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2024 International Conference on Guidance, Navigation and Control

作者： Sima, Jun Yue, Fan Zhao, Zhen Shanghai Aircraft Design & Res Inst Shanghai 201210 Peoples R China

ISBN: (纸本)9789819622702;9789819622689;9789819622672

Surface oscillation failure is a specific failure mode in FBW system, and excessive surface oscillation may cause serious safety impact on aircraft controllability and structural loads. The failure sources resulted in surface oscillation are diverse, while oscillation failure from flight parameter sensors used in closed-loop control being the main causes. This paper elaborates on the failure analysis and monitors design for flight parameter oscillation in flight control system, and proposes a verification method and testing setup to validate and verify the safety performance of oscillation monitors.

关键词： FBW flight parameters Oscillation Monitor Verification

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Construction method of multi-stage degradation threshold for shipborne helicopter based on flight parameters

Construction method of multi-stage degradation threshold for...

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Prognostics and Health Management Conference (PHM-2022 London)

作者： Liu, Changrong AVIC Shanghai Aero Measurement Controlling Res In Aviat Key Lab Sci & Technol Fault Diag & Hlth Man Shanghai Peoples R China

ISBN: (纸本)9781665479547

Safety is an important indicator to measure the performance of ship-borne helicopters, and the state monitoring of shipborne helicopters is the main way to ensure the safety of shipborne helicopters. As the flight time of the shipborne helicopter increases, many components will gradually degrade, and corresponding threshold need to be set to ensure the normal operation the shipborne helicopter. The commonly used fixed threshold method will cause false alarms due to different flight states, so it is necessary to dynamically construct the state thresholds under different flight states. Firstly, the empirical mode decomposition is used to denoise the signal, and then the extracted monitoring features of the shipborne helicopter are classified according to the stability in multiple flight states. A fixed threshold is setted by statistical characteristics for stable features. The dynamic feature selects flight parameters that are highly correlated with feature changes as indicators, and uses principal component analysis to fuse them to construct a dynamic threshold *** proposed method is verified by actual flight data, and the result shows that the dynamic threshold index can effectively reduce the false alarm rate.

关键词： shipborne helicopter dynamic threshold health management flight parameters

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Dynamic Determining Method of Infrared Radiation Characteristics based on flight parameters

Dynamic Determining Method of Infrared Radiation Characteris...

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Applied Optics and Photonics China (AOPC) Conference - Optical Sensing and Imaging Technology

作者： Yu, Chenfei Zheng, Guofeng Cheng, Xiaoliang Sci & Technol Electroopt Control Lab Luoyang 471000 Peoples R China Luoyang Inst Electroopt Equipment Luoyang 471000 Peoples R China

ISBN: (纸本)9781510639560

Based on basic principle of infrared radiation, aiming at infrared radiation characteristics of aircraft in different altitude, speed and attitude, a dynamic measurement method of infrared radiation characteristics based on flight parameters is proposed, and the infrared radiation intensity of a typical aircraft is simulated and analyzed. A typical aircraft is simulated and analyzed. These conclusions provide a basis for stealth aircraft design and the IR guidance air-defense weapon system design and application.

关键词： Stealth aircraft Infrared radiation flight parameters Air defense system

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Aircraft reliability assessment for an individual mission based on recordable flight parameters

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QUALITY AND RELIABILITY ENGINEERING INTERNATIONAL 2018年第8期34卷 1605-1614页

作者： Ma, Xiaobing Wang, Zhihua Guan, Tianyu Ma, Tao Beihang Univ Sch Reliabil & Syst Engn Beijing Peoples R China Beihang Univ Sch Aeronaut Sci & Engn Beijing 100191 Peoples R China China Flight Test Estab Reliabil Res Ctr Xian Shanxi Peoples R China

Reliability of aircraft varies with different missions, because load conditions are always diverse. In limited sample size circumstances, convention aircraft mission reliability assessment method can only give an average result for a kind of mission. Motivated by the practical need of reliability assessment for an individual mission, this paper constructs a novel method, which can assess reliability for a specific mission based on flight parameters. The mission reliability model can be established according to the relationship between flight loads, flight parameters, and reliability via adopting fault data and flight parameters synthetically. Statistical inference of aircraft failure rate is proposed, and then, the mission reliability can be assessed according to the fault data of the focused aircraft. It is worth noticing that the proposed method can also assess the reliability for a mission category via conducting an average calculation across all individual missions belonging to the target mission category. An illustrative example shows that the proposed method not only can give reliability assessments with a same precision with existing approaches for a specific mission category but also can reasonably assess the reliability regarding an individual mission.

关键词： aircraft an individual mission fault data flight parameters mission reliability assessment

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Skydiver flight parameters Recorder 15

Skydiver Flight Parameters Recorder

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15th International Scientific Conference on Optoelectronic and Electronic Sensors (COE)

作者： Pachwicewicz, Marek Weremczuk, Jerzy Rzewuski, Stanislaw Warsaw Univ Technol Fac Elect & Informat Technol Inst Elect Syst Warsaw Poland RS Technol Sp Zoo Warsaw Poland

ISBN: (纸本)9781538641071

This paper presents skydiver flight parameters recorder named SKYBOX and data which can be acquired by it. It is unique device which can measure not only height profile and GPS track but body orientation also. The device can collect not only height and geographic position but also inertial information - accelerations and rotational speeds. Basic information about metrological specification of the device are presented. Additionally, sample data like height profile, GPS track and movement parameters are shown. It is shown that individual phases of the skydiver flight can be discriminated.

关键词： skydiver IMU flight parameters skydiving parachuting flight recorder

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Research on flight parameters based on statistical theory

Research on flight parameters based on statistical theory

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

作者： Xinbin Zhao Xiuting Zhou Xiaoyue Zhang China Academy of Civil Aviation Science and Technology Aviation Safety Institute Beijing China

ISBN: (纸本)9781728125992

Safety is the lifeline of the civil aviation industry, and safety is the foundation for ensuring the operation of civil aviation. flight Operational Quality Assurance (FOQA) is one of the effective means to implement safety management, it mainly aims to detect the flight risk by analyzing the flight parameters. Statistical analysis methods are very important for FOQA. How to analyze the flight parameters reasonably is a hot research topic. Based on the basic theory of statistics, this paper presents theory and methods for processing normal data and non-normal data, and introduces some the risk models and algorithms for early warning.

关键词： FOQA Risk flight parameters Statistical theory flight parameter Statistical analysis safety aerospace industry

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Development of virtual sensors to estimate critical aircraft flight parameters

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IFAC-PapersOnLine 2017年第1期50卷 14174-14179页

作者： Alcalay, G. Seren, C. Hardier, G. Delporte, M. Goupil, P. AIRBUS Operations SAS Toulouse France ONERA The French Aerospace Lab Toulouse France

This paper addresses the estimation of flight parameters in nominal and degraded flight conditions when one or several specific sensors become faulty. Anticipating more stringent regulations for future aircraft, reconstructing through time the missing signals is a challenging objective for flight Control Systems, especially because some of them are essential for control purposes. To this end, this paper proposes a solution based on virtual sensors which makes use of an Adaptive Extended Kalman Filter. This allows the longitudinal flight parameters of a civil aircraft to be estimated on-line before and after the occurrence of one or several failures. This solution offers interesting monitoring capabilities including the detection of common mode failures (i.e., simultaneous failures occurring on redundant sensors), and also provides the capability of correcting a wrong aircraft weight in addition to the sensors monitoring. Typical results using real flight test data are shown to evaluate the performances of the approach in terms of detection and estimation capabilities. © 2017

关键词： flight control systems Aircraft detection Fault detection Kalman filters Parameter estimation State estimation Adaptive extended Kalman filters Common mode failures Detection and estimation flight conditions flight parameters Monitoring capabilities Stringent regulations Virtual sensor

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Algorithms of Aircraft flight parameters Determination via the Visual Data 14

Algorithms of Aircraft Flight Parameters Determination via t...

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14th International Conference on Informatics in Control, Automation and Robotics (ICINCO)

作者： Sokolov, Sergey Beklemichev, Nikolay Boguslavskiy, Andrey RAS Keldysh Inst Appl Math Miusskaya Sq 4 Moscow Russia

ISBN: (纸本)9789897583049

This paper provides the information about the possibility of independent information channel development for determination of altitude, list and pitch of aircrafts based on the visual data analysis. All stages of solving the information support problem for aircraft control system based on the collection and processing of the visual data are considered here. This paper provides the information about the development of mathematical model, the calibration of visual fields and the provision of stereoscopic calculations accuracy. The mathematical support of the computer vision system, consisting of two video cameras and computing unit installed on the aircraft, is also described here. The proposed algorithms are implemented for the system model as a part of the flying laboratory. The results of the experiments carried out for this model are also presented here. The results allow drawing the conclusion about the possibility of successful solution of the problem. Possible ways for further system improvement are also presented in this paper.

关键词： Aircraft flight parameters Computer Vision System Altitude Pitch List Unmanned Aerial Vehicle

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Optimal flight parameters of unmanned helicopter for tea plantation frost protection

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International Journal of Agricultural and Biological Engineering 2015年第5期8卷 50-57页

作者： Hu Yongguang Liu Shengzhong Wu Wenye Wang Jizhang Shen Jianwen School of Agricultural Equipment Engineering Jiangsu UniversityZhenjiang 212013China Electronic Application Laboratory of Wuxi Hanhe Unmanned Helicopters Wuxi 214135China

To determine proper flight parameters of an unmanned helicopter for tea plantation frost protection,field experiments were conducted to study the impact of flight height,speed and interval on airflow disturbance and temperature rise around tea canopies based on the analysis and simulation of frost protection with a certain *** relationship between temperature rise after flight and the above flight parameters was established through a regression orthogonal experiment,based on which the optimal combination of flight parameters was obtained through the single-factor golden section *** results showed that wind speed around tea canopies decreased with the increase of flight height when flight speed was *** was a multivariate linear relationship between temperature rise and flight parameters,and the sequence of flight parameters’influence on frost protection effect was flight interval,flight height,flight *** optimal combination of flight parameters were flight height of 4.0 m,flight speed of 6.0 m/s and flight interval of 20 *** the flight with the above parameters air temperature around tea canopies increased 1.6℃ when background thermal inversion strength was 3.8℃.

关键词： thermal inversion frost protection unmanned helicopter flight parameters orthogonal experiment single-factor golden section method tea plants

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Improving primate detection using thermal infrared imaging: availability and observer errors in drone surveys of mixed tropical forests

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INTERNATIONAL JOURNAL OF REMOTE SENSING 2025年第11期46卷 4345-4373页

作者： Reinegger, Raphael D. Bissessur, Prishnee Meereechpersad, Ishwardev Bhanda, Geetika Gazagne, Eva Jones, Gareth Univ Bristol Sch Biol Sci Life Sci Bldg24 Tyndall Ave Bristol BS8 1TQ England Univ Mauritius Fac Sci Dept Biosci & Ocean Studies Trop Isl Biodivers Ecol & Conservat Pole Res Le Reduit Mauritius Minist Agro Ind & Food Secur Natl Pk & Conservat Serv LeReduit Lereduit Mauritius Univ Liege Unit Res SPHERES Liege Belgium

Drones with thermal infrared (TIR) cameras are increasingly used to survey terrestrial endotherms, including primates, but the relative lack of standardized protocols hampers their effectiveness. Detection errors, both observer (animal is available for detection but missed/misidentified by the observer) and availability errors (animal is present but unavailable for detection), vary across species, habitats and flight parameters, and may be exacerbated by anti-predator responses. We evaluated the suitability of drone-mounted TIR cameras in surveys of long-tailed macaques (Macaca fascicularis) by measuring detection errors for different flight altitudes (70, 60, 50 and 40 m above ground level [AGL]) and camera angles (45 degrees and 90 degrees) in two secondary forest habitats in Mauritius, characterized by open canopy with low thermal contrast and closed canopy with high thermal contrast. First, we determined the true size of three habituated macaque groups with full-day follows, and assessed their response to the drone. Next, we measured availability error (detection rate) in TIR videos after correcting for observer error (misidentification rate) using corresponding red-green-blue (RGB) videos. Finally, we assessed whether adjusting counts with mean detection rates improved group size estimates for different flight parameter combinations. Both error types were lowest for morning flights at 50 and 60 m AGL (40 and 50 m above canopy respectively) and with 45 degrees camera angle in high thermal contrast conditions. The higher detection rates at 50 and 60 m compared to 40 m resulted from milder anti-predator behaviours (increased vigilance instead of dispersal). In secondary forest habitats with few dominant canopy species (e.g. Eucalyptus, Litsea and Pinus spp.), and for primate species with behavioural ecology comparable to long-tailed macaques, we recommend surveying at 40-50 m above closed-canopy vegetation with a 45 degrees camera angle. With other flight paramete

关键词： Detection rate ecological monitoring flight parameters Macaca fascicularis Mauritius unmanned aerial vehicle

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