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Design and simulation of aircraft altitude control based on RBFPID controller

Design and simulation of aircraft altitude control based on ...

引用

2024 CSAA/IET International Conference on aircraft Utility systems, AUS 2024

作者： Huang, Min Hu, Xiaowei State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai China COMAC Shanghai Aircraft Design and Research Insti Shanghai China

Altitude control is crucial for flight. In cruise flight, it is important to avoid longitudinal movement of the aircraft. Maintaining a fixed favorable altitude can improve the economy of the aircraft and increase its range. This can be achieved by using a longitudinal dynamics model of the aircraft and the root trajectory method, which is constructed based on the pitch angle and pitch angle rate feedback of the stabilizing and damping controllers. To enhance the control performance and robustness of altitude control, it is suggested to replace the traditional altitude P1D controller with the RBFPID(Radical Basis Function Proportion Integral Differential) controller. The results indicate that the use of the RBFPID controller is beneficial for improving the control performance of the altitude modes . © The Institution of Engineering & technology 2024.

关键词： flight paths

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Influence of different weight reduction configurations of thermal/acoustic insulation blankets on the transmission loss of aircraft panel 4

Influence of different weight reduction configurations of th...

引用

2024 4th International Conference on Mechatronics technology and Aerospace Engineering, ICMTAE 2024

作者： Zhao, Yi Dai, Zheng Meng, Lingda State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai200000 China COMAC Shanghai Aircraft Design & Research Institute Shanghai200000 China

Thermal/acoustic insulation blankets are the main material for noise reduction of aircraft panel structures. Due to the lack of design experience of domestic civil aircraft manufacturers, it is difficult to carry out the weight reduction design of the thermal/acoustic insulation blankets based on meeting the cabin noise requirements. Therefore, the sound insulation performances of the metal fuselage panel with different weight reduction configurations of the thermal/acoustic insulation blankets are tested by using the sound intensity method under the condition of an anechoic-reverberation chamber. Based on the analysis of the experimental results, the influence laws of different weight reduction configurations of the thermal/acoustic insulation blankets on the sound insulation performance of the composite panel are summarized, which have important guiding significance for the weight reduction design of the thermal insulation and sound insulation layers for civil aircraft manufacturers. © 2025 Institute of Physics Publishing. All rights reserved.

关键词： Sound insulation

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Research on pipeline stress test method of civil aircraft hydraulic system 2

Research on pipeline stress test method of civil aircraft hy...

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2023 2nd International Conference on Mechanical, Aerospace technology and Materials Application, MATMA 2023

作者： Ni, Junfei Qi, Xiaoyan Shanghai Aircraft Design & Research Institute Shanghai200120 China State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai200120 China

The hydraulic system is an important component of the aircraft, whose performance status directly affects the aircraft's flight safety, and aircraft hydraulic system piping is the main component of the hydraulic system. In the development process, civil aircraft must be tested and analyzed on the hydraulic system piping vibration and stress. This paper takes the hydraulic system pipeline of civil aircraft as the research object, carries out the research of pipeline stress test method, and provides the stress test method and reliable test data for verifying whether the design of the hydraulic system pipeline is reasonable. © Published under licence by IOP Publishing Ltd.

关键词： Pipelines

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NUMERICAL STUDY ON NACELLE EXHAUST PERFORMANCE BY AXISYMMETRIC 2D APPROACH WITH THE CONSIDERATION OF PYLON BOAT TAIL EFFECTS

NUMERICAL STUDY ON NACELLE EXHAUST PERFORMANCE BY AXISYMMETR...

引用

2024 CSAA/IET International Conference on aircraft Utility systems, AUS 2024

作者： Zhu, Jianjun Jin, Jiangchen He, Bihai Yan, Yan Zhao, Qiang Liu, Hao Jiang, Jintao COMAC Shanghai Aircraft Design and Research Institute Shanghai China State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai200126 China

A method to predict nacelle exhaust performance in axisymmetric 2D frame with the consideration of pylon boat tail effects is developed. Three cases of different nacelle configurations are numerical studied based on the method developed in present work as well as the traditional 3D simulation. The results show the maximum relative differences between the exhaust performance coefficient results is less than 1%. The method developed in present work is proved to be accurate enough for engineering apply, especially for exhaust aeroline design and optimization during exhaust preliminary design states. © The Institution of Engineering & technology 2024.

关键词： Boats

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RESEARCH ON DESIGN AND VERIFICATION METHODS OF ELECTRIC PUMP SHOCK MOUNT IN CIVIL aircraft HYDRAULIC SYSTEM

RESEARCH ON DESIGN AND VERIFICATION METHODS OF ELECTRIC PUMP...

引用

2024 CSAA/IET International Conference on aircraft Utility systems, AUS 2024

作者： Wu, Tonggang Li, Tao Duan, Boyang COMAC Shanghai Aircraft Design & Research Institute Shanghai China State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai200126 China

In this paper, the electric pump shock mount in civil aircraft hydraulic system is taken as the research object, and the design requirements, function realization and verification methods of the shock mount were comprehensively analyzed. At the same time, typical electric pump shock mounts were taken as an example to research and verify the design and verification methods. The results show that the shock mount has a good damping effect and can basically meet the damping requirements. The design and verification methods of the shock mount is reasonable and feasible, and can guide the design and verification of related products. © The Institution of Engineering & technology 2024.

关键词： aircraft hydraulic systems

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The influence of lay-up lap size on composite material laminate repair 10

The influence of lay-up lap size on composite material lamin...

引用

10th International Conference on Mechanical Engineering, Materials, and Automation technology, MMEAT 2024

作者： Wu, Shuang State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai200000 China Shanghai Aircraft Design and Research Institute Shanghai200000 China

ISBN: (纸本)9781510682634

Damage is inevitable during the operation process of civil aircraft, composite material repair technology has been widely used in civil *** repair parameters have an important effect on the reliability of the composite materials. Thus, in this paper, the laminates have been mending by different argument, and the influences of the lay-up lap size on failure strength, toughness, strain and measurement uncertainty on laminates has been investigated. The results shown that, with increased lay-up size, samples’ failure strength and measurement uncertainty was increased, toughness was decreased, the strain change tend of all samples was non repair area> edge of repair area> center of the repair area. © 2024 SPIE.

关键词： Laminated composites

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Experimental study on cloud parameters in an open icing wind tunnel for aircraft ground icing tests 3

Experimental study on cloud parameters in an open icing wind...

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2024 3rd International Conference on Aerospace, Aerodynamics and Mechatronics Engineering, AAME 2024

作者： Zhou, Qiongyao Dong, Mingsai Shanghai Aircraft Design & Research Institute Shanghai201210 China State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai201210 China

Supporting ground icing test of aircraft air intake system, this article uses a seasonal open icing wind tunnel to provide an artificial freezing fog environment. In order to verify that the freezing fog environment created by the seasonal open icing wind tunnel meets the test requirements, the impact of compressed air-water pressure ratio on MVD and the impact of water supply flow rate on LWC were studied in this article. Additionally, an ice thickness evaluation method based on an ice grid to test the uniformity of LWC within a range of 1 m×1 m was conducted. The research results show that: 1) When the compressed-water pressure ratio is 2.6±0.26 (M±SD), the MVD meets the test requirements;2) LWC and water supply flow rate have a good linear relationship, and LWC increases linearly with the increase of water supply flow rate;3) The uniformity of LWC within a range of 1 m×1 m can meet the requirements of ±20%, and the consistency between the two tests is good. © Published under licence by IOP Publishing Ltd.

关键词： Wind tunnels

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DESIGN AND VALIDATION OF EXPERIMENTAL TEST PLATFORM FOR FIELD-CIRCUIT COUPLING WIDE-FREQUENCY CHARACTERISTICS MODEL OF POWER TRANSFORMER

DESIGN AND VALIDATION OF EXPERIMENTAL TEST PLATFORM FOR FIEL...

引用

2024 CSAA/IET International Conference on aircraft Utility systems, AUS 2024

作者： Xue, Mizi Yang, Gang Shanghai Aircraft Design and Research Institute Shanghai201210 China State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai200126 China

This paper considers the nonlinear core material, the weak magnetic effect of core eddy current and the non-measured coil load operation under the condition of wide-frequency transformer. A field-circuit coupling model suitable for the calculation of inductance parameters in wide-frequency applications such as transformer lightning impulse wave process analysis and frequency-dependent response analysis is *** order to verify the correctness of the electromagnetic coupling between the coil units in the equivalent model, a test model of electromagnetic parameters was *** influence of the magnetic conductivity of the core on the wide-frequency inductance parameters is analyzed under the different *** synthetic inductance parameters were measured and compared with the calculated results to verify the validity of the proposed model. © The Institution of Engineering & technology 2024.

关键词： Inductance

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Experimental research on blowing-rain intensity and uniformity of rain tunnel for aircraft rain removal testing 2

Experimental research on blowing-rain intensity and uniformi...

引用

2023 2nd International Conference on Aerospace and Control Engineering, ICoACE 2023

作者： Liu, Qianqian Zhao, Yi Liu, Caixia Shanghai Aircraft Design & Research Institute Shanghai201210 China State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai201210 China

The objective of the present study is to characterize a rain tunnel that is used for performance testing of aircraft windshield rain removal systems. The rain tunnel in the present study is an open jet wind tunnel with six full cone pressure swirl nozzles arranged at its outlet. Experiments are conducted with water at room temperature as the working medium. The influence of total water supply flow rate and air velocity on the blowing-rain intensity and uniformity is studied. The total water supply flow rate varies from 0.57 m3/h to 1.03 m3/h, while the pressure at the inlet of the nozzle ranges from 1.44 bar to 6.52 bar. The air velocity of 30 m/s, 40 m/s, and 50 m/s is studied. A special test setup has been designed for measurements of the blowing-rain intensity and uniformity. Experimental results indicate that the blowing-rain intensity and uniformity both increase with the increasing total water supply flow rate and decrease with the increasing air velocity. © Published under licence by IOP Publishing Ltd.

关键词： Water supply

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Numerical research on rain field intensity and uniformity of a high-velocity rain wind tunnel 3

Numerical research on rain field intensity and uniformity of...

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2024 3rd International Conference on Aerospace, Aerodynamics and Mechatronics Engineering, AAME 2024

作者： Liu, Qianqian Liu, Huayuan Zhou, Qiongyao Dong, Mingsai Shanghai Aircraft Design & Research Institute Shanghai201210 China State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai201210 China

Rain field intensity and uniformity are essential to high-velocity rain wind tunnels. This paper investigated the rain field of a high-velocity rain wind tunnel via a two-way coupled Eulerian-Lagrangian approach. The simulation results show that the spray diffusion degree is mainly affected by air velocity, followed by the initial particle velocity. The intensity of the rain field increases with the growth of the nozzle flow rate and the increase of the air velocity, while the uniformity of the rain field is mainly affected by the air velocity. Under the same air velocity and nozzle flow rate, the farther away from the outlet, the lower the rain field intensity, while the uniformity of the rain field displays the tendency to rise initially and then decline. © Published under licence by IOP Publishing Ltd.

关键词： Rain

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