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Laboratory simulation method for flight attitude disturbance

A laboratory simulation and flight attitude technology, which is applied in the field of vehicle-mounted shipboard applications and laboratory accurate simulation, can solve the problems of difficult to guarantee simulation accuracy, difficult to reproduce airborne interference, complicated implementation process, etc., and achieve simple and convenient operation. , Good adaptability to model objects, and the effect of improving measurement accuracy

Active Publication Date: 2015-12-09
SHANGHAI INST OF TECHNICAL PHYSICS - CHINESE ACAD OF SCI
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AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to propose a laboratory simulation method for flight attitude disturbances to solve the shortcomings of the existing simulation methods, such as complex implementation process, poor simulation versatility, difficulty in ensuring simulation accuracy, and difficulty in reproducing the actual situation of airborne interference

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  • Laboratory simulation method for flight attitude disturbance

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Embodiment Construction

[0025] According to the laboratory simulation method proposed by the present invention, the data obtained on the Yun 5-B aircraft in an aviation remote sensing test in Pingyin County, Shandong Province will be processed below, and the implementation example of the present invention will be described in further detail by this case, But it is not limited to this implementation example, and all similar methods and similar changes of the present invention should be included in the protection scope of the present invention.

[0026] Table 1 PPOIA61-A position and attitude measurement accuracy indicators

[0027]

[0028] 1) Before the flight test of Y-5-B aircraft (No. B-8173), the inertial measurement unit (IMU) of the PPOIA61-A high-precision positioning and orientation system (POS) produced by Lead Space Information Co., Ltd. was fixed on the On the optical observation window of the aerial remote sensing equipment, other configurations and operating procedures of the POS syst...

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Abstract

The invention discloses a laboratory simulation method for flight attitude disturbance, comprising the following steps: (1) using a high-precision inertia and satellite integrated navigation system to collect and record original data of attitude disturbance in an airborne environment in real time during flight test; (2) post-processing and optimizing the original data to improve the accuracy of measurement; (3) carrying out frequency domain and amplitude evaluation of the post-processing result data, and selecting a six-degrees-of-freedom motion platform of which both the frequency response and amplitude satisfy the requirements of simulation; (4) carrying out attitude disturbance simulation test under laboratory conditions with the post-processing result data as the position input of the motion track of the six-degrees-of-freedom motion platform; and (5) using the high-precision inertia and satellite integrated navigation system to collect and acquire attitude disturbance simulation data and make frequency domain and amplitude analysis, and comparing the amplitude-frequency characteristic of the attitude disturbance simulation data with that of the post-processing result data to confirm the accuracy of simulation. The laboratory simulation method for flight attitude disturbance has the advantages of high accuracy of attitude simulation, good airborne condition reproducibility, good adaptability to models, and simple and convenient operation.

Description

technical field [0001] The invention relates to an aircraft simulation technology, in particular to a technology for accurately simulating in a laboratory the attitude disturbance caused by the load of the aircraft during flight. This technology can be used to evaluate and detect the adaptability of aerospace loads to its flight platform attitude disturbance, and it is also suitable for vehicle-mounted applications. Background technique [0002] At present, there are two main methods for simulating the attitude disturbance of the aircraft in the air: [0003] One is to perform feature extraction and mathematical modeling on the flight attitude data, and then use the established mathematical model as the design or motion control input of the aircraft attitude simulation system, so as to realize the simulation of the attitude disturbance of the load in flight. The simulation accuracy of this method for flight attitude disturbance largely depends on whether the established mat...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B17/02
Inventor 刘敏杨艳艳王义坤周潘伟亓洪兴
Owner SHANGHAI INST OF TECHNICAL PHYSICS - CHINESE ACAD OF SCI
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