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Aircraft aeroelasticity inertia sensor layout method

An inertial sensor and aeroelasticity technology, which is applied in instruments, special data processing applications, electrical digital data processing, etc., can solve problems such as the layout optimization method of aircraft aeroelasticity inertial sensors that have not yet been retrieved, and achieve the effect of reducing costs.

Active Publication Date: 2015-10-21
BEIJING INSTITUTE OF TECHNOLOGYGY +1
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AI Technical Summary

Problems solved by technology

At present, most sensor layout optimization schemes are often obtained based on experience and trial and error, and no general aircraft aeroelastic inertial sensor layout optimization method has been retrieved.

Method used

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  • Aircraft aeroelasticity inertia sensor layout method
  • Aircraft aeroelasticity inertia sensor layout method
  • Aircraft aeroelasticity inertia sensor layout method

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Embodiment 1

[0040] Embodiment one: this embodiment comprises the following steps:

[0041] 1. On the basis of using the finite element method to solve the dynamic response of the aircraft structure, the finite element model is corrected by the fluid-structure coupling MPCCI or other fluid-structure coupling methods, and the fluid-structure coupling analysis that traverses all flight states and disturbance factors is performed. Aircraft aeroelastic inertia analysis includes harmonic response analysis, random vibration and transient response analysis, and corresponding harmonic response loading, random vibration response and transient response experiments are carried out.

[0042] 2. Calculate the relatively accurate structural dynamic response and obtain the response of each node in the finite element model: due to limited computing resources in actual engineering calculations, the response analysis data obtained by fluid-solid coupling calculations are often not comprehensive enough, but t...

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Abstract

The invention relates to an aircraft aeroelasticity inertia sensor layout method. According to the method, the aircraft structure dynamic response is solved by employing the finite element method, a finite element model is corrected via a fluid-solid interaction method, and a fluid-solid coupling analysis of all the flight states and disturbance factors is conducted; the relatively precise structure dynamic response is calculated, and the response of each node in the finite element model is obtained; standardization processing of a data set is performed, and an elasticity wing structure dynamic response data set is generated; and data clustering by employing a clustering method based on distance measurement in pattern recognition is finally performed, and the final positions of the sensors are optimized and obtained. According to the method, the maximization of measuring information of sensors is regarded as the overall goal, optimization balance between the quantity of the sensors and the optimal layout positions is performed, and valuable aeroelasticity characteristic values can be acquired at the arranging position of each sensor.

Description

Technical field: [0001] The invention relates to the field of aircraft aeroelastic inertial sensor layout, and is based on the dynamic response analysis and dynamic clustering method of the aircraft structure. Background technique: [0002] Since the end of the last century, NASA has started a research on the intelligent structure control technology of flexible aircraft. The research plan aims to optimize the layout configuration for embedded sensors and actuators, so as to realize the wing shape, aircraft structure noise and structure vibration. active control. From large space vehicles to micro-aircraft, related research results have been applied to aircraft of various sizes, and this technology can be used to improve the safety, reliability and environmental adaptability of aircraft. The research on optimized sensor layout technology is a crucial research content of this research plan. [0003] In the initial stage of sensor layout technology research, domain experts of...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 由育阳杨志宏
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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