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Cockpit Crew Task Analysis for Civil aircraft Based on Image Recognition

Cockpit Crew Task Analysis for Civil Aircraft Based on Image...

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Mechanical Engineering and Robotics Research (ICMERR), International Conference on

作者： Jun Jiang Xinyang Zhu Yiyuan Zheng State Key Laboratory of Airline Integration Technology and Flight Simulation Shanghai Cockpit integration Shanghai Aircraft Design and Research Institute Shanghai China Human Factors Shanghai Aircraft Airworthiness Certification Center Shanghai China

ISBN: (数字)9798331509262

ISBN: (纸本)9798331509279

Whether the cockpit crew task design of civil aircraft is accurate and reasonable directly affects the preparation y requirements of civil aircraft crew and flight safety. Civil aircraft cockpit minimum flight crew provisions is also an important provision in the process of airworthiness certification of new models, at this stage, the airworthiness certification of this provision is mainly analysed through the simulator test and test flight test through the pilot's subjective evaluation, there is a strong subjectivity, not able to objectively evaluate the workload of the crew, which has brought a lot of challenges to the airworthiness certification. This paper proposes a method based on image recognition to carry out the minimum crew task analysis in the cockpit of a civil aircraft. According to the route operation scenario of a civil aircraft, we carry out the simulation test of the man-in-the-loop, use the camera to track and record the spatial movement trajectory of the pilot's hand, judge the crew's operation task in the cockpit by identifying the crew's gesture, and make use of the cockpit's interface for displaying some information to carry out the analysis of the crew's task in the cockpit of a civil aircraft. The method helps to improve the accuracy and efficiency of the monitoring of crew tasks in the cockpit of civil aircraft, and provides a basis for optimising crew resource management and flight safety.

关键词： Image recognition Accuracy Tracking Safety Trajectory aircraft Task analysis aircraft propulsion Certification Robots

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Research on Component Level PHM technology for Electromechanical systems Based on Machine Learning

Research on Component Level PHM Technology for Electromechan...

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IEEE International Conference on Civil Aviation Safety and Information technology (ICCASIT)

作者： Junyi Zhai Zhengqiang Li Bin Chen State Key Laboratory of Airline Integration Technology and Flight-Simulation Shanghai Aircraft Design and Research Institute Shanghai China

Prognostics and Health Management (PHM) technology is a maintenance support method that utilizes condition-based maintenance. It encompasses fault diagnosis, fault prediction, and health management, ultimately leading to reduced equipment support costs. Currently, data-driven PHM technology is a popular research area, with a focus on the application of machine learning methods. This article utilizes machine learning techniques to study fault diagnosis and residual service life prediction. Specifically, it investigates machine learning-based fault diagnosis methods by analyzing and implementing a BP neural network model for fault diagnosis of hydraulic actuators. Additionally, it compares the differences between standard Gradient descent and Adaptive learning rate Gradient descent. The article also explores the SVM method and its parameter optimization, proposing a fault diagnosis method based on the GA-SVM algorithm and demonstrating its effectiveness. The primary focus is on developing a similarity-based framework for residual service life prediction. This involves elaborating on three similarity measure functions and proposing a health factor construction method based on PCA and BP neural network for multi-source statistical data.

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simulation research for flap skew on a certain type of aircraft

Simulation research for flap skew on a certain type of aircr...

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CSAA/IET International Conference on aircraft Utility systems (AUS 2024)

作者： Xianyu Wang State Key Laboratory of Airliner Integration Technology and Flight Simulation COMAC Shanghai Aircraft Design and Research Institute Shanghai People's Republic of China

ISBN: (数字)9781837242108

This paper describes the different kinds of flap skew malfunctions and principles of flap skew sensor monitoring on an aircraft. Taking a certain type of aircraft as an example, a flap system model is established by Simulink platform. Based on this model, the skew malfunctions can be simulated. The simulation results show that the established flap system model is effective, which lays a foundation for further research.

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Research on failure mode analysis and redundant backup design of EMA

Research on failure mode analysis and redundant backup desig...

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CSAA/IET International Conference on aircraft Utility systems (AUS 2024)

作者： Xiaowei Hu Min Huang State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai People's Republic of China

ISBN: (数字)9781837242108

The article designs an EMA functional platform that allows for dual inputs, studies the failure modes and probabilities of EMA, and then uses FHA method to calculate the likelihood of EMA functional loss and abnormality. Finally, failure mode experiments were conducted to analyze relevant data, and it was found that redundant backup design can reduce the impact of system failures on performance, improve system availability and safety.

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Test research for flap skew on iron bird on a certain type of aircraft

Test research for flap skew on iron bird on a certain type o...

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CSAA/IET International Conference on aircraft Utility systems (AUS 2024)

作者： Xianyu Wang State Key Laboratory of Airliner Integration Technology and Flight Simulation COMAC Shanghai Aircraft Design and Research Institute Shanghai People's Republic of China

ISBN: (数字)9781837242108

This paper focuses on the flap skew test under the ground-based laboratory environment on the iron bird, taking a certain type of aircraft as an example to introduce the environment and skew malfunction principles about the flap skew test on aircraft. The mechanical devices used to simulate flap skew malfunction and recover flap skew malfunction are designed and applied in the ground simulation test of a certain type of aircraft. According to the results, the designed mechanism can be proved to be used normally and can carry out the flap skew test successfully.

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The decoupling and simulation analysis of the six-force sensors structure for aircraft wheel in ground dynamic testing

The decoupling and simulation analysis of the six-force sens...

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CSAA/IET International Conference on aircraft Utility systems (AUS 2024)

作者： Bo Jiang Tao Li YiFan Shao Shanghai Aircraft Design and Research Institute of COMAC State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai People's Republic of China

ISBN: (数字)9781837242108

To meet the needs of aircraft ground dynamics testing, a six-force sensors decoupling structure is designed and simulated for verification. The core unit is a six-force sensors with an elastic body structure composed of several strain beams. The six-force sensor adopts an eight-beam design, with four strain gauges attached to each beam. Through Abaqus simulation analysis, the structural design of the strain gauges enables partial decoupling of the six-forces. The undecoupled forces of the six-force are decoupled by constraining the rotational freedom of the sensor. By designing the structure of the six-force sensor and constraining its rotational freedom, the decoupling of each output channel can be achieved.

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Design and simulation of aircraft altitude control based on RBFPID controller

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

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CSAA/IET International Conference on aircraft Utility systems (AUS 2024)

作者： Min Huang Xiaowei Hu State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai People's Republic of China

ISBN: (数字)9781837242108

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 PID 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.

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Research on Development of simulation Models Based on Civil aircraft Engineering Simulator

Research on Development of Simulation Models Based on Civil ...

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International Conference on Machine Learning, Big Data and Business Intelligence (MLBDBI)

作者： Shuai Huang State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai China

The engineering simulator is one of the most important test equipments in the development of civil aircraft. simulation models are the core component of engineering simulator. Based on the engineering simulator, the development process and idea of the simulation models are proposed, including the requirements capture, model development, model verification and validation. For the simulation model, the ultimate goal is to achieve its fidelity. In order to meet the needs of engineering simulators for airworthiness compliance testing (MOC8 test), the requirements, airworthiness compliance assessment and model configuration management are analyzed and explained in this paper, which is based on the development experience of a certain type of aircraft.

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Study on icing environment of typical civil aircraft boarding gate

Study on icing environment of typical civil aircraft boardin...

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CSAA/IET International Conference on aircraft Utility systems (AUS 2024)

作者： Yifan Zhu Xudong Qiu State Key Laboratory of Airliner Integration Technology and Flight Simulation COMAC Shanghai Aircraft Design and Research Institute Shanghai 200126 People's Republic of China

ISBN: (数字)9781837242108

In order to verify the compliance requirements of typical civil aircraft cabin doors to airworthiness provisions in cold weather, a high and low temperature experimental cabin was built with the boarding door as the research object. The freezing opening test of the cabin door's inner handle and outer handle was carried out by means of rain in a low temperature environment. It is found that the ice surface faults are orderly, there is no stuck and no noise during the test, the mechanism is intact, and the hatch door can be closed normally. The opening time of the inner handle after icing is 6.17 s, which meets the requirements of the airworthiness clause. The test results can provide a basis for the design index of the model gate under the icy environment.

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Based on the scenario analysis: the research of auxiliary power unit (APU) system requirement demonstration on high plateaus

Based on the scenario analysis: the research of auxiliary po...

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CSAA/IET International Conference on aircraft Utility systems (AUS 2024)

作者： Yuchen Sun State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai 200126 People's Republic of China

ISBN: (数字)9781837242108

When capturing the design requirements for civil aircraft, it is necessary to analyze them according to the requirements of ARP 4754A, based on the forward design principle of scenario combing. In this paper, the requirements for APU utilization are captured from the actual operation scenarios of civil aircraft at high plateaus in China[1]. For example, the utilization of APU needs to take into account the impact of plateau environments on its performance, such the altitude to start up on the ground and the altitude to provide bleed air,etc.[2-3] Different from plain aircraft, when operating at high plateau, APU s are usually used in takeoff and approaching phases to supplement engine thrust to obtain the performance *** article provides scenarios for using the APU during normal aircraft operation scenario and system failure scenario, and demonstrates the APU ground start height and air supply and bleed air height indicators based on the characteristics of high-altitude airports in China.

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