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6th International Conference on Artificial Intelligence and Security,ICAIS 2020

作者： Wu, Feng Gao, Limin Wu, Xinyun Feng, Xudong Leng, Lintao Li, Yaoyu School of Power and Energy Northwestern Polytechnical University Xi’an710072 China The National Key Laboratory of Aerodynamic Design and Research Xi’an710129 China School of Information and Software Engineering University of Electronic Science and Technology of China Chengdu610054 China Key Laboratory of Science and Technology on Aero-Eigine Altitude Simulation AECC Sichuan Gas Turbine Establishment Chengdu610000 China

ISBN: (纸本)9789811581007

An inlet-engine altitude test facility for flight condition simulation is modeled for the system dynamic performance improvement. The system model equations are solved with an improved Euler integral method. To simulate the interaction between the tested engine and the test bench accurately, a turbojet engine module is introduced in the system model. By modeling and simulation, a linear temperature compensation control algorithm based on the control error is validated for feasibility;controller parameters optimization for cabin static pressure stabilizing is also carried out. In this paper, some issues like temperature transient performance and engine operate impact restraint on cabin static pressure are discussed efficiently and economically. With the characteristics of high efficiency and economy, the modeling and simulation tools are suitable for the optimization of such systems. © Springer Nature Singapore Pte Ltd 2020.

关键词： engines

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Health Assessment of Split Torque Transmission System Using Improved Generative Adversarial Networks

Health Assessment of Split Torque Transmission System Using ...

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TEPEN International Workshop on Fault Diagnostics and Prognostics, TEPEN-IWFDP 2024

作者： Wang, Zhi Hu, Niaoqing Xu, Fujian Yang, Yi Hu, Lei Laboratory of Science and Technology on Integrated Logistics Support NUDT Changsha410073 China Beijing Tangzhi Technology Development Co. LTD Beijing100043 China AECC Hunan Aviation Powerplant Research Institute Zhuzhou412002 China Aero-Engine Vibration Technology in Aeronautical Science Key Laboratory Zhuzhou412002 China Hunan Provincial Key Laboratory of Health Maintenance for Mechanical Equipment Hunan University of Science and Technology Xiangtan411201 China

ISBN: (纸本)9783031694820

Split-torque transmission system (STTS) is a new type of helicopter main rotor transmission. It has the characteristics of light quality, fewer transmission stages, high transmission efficiency, high reliability, low noise and so on. It is of great significance to carry out health detection and assessment for helicopter STTS. In order to solve the lack of fault data and priori knowledges, this paper proposes a framework for STTS anomaly detection and health assessment based on improved generative adversarial networks (IGAN). The framework is validated with fault simulation data of a STTS. © The Author(s), under exclusive license to Springer Nature Switzerland AG 2024.

关键词： Generative adversarial networks

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RUL Prediction of Split Torque Transmission System Using Particle Filtering and Degenerate Model

RUL Prediction of Split Torque Transmission System Using Par...

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TEPEN International Workshop on Fault Diagnostics and Prognostics, TEPEN-IWFDP 2024

作者： Yang, Weixin Wang, Zhi Tang, Xin Hu, Lei Xu, Yuandong AECC Hunan Aviation Powerplant Research Institute Zhuzhou412002 China Aero-Engine Vibration Technology in Aeronautical Science Key Laboratory Zhuzhou412002 China Laboratory of Science and Technology on Integrated Logistics Support NUDT Changsha410073 China Beijing Tangzhi Technology Development Co. LTD. Beijing100043 China Hunan Provincial Key Laboratory of Health Maintenance for Mechanical Equipment Hunan University of Science and Technology Xiangtan411201 China

ISBN: (纸本)9783031694820

The split-torque transmission system (STTS) is considered to be the most likely alternative to a planetary gearbox for helicopter main rotor transmissions. SSTS has obvious advantages in reliability, weight, deceleration ratio, noise, and so on. The remaining useful life (RUL) prediction of STTS is of great significance to support the maintenance of helicopters and prevent them from failure. This paper designs a RUL prediction framework based on particle filtering and degenerate models. The prediction method of the degradation rate tracking particle filter (DRT-PF) eliminates the binding of the fitted model, and estimates and predicts the degradation process of the system by using the statistical law of the degradation rate of the historical data. The prediction framework is validated with simulation signals from a STTS fault model. © The Author(s), under exclusive license to Springer Nature Switzerland AG 2024.

关键词： Epicyclic gears

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Failure analysis of smoke lampblack machine crack

Failure analysis of smoke lampblack machine crack

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2022 International Conference on Metallurgical engineering and Automation technology, MEAT 2022

作者： Kong, Huanping Jiang, Tao Zhao, Kai Liu, Changkui AECC Beijing Institute of Aeronautical Beijing100095 China Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Beijing100095 China Key Lab. of Sci. and Technol. on Aero. Mat. Test. and Evaluation of Aero Engine Corporation of China Beijing100095 China Aviation Key Laboratory of Science and Technology on Materials Testing and Evaluation Beijing100095 China AECC Failure Analysis Center Beijing100095 China

The smoke lampblack machine cracked in use. Through macro and micro morphology observation, energy spectrum detection, metallographic examination and finite element simulation calculation and analysis, the failure nature and reason of the smoke lampblack machine were determined. The results showed that the cracking property was corrosion fatigue, and the cracking of the smoke lampblack machine was caused by the damage of the protective layer in the vibration environment. It was suggested that the surface protection of smoke lampblack machine should be strengthened and the structural design of stress concentration should be improved. © Published under licence by IOP Publishing Ltd.

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μ-Synthesis-based robust L1 adaptive control for aeropropulsion system test facility

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aerospace science and technology 2023年第1期140卷

作者： Liu, Jiashuai Wang, Xi Liu, Xi Zhu, Meiyin Pei, Xitong Dan, Zhihong Zhang, Song School of Energy and Power Engineering Beihang University Beijing100191 China Zhongfa Aviation Institute Beihang University Hangzhou311115 China Research Institute of Aero-Engine Beihang University Beijing100191 China Science and Technology on Altitude Simulation Laboratory AECC Sichuan Gas Turbine Establishment Mianyang621703 China

For aeropropulsion System Test Facility (ASTF) applied in aero-engine performance testing, it is critical to accurately control the pressure and temperature of the airflow to simulate the flight environment. This article presents a μ-synthesis-based robust L1 adaptive control method for ASTF to achieve excellent control performance within a wide working envelope. A μ controller based on a reference model is first designed as the baseline, which can address the coupling effect and guarantee the desired dynamic despite uncertainties. Thereafter, an L1 adaptive compensation term is incorporated to cancel out the large (matched and unmatched) uncertainties, and then recover the baseline performance. This control scheme augments the μ controller to control the ASTF over a wide working envelope and avoids complex gain scheduling design. Furthermore, μ controller can still ensure the robust performance of the closed-loop system even if the adaptive compensation is inadequate. Numerical simulations are performed on high-fidelity nonlinear model to verify the effectiveness of the proposed method. Compared with other state-of-the-art techniques, the robust L1 adaptive control possesses better performance and robustness. © 2023 Elsevier Masson SAS

关键词： Controllers

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Arrangement of Signal Measuring Points of Planetary Gear Transmission Based on Dynamics simulation

Arrangement of Signal Measuring Points of Planetary Gear Tra...

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Prognostics and System Health Management Conference (PHM-Qingdao)

作者： Weixin Yang Feichun Liu Tang Xin Rupeng Zhu AECC Hunan Aviation Powerplant Research Institute Zhuzhou China Aero-engine vibration technology in Aeronautical Science Key Laboratory Zhuzhou China Nanjing University of Aeronautics and Astronautics Nanjing China

ISBN: (数字)9798350354010

ISBN: (纸本)9798350354027

Planetary gear box has complex structure and high failure rate. How to effectively reveal the fault characteristics of the key components in the planetary gear box and find and solve the fault in time is the focus and difficulty of current research. This paper takes the planetary gear meshing system as the research object, combines multi-body dynamics and finite element analysis, considers the transmission path of vibration signals, establishes a rigid-flexible coupling model, analyzes the characteristics and causes of the vibration signals obtained by simulation, seeks the best measuring point position of the vibration acceleration sensor, and verifies the effectiveness of the simulation model through the measured signals.

关键词： Vibrations Analytical models Gears Current measurement Vibration measurement Position measurement Extraterrestrial measurements Finite element analysis Reliability Prognostics and health management

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Fractional Order Modeling of Dynamic Response for Shielded Total Temperature Probes Considering Unsteady aerothermal Processes

SSRN

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SSRN 2024年

作者： Li, Zhen Zhang, Weihao He, Tingyu Yang, Weiping School of Energy and Power Engineering Beihang University Beijing100191 China National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics Beijing100191 China Hunan Aviation Powerplant Research Institute Zhuzhou412002 China

In this paper, unsteady conjugate heat transfer simulation with radiation model was employed to analyze the gas flow, heat transfer characteristics inside and outside the typical shielded total temperature probe. It was found that the calculation formula of time constant, which represents the dynamic response performance, is not applicable to the structurally complex shielded probe and the error in the evaluation exceeds 40%. Through careful evaluation of dynamic heat transfer paths, one-dimensional heat transfer equations of the shield and the junction are constructed to overcome the shortcomings of traditional zero-dimensional lumped parameter method. Considering the unsteady aerothermal processes in dynamic response, fractional order model has an advantage over first order system for junction heat conduction in avoiding the infinite velocity of heat waves and abrupt change of temperature. Moreover, for shield heat conduction, it’s necessary to employ non-Fourier heat conduction model to describe finite heat diffusion. Combined automatic control system with numerical solution, the new model reduces time constant error of the shielded total temperature probe by approximately 50% compared to the lumped parameter method. The steady state error after stabilization reaches an agreement with steady state error model, demonstrating good effect. © 2024, The Authors. All rights reserved.

关键词： Dynamic response

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A Multi-Feature Fusion Method for Fault Diagnosis with Applications in Tail Paddle Lever Bearing

A Multi-Feature Fusion Method for Fault Diagnosis with Appli...

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Prognostics and System Health Management Conference (PHM-Qingdao)

作者： Zhou Long Hao Gan Weixin Yang Kai Li Xiuwen Li AECC Hunan Aviation Power Plant Research Institute Aero-engine vibration technology in Aeronautical Science Key Laboratory Zhuzhou China TangZhi Science & Technology Hunan Development Co. Ltd. Changsha China BeiJing TangZhi Technology Development Co. LTD. Beijing China

ISBN: (数字)9798350354010

ISBN: (纸本)9798350354027

Aiming at the problems such as difficult monitoring and inaccurate state evaluation of helicopter tail rotor rod bearing. In this paper, temperature and vibration sensors are used to collect the temperature and vibration signals of bearings. Then the collected signal is constructed by means of noise reduction, feature extraction and feature fusion. And the characteristic data set is used as the input of fault diagnosis model after state index evaluation, health index generation and dimensionality reduction. Last, the improved gravity search algorithm (GGSA) is used to optimize the parameters of support vector machine (SVM) diagnosis model to form GGSA-SVM model for bearing fault diagnosis. In the simulation test, compared with the previous method, the number of iterations of the model is reduced by 21 times, the fitness is reduced to 0.4%, and the accuracy of bearing fault diagnosis is increased by 4.4% to 97.9 % . The experimental results show that the model can be used for bearing fault diagnosis better.

关键词： Fault diagnosis Temperature sensors Vibrations Support vector machines Temperature Tail Sensor phenomena and characterization Feature extraction Vectors Indexes

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