scholarly journals Research on the Gravity Disturbance Compensation Terminal for High-Precision Position and Orientation System

Sensors ◽  
2020 ◽  
Vol 20 (17) ◽  
pp. 4932
Author(s):  
Zhuangsheng Zhu ◽  
Hao Tan ◽  
Yue Jia ◽  
Qifei Xu

The Position and Orientation System (POS) is the core device of high-resolution aerial remote sensing systems, which can obtain the real-time object position and collect target attitude information. The goal of exceeding 0.015°/0.003° of its real-time heading/attitude measurement accuracy is unlikely to be achieved without gravity disturbance compensation. In this paper, a high-precision gravity data architecture for gravity disturbance compensation technology is proposed, and a gravity database with accuracy better than 1 mGal is constructed in the test area. Based on the “Block-Time Variation” Markov Model (B-TV-MM), a gravity disturbance compensation device is developed. The gravity disturbance compensation technology is applied to POS products for the first time, and is applied in the field of aerial remote sensing. Flight test results show that the heading accuracy and attitude accuracy of POS products are improved by at least 6% and 16%, respectively. The device can be used for the gravity disturbance compensation of various inertial technology products.

2017 ◽  
Vol 71 (3) ◽  
pp. 711-728 ◽  
Author(s):  
Zhuangsheng Zhu ◽  
Yiyang Guo ◽  
Wen Ye

Motion compensation is a significant part of an airborne remote sensing system. A Position and Orientation System (POS) can directly measure the motion information of an airborne remote sensing payload that can improve the quality of airborne remote sensing images. Gravity disturbance, information on which is often ignored due to being difficult to acquire in real-time, has become the main error source of POS in the development of inertial components. In this paper, a new real-time gravity compensation method is proposed, which includes the gravity disturbance as the error states of a POS Kalman filter, and an accurate gravity disturbance model is constructed using a time-varying Gaussian-Markov model based on a high-precision gravity map, whose resolution is enhanced by a new interpolation method based on Gaussian Process Regression (GPR). A flight experiment was conducted to evaluate the efficiency of the proposed method and the results showed that the proposed method performs well when compared with other real-time gravity compensation methods.


2017 ◽  
Vol 2017 ◽  
pp. 1-11 ◽  
Author(s):  
Jianli Li ◽  
Jiancheng Fang ◽  
Zhaoxing Lu ◽  
Lijian Bai

The airborne Position Orientation System (POS) can accurately measure space-time reference information and plays a vital role in aerial remote sensing system. It may be applied in a direct georeference system for optical camera and a motion imaging system for Synthetic Aperture Radar (SAR), which further advances efficiency and quality of imaging sensors. In this paper, the operation principle and components of airborne POS are introduced. Some key technologies of airborne POS are summarized. They include the error calibration and compensation, initial alignment, lever arm error modeling, time synchronization, and integrated estimation method. A high precision airborne POS has been developed and applied to a variety of aerial remote sensing systems.


2020 ◽  
Vol 28 (10) ◽  
pp. 2360-2369
Author(s):  
Xin JIANG ◽  
◽  
Wu-xiong CHEN ◽  
Hai-tao NIE ◽  
Zhi-cheng HAO ◽  
...  

2013 ◽  
Vol 475-476 ◽  
pp. 1572-1577 ◽  
Author(s):  
Zhi Yang Gou ◽  
Lai Wei Jiang ◽  
Sheng Hong Fan ◽  
Chang Ru Liu ◽  
Qiang Wang

The attitude information is indispensable to realize the full range of navigation part. Besides, in aerial remote sensing, photogrammetry and laser scanning, we can get exterior orientation elements by attitude of device. Based on Picard solving quaternion differential equation realized the real-time dynamic attitude matrix updating and attitude solution. Comparison of IMU three axis output, calculation error of heading is 0.036183°, pitch is 0.007969° and roll is 0.009627°. Finally, verify the feasibility and stability of Picard solving attitude.


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