Abstract
With the demand for high resolution remote sensing, load array technology has gradually become an effective measure to improve imaging resolution. However, the external flow and internal engine vibration disturbance may lead to the flexible deformation of wings. The traditional rigid baseline error compensation method cannot solve the problem of serious coupling movement error caused by flexible deformation. To address the problem, a transfer alignment model based on fiber Bragg grating for distributed position and orientation system is proposed in this paper. Firstly, based on the multidimensional requirements of flexible deformation information, the layout scheme of fiber Bragg grating was designed, then the continuous strain in the wing surface was obtained after the quadratic fitting of strain measured by fiber Bragg gratings, and the deformation displacement and angle are calculated. Thirdly, flexible deformation compensation for distributed position and orientation system based on fiber Bragg grating was studied. The state equation including position error, velocity error, misalignment angle, and inertial device error was established. The position and attitude information compensated by the flexible lever arm was used as the quantitative measurement. The filtering estimation improved the measurement accuracy of the slave inertial navigation systems. At last, the experiment was carried out and showed that the accuracy of the transfer alignment has been improved significantly.
Highlights
With the development of the flight platform technology, it is possible to realize simultaneous observation of multi-remote sensing devices on the same platform using multiple observation windows, such as SAR, visible light camera, imaging spectrometer, and laser radar, which can operate at the same time [1,2,3]
The wing deformation test and verification system based on fiber Bragg grating (FBG) is composed of a simulated wing structure, the FBG deformation measurement system, the distributed POS (DPOS), and six degree of freedom motion simulator
Deformation measurement system is composed of FBG sensors and a demodulator, in which the FBG sensor is installed on the upper surface and lower surface of the simulated wing structure
Summary
With the development of the flight platform technology, it is possible to realize simultaneous observation of multi-remote sensing devices on the same platform using multiple observation windows, such as SAR, visible light camera, imaging spectrometer, and laser radar, which can operate at the same time [1,2,3]. The subarray antenna is often installed at different wing nodes, which is limited by volume weight and even cost and conducts distributed motion measurement often using. This paper used to obtain the three-dimensional deformation between deformation between the main node and the sub nodes, which includes the flexural deformation the main nodevector and the which includes thethe flexural deformation vector displacement andsub the nodes, deflection angles between main system and thedisplacement sub-nodes, the and the deflection angles between the main system and the sub-nodes, the high-precision high-precision measurement information is obtained, and at the same time, the transfer alignment measurement obtained, and the samethe time, the transfer alignmentismodel basedand on model based information on FBG is isestablished.
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