
关键词 Liquid oxygen/liquid methane(LOX/LCH4)rocket engine Gas film cooling Regenerative cooling Heat transfer characteristics
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Brief Review of N2O Decomposition Catalysts for Engines 被引量:1
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作者 A.A.Boryaev 《火炸药学报》 EI CAS CSCD 北大核心 2020年第2期116-132,共17页
A brief review of nitrous oxide decomposition catalysts was presented.The features of catalyst operating conditions in low-thrust engines of space vehicles and requirements to monopropellant(hydrogen peroxide,hydrazin... A brief review of nitrous oxide decomposition catalysts was presented.The features of catalyst operating conditions in low-thrust engines of space vehicles and requirements to monopropellant(hydrogen peroxide,hydrazine,nitrous oxide)decomposition catalysts were considered.A scientific basis for development of a nitrous oxide decomposition catalyst and general principles for selection of efficient catalysts were formulated.The results of selecting catalyst systems for the development of decomposition catalysts for N2O as a monopropellant were presented.Preliminary selection of catalyst systems for the development of a catalyst designed for low-thrust rocket engines(LTREs)was carried out:supporter—Al2O3 and ZrO2;active substances—Co,Ni,Fe,Pd,Rh,Pt,Ru,Ir,NiO,Fe2O3,RuO2,Rh2O3,PdO,IrO2,PtO2,CoO,Al2O3,La2NiO4,Nd2NiO4,Pr 2NiO4,La2O3,TiO2,NiO,La2O3,TiO2,ZnO.With 71 references. 展开更多
关键词 PROPELLANT nitrous OXIDE catalyst LOW-THRUST rocket engine
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Underwater Explosion Technology for Offshore Engineering Applications 被引量:1
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作者 Hu Tiezhao Senior Engineer, Bohai Oil Company, 300452 Tianjin 《China Ocean Engineering》 SCIE EI 1992年第3期377-382,共6页
- This article briefs how to improve the holding power of a drilling vessel's anchor and to remove those unreasonable structures by such a technology - underwater-explosion technology. The article gives details of... - This article briefs how to improve the holding power of a drilling vessel's anchor and to remove those unreasonable structures by such a technology - underwater-explosion technology. The article gives details of the structure, characteristics and applications of a rocket-launched anchor; as well as the principle, properties, applications of directional explosion cutting. 展开更多
关键词 offshore engineering CONSTRUCTION underwater operation directional explosion rocket-launched anchor
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China's Largest Thrust Solid Engine Hot Firing Test Succeeded
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作者 RONG Yuanzhao CHEN Xu 《Aerospace China》 2019年第1期59-59,共1页
On March 5,a 200 t-thrust advanced solid engine completed its ground hot firing test with success.The engine was developed by the Academy of Aerospace Solid Propulsion Technology(AASPT),aiming at future commercial spa... On March 5,a 200 t-thrust advanced solid engine completed its ground hot firing test with success.The engine was developed by the Academy of Aerospace Solid Propulsion Technology(AASPT),aiming at future commercial space launch service market.It is a solid fuel rocket engine with the maximum capacity and the largest thrust among the existing Chinese solid fuel engines. 展开更多
关键词 THRUST SOLID engine rocket MAXIMUM capacity
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重复使用运载火箭液体动力技术发展 被引量:1
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作者 李斌 李程 +2 位作者 高玉闪 张淼 吕发正 《火箭推进》 CAS 北大核心 2024年第1期1-11,I0002,共12页
重复使用是未来运载火箭更新换代的技术发展趋势,是降低航天发射成本、实现规模化航天发射的有效途径。重点概述了国内外垂直起降重复使用运载火箭动力技术的发展现状,分析了垂直起降重复使用运载火箭发射和回收全任务剖面,总结了垂直... 重复使用是未来运载火箭更新换代的技术发展趋势,是降低航天发射成本、实现规模化航天发射的有效途径。重点概述了国内外垂直起降重复使用运载火箭动力技术的发展现状,分析了垂直起降重复使用运载火箭发射和回收全任务剖面,总结了垂直起降重复使用运载火箭动力技术的特点,包括宽范围入口压力多次启动技术、大范围快速高精度推力调节技术、故障诊断及健康管理技术、状态检测与维修维护技术等。 展开更多
关键词 垂直起降 重复使用 液体火箭发动机 运载技术
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液体火箭发动机健康监控技术研究进展 被引量:1
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作者 杨述明 谢昌霖 +1 位作者 程玉强 宋立军 《火箭推进》 CAS 北大核心 2024年第1期28-45,共18页
液体火箭发动机健康监控技术作为保障运载火箭安全、可靠发射的核心关键技术,经过几十年的发展,有力推动了航天事业的进步。介绍了液体火箭发动机健康监控技术中故障检测与诊断、容错控制与健康监控系统研制等技术的研究现状与发展趋势... 液体火箭发动机健康监控技术作为保障运载火箭安全、可靠发射的核心关键技术,经过几十年的发展,有力推动了航天事业的进步。介绍了液体火箭发动机健康监控技术中故障检测与诊断、容错控制与健康监控系统研制等技术的研究现状与发展趋势;梳理了健康监控领域面临的重难点问题,并提出相应的解决方案。分析展望了液体火箭发动机健康监控技术未来发展趋势,为从事火箭发动机健康监控技术研究的科研人员提供参考。 展开更多
关键词 液体火箭发动机 健康监控技术 故障检测与诊断 容错控制 健康监控系统
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助推段火箭发动机喷焰红外辐射特性数值计算
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作者 张腾 牛青林 +2 位作者 柳云峰 高文强 董士奎 《兵工学报》 EI CAS CSCD 北大核心 2024年第7期2228-2239,共12页
助推段火箭发动机尾喷焰具有显著的红外辐射特性,成为天基红外预警系统重点关注的对象。以三组元固体发动机为研究对象,建立连续流域和过渡流域的尾喷焰反应流场计算模型,采用两级助推段质心弹道法确定飞行弹道,通过反向寻优法完备发动... 助推段火箭发动机尾喷焰具有显著的红外辐射特性,成为天基红外预警系统重点关注的对象。以三组元固体发动机为研究对象,建立连续流域和过渡流域的尾喷焰反应流场计算模型,采用两级助推段质心弹道法确定飞行弹道,通过反向寻优法完备发动机型谱参数,基于等效单喷管法简化流场计算,基于窄谱带法和视在光线法计算尾喷焰的红外辐射特性。研究结果表明:复燃效应使得尾喷焰红外辐射光谱强度升高约20倍,谱带积分强度升高约10倍;尾喷焰红外光谱存在2.7μm和4.3μm的特征峰值;低空流域的光谱强度较高,且不同谱带内积分强度随高度的升高呈现出波动规律和暗区现象;助推段尾喷焰辐射强度差值高达3个量级,尤其在4.3μm较为明显。所得成果可为火箭在助推段的探测和识别提供一定的理论参考。 展开更多
关键词 火箭发动机 三组元推进剂 助推段 尾喷焰 红外辐射
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基于Hessian局部线性嵌入和MLP-Mixer的液体火箭发动机涡轮泵轻量化故障诊断框架
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作者 窦唯 赵东方 +1 位作者 张宏利 刘树林 《振动与冲击》 EI CSCD 北大核心 2024年第2期156-165,共10页
作为液体火箭发动机推进剂输送系统的关键部件,涡轮泵的运行状态直接影响着整个运载系统的性能,然而,现有的故障诊断方法往往面临特性参数选择片面及计算复杂度高等问题。针对上述局限,提出了面向涡轮泵的轻量化故障诊断框架。所提方法... 作为液体火箭发动机推进剂输送系统的关键部件,涡轮泵的运行状态直接影响着整个运载系统的性能,然而,现有的故障诊断方法往往面临特性参数选择片面及计算复杂度高等问题。针对上述局限,提出了面向涡轮泵的轻量化故障诊断框架。所提方法利用Hessian局部线性嵌入算法对信号时域、频域及时频特征进行降维,并引入一种轻量化的深度学习模型MLP-Mixer作为分类器,进而实现不同故障状态的辨识。采用某型号涡轮泵试车数据验证了所提方法的有效性,结果表明,该方法能够在保障诊断精度的同时有效降低计算复杂度,提高诊断效率。 展开更多
关键词 液体火箭发动机涡轮泵 故障诊断 Hessian局部线性嵌入 MLP-Mixer
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泵入口参数对全流量补燃循环发动机动态特性影响研究
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作者 王珏 周闯 +2 位作者 朱平平 俞南嘉 蔡国飙 《宇航总体技术》 2024年第4期31-42,共12页
全流量补燃循环发动机性能高,并具备便于重复使用的优势,是未来重复使用运载器的最佳选择之一。在液体火箭发动机启动过程中,泵入口推进剂的压力和温度变化会对全流量补燃循环发动机动力系统的启动特性造成一定的影响。为分析其影响规律... 全流量补燃循环发动机性能高,并具备便于重复使用的优势,是未来重复使用运载器的最佳选择之一。在液体火箭发动机启动过程中,泵入口推进剂的压力和温度变化会对全流量补燃循环发动机动力系统的启动特性造成一定的影响。为分析其影响规律,建立了涡轮泵、预燃室、推力室、两相流和混合气体组件等动力学模型并进行求解。结果表明,随着燃料泵入口压力升高或氧化剂泵入口压力降低,涡轮泵系统参数的波动将会逐渐增大,甲烷温度和液氧温度所产生的影响要强于甲烷压力和液氧压力,而液氧的影响则强于甲烷。为动力系统中泵入口推进剂状态参数控制提供了一定的指导。 展开更多
关键词 火箭发动机 启动特性 敏感度 泵入口压力
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某液体火箭发动机用起动器峰值压力时间超差故障研究
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作者 吴昊 唐井爽 +1 位作者 王天宝 王坤 《火工品》 CAS CSCD 北大核心 2024年第2期36-40,共5页
针对某液体火箭发动机用起动器峰值压力时间超差故障,进行了原因分析,提出了改进措施并对其有效性进行了试验验证。结果表明:造成起动器峰值压力时间超差故障的原因为起动器内膜片与端盖间的焊接强度不足,在高温燃气冲击下膜片过早脱落... 针对某液体火箭发动机用起动器峰值压力时间超差故障,进行了原因分析,提出了改进措施并对其有效性进行了试验验证。结果表明:造成起动器峰值压力时间超差故障的原因为起动器内膜片与端盖间的焊接强度不足,在高温燃气冲击下膜片过早脱落、烧蚀,从而导致压力提前泄放。提出将1圈焊接改进为2圈焊接、将点焊改进为连续焊接,焊接后增加气密性及承压性能检测,以及加强削弱槽深度检测等改进措施。验证试验表明上述改进措施可有效避免起动器出现峰值压力时间超差故障。 展开更多
关键词 起动器 液体火箭发动机 峰值压力时间 膜片 焊接强度
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