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作者： Yangzhi Zeng Xiaodong Shao Qinglei Hu Haifeng Hu Hao Pan School of Automation Science and Electrical engineering Beihang University School of Aeronautic Science and engineering Beihang University Beijing Advanced Innovation Center for Big-Data Based Precision Medicine Beihang University Beijing Aerospace Automatic Control Institute China Academy of Launch Vehicle Technology

The fault diagnosis algorithm proposed in this paper firstly establishes the nonlinear thermodynamic model of the thrust chamber of the liquid Rocket engine under normal mode and four common fault modes.Secondly,the particle filter is designed to estimate the output and residuals of the thrust chamber and complete the fault detection task by using the generalized likelihood ratio test method.Thirdly,an extended fault estimation particle filter is established by merging the fault estimation vector into the extended state estimation vector to complete the task of fault estimation.Finally,a fault recognition algorithm is designed according to the fault estimation result to complete the fault recognition task in the case of a single fault,at the same time,the recognition result is used to improve the accuracy of the enhanced particle filter.The proposed method is verified to realize real-time and accurate fault diagnosis of thrust chamber under the influence of uncertain factors such as process and measurement noise.

关键词： Rocket engine thrust chamber fault diagnosis particle filter

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Damage localization effects of the regeneratively-cooled thrust chamber wall in LOX/methane Rocket engines

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Chinese Journal of Aeronautics 2018年第8期31卷 1667-1678页

作者： Jiawen SONG Bing SUN School of Astronautics Beihang University

To investigate the damage localization effects of the thrust chamber wall caused by combustions in LOX/methane Rocket engines, a fluid-structural coupling computational methodology with a multi-channel model is developed to obtain 3-demensioanl thermal and structural responses.Heat and mechanical loads are calculated by a validated finite volume fluid-thermal coupling numerical method considering non-premixed combustion processes of propellants. The methodology is subsequently performed on an LOX/methane thrust chamber under cyclic operation. Results show that the heat loads of the thrust chamber wall are apparently non-uniform in the circumferential direction. There are noticeable disparities between different cooling channels in terms of temperature and strain distributions at the end of the hot run phase, which in turn leads to different temperature ranges, strain ranges, and residual strains during one cycle. With the work cycle proceeding, the circumferential localization effect of the residual strain would be significantly enhanced. A post-processing damage analysis reveals that the low-cycle fatigue damage accumulated in each cycle is almost unchanged, while the quasi static damage accumulated in a considered cycle declines until stabilized after several cycles. The maximum discrepancy of the predicted lives between different cooling channels is about 30%.

关键词： Cyclic plasticity Damage Heat transfer Regenerative cooling Rocket engine Service life Thrust chamber

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维普期刊数据库

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Aircraft engine Design, Second Edition 2nd ed.

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丛书名： AIAA Education Series

2002年

作者： Jack D. Mattingly William H. Heiser David T. Pratt

ISBN: (数字)9781600861444

ISBN: (纸本)9781563475382

Winner of the Summerfield Book Award! The text presents a complete and realistic aircraft engine design experience. From the request for proposal for a new aircraft to the final engine layout, the book provides the concepts and procedures required for the entire process. It is a significantly expanded and modernized version of the best-selling first edition that emphasizes recent developments impacting engine design such as theta break-throttle ratio, life management, controls, and stealth. The key steps of the process are detailed in 10 chapters that encompass aircraft constraint analysis, aircraft mission analysis, engine parametric (design point) analysis, engine performance (off-design) analysis, engine installation drag and sizing, and the design of inlets, fans, compressors, main combustors, turbines, afterburners, and exhaust nozzles.The AEDsys software that accompanies the text provides comprehensive computational support for every design step. The software has been carefully integrated with the text to enhance both the learning process and productivity, and allows effortless transfer between British engineering and SI units. The AEDsys software is furnished on CD-ROM and runs on the Windows operating system. A user’s manual is provided with the software, along with the complete data files used for the Air-to-Air Fighter and Global Range Airlifter design examples of the book.

关键词： Aircraft engines Combustion Chambers Combustors Nozzles Propulsion and Power Rocket engine rocketry

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Flight Vehicle Performance and Aerodynamic Control

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丛书名： AIAA Education Series

2001年

作者： Frederick O. Smetana

ISBN: (数字)9781600861857

ISBN: (纸本)9781563474637

Flight Vehicle Performance and Aerodynamic Control is designed to serve as a text for either an 11-week or a 16-week course at the sophomore level. It explains typical methods used to estimate aircraft performance, the theoretical basis of these methods, and how various parameters derived from the aircraft geometry can be used to estimate the requirements of control surfaces and the aerodynamic forces required to actuate these surfaces. This book includes time-tested computer programs that perform the analyses in a manner that reduces student error and improves result accuracy. Because the source code is given, users with a FORTRAN compiler can modify the program to suit particular needs. The major advantage of the software is that more realistic problems may be treated and the effects of parametric programs are more accurate than calculators. The programs are available as executables for Windows machines as well as in ASCII source code versions that can be readily compiled and then executed on Unix, Linux, and Macintosh machines, and on mainframes.

关键词： Aerodynamic Performance Aerodynamics Aeronautical engineering Aeronautics Aerospace engineering Aerospace Sciences Aircraft Carriers Aircraft Components and Structure Aircraft Conceptual Design Aircraft Design Aircraft Dynamic Modes Aircraft engines Aircraft Instruments Aircraft Operations Aircraft Operations and Technology Aircraft Performance Aircraft Stability and Control Aircraft Stabilizer Aircraft Wing Components Aircraft Wing Design Aircrafts Airfoil Airfoil Nomenclature Airspeed Astrodynamics Astronautics Atmospheric Science Aviation Aviation Authorities and Organizations Aviation Safety Avionics Civil Aviation Combat Aircraft Combustion Chambers Compressors Energy Energy Conversion Energy Economics Energy Forms Energy Forms, Production and Conversion Energy Production Fixed-Wing Aircraft Flight Control Surfaces Flight Dynamics Flight Mechanics Flight Test Flight Training Fluid Dynamics Fluid Flow Properties Fluid Mechanics Fossil Fuels Fuel Injection Fuels Gas Turbine Guidance, Navigation, and Control Systems Heat engines Helicopters Hydraulics Hydrodynamics Ignition Systems Jet Aircraft Liquid Fuels Longitudinal Static Stability Military Airbases Military Aircraft Military Aviation Non-Renewable Energy Petroleum Power Station Propulsion and Power Reciprocating engine Rocket engine rocketry Rotorcrafts Sensors Short Takeoff and Landing Takeoff and Landing Transducers Turbines Turbomachinery Unmanned Aerial Vehicle Wind engineering Wind Tunnels Wind Turbine Wing Configurations Wing Planforms

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Numerical Investigation of Separated Plug Nozzle Flow

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Tsinghua Science and Technology 2000年第4期5卷 391-394页

作者：张扬军诸葛伟林郑孟伟张宝宁李字明王瑞发 Department of Automotive engineering Tsinghua UniversityBeijing 100084China

Modern analysis techniques that provide improved viability have enabled further investigation of plug nozzle Rocket engines as advanced launch vehicle concepts. A plug nozzle for future single-stage-to-orbit vehicles in China has been designed, and the flow field in the plug nozzle has been studied numerically for different ambient pressures. Calculations were performed by solving the Navier-Stokes equations for an ideal gas. Turbulence is modelled using the k-ε turbulence model. The advantages of the plug nozzles are the external expansion, which automatically adapts to external pressure variations, and the short compact design for high expansion ratios. Expansion waves, compression shocks, and the separated base flow dominate the flow structures and affect the plug nozzle Rocket engine performance.[

关键词： plug nozzle Rocket engine separated flo?

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