Map Creation Algorithm and Initial Attitude Estimation Method for Optical Head Tracker System

This paper proposes an interlaced attitude estimation method for spacecraft using vector observations, which can simultaneously estimate the constant attitude at the very start and the attitude of the body frame relative to its initial state. The arbitrary initial attitude, described by constant attitude at the very start, is determined using quaternion estimator which requires no prior information. The multiplicative extended Kalman filter (EKF) is competent for estimating the attitude of the body frame relative to its initial state since the initial value of this attitude is exactly known. The simulation results show that the proposed algorithms could achieve better performance compared with the state-of-the-art algorithms even with extreme large initial errors. Meanwhile, the computational burden is also much less than that of the advanced nonlinear attitude estimators.

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Optical Head Tracker using Pattern Matching for Initial Attitude

Journal of the Korean Society for Aeronautical & Space Sciences ◽

10.5139/jksas.2009.37.5.470 ◽

2009 ◽

Vol 37 (5) ◽

pp. 470-475 ◽

Cited By ~ 1

Keyword(s):

Pattern Matching ◽

Optical Head ◽

Initial Attitude ◽

Head Tracker

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High-precision roll attitude estimation of decoupled canards relative to the projectile body using bipolar hall-effect sensors

Journal of Intelligent & Fuzzy Systems ◽

10.3233/jifs-189718 ◽

2021 ◽

pp. 1-9

Author(s):

Tingting Yin ◽

Zhong Yang ◽

Youlong Wu ◽

Fangxiu Jia

Keyword(s):

Hall Effect ◽

Real Time ◽

High Precision ◽

Solution Method ◽

Estimation Method ◽

Estimation Algorithm ◽

Attitude Estimation ◽

Fuzzy Algorithms ◽

Positioning Method ◽

Hall Effect Sensors

The high-precision roll attitude estimation of the decoupled canards relative to the projectile body based on the bipolar hall-effect sensors is proposed. Firstly, the basis engineering positioning method based on the edge detection is introduced. Secondly, the simplified dynamic relative roll model is established where the feature parameters are identified by fuzzy algorithms, while the high-precision real-time relative roll attitude estimation algorithm is proposed. Finally, the trajectory simulations and grounded experiments have been conducted to evaluate the advantages of the proposed method. The positioning error is compared with the engineering solution method, and it is proved that the proposed estimation method has the advantages of the high accuracy and good real-time performance.

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Deep learning–based fifth-generation millimeter-wave communication channel tracking for unmanned aerial vehicle Internet of things networks

International Journal of Distributed Sensor Networks ◽

10.1177/1550147719865882 ◽

2019 ◽

Vol 15 (8) ◽

pp. 155014771986588 ◽

Cited By ~ 3

Author(s):

Shan Meng ◽

Xin Dai ◽

Bicheng Xiao ◽

Yimin Zhou ◽

Yumei Li ◽

...

Keyword(s):

Internet Of Things ◽

Unmanned Aerial Vehicle ◽

Millimeter Wave ◽

Estimation Method ◽

Attitude Estimation ◽

Base Stations ◽

Communication Link ◽

Multiple Sensors ◽

Channel Tracking ◽

Aerial Vehicle

Using unmanned aerial vehicle as movable base stations is a promising approach to enhance network coverage. Moreover, movable unmanned aerial vehicle–base stations can dynamically move to the target devices to expand the communication range as relays in the scenario of the Internet of things. In this article, we consider a communication system with movable unmanned aerial vehicle–base stations in millimeter-Wave. The movable unmanned aerial vehicle–base stations are equipped with antennas and multiple sensors for channel tracking. The cylindrical array antenna is mounted on the movable unmanned aerial vehicle–movable base stations, making the beam omnidirectional. Furthermore, the attitude estimation method using the deep neural network can replace the traditional attitude estimation method. The estimated unmanned aerial vehicle attitude information is combined with beamforming technology to realize a reliable communication link. Simulation experiments have been performed, and the results have verified the effectiveness of the proposed method.

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Attitude Estimation Method of Space Targets by 3D Reconstruction of Principal Axis from ISAR Image

Procedia Computer Science ◽

10.1016/j.procs.2019.01.211 ◽

2019 ◽

Vol 147 ◽

pp. 158-164

Author(s):

Huo Chao-ying ◽

Yin Hong-cheng ◽

Wei Xiao ◽

Xing Xiao-yu ◽

Man Liang

Keyword(s):

3D Reconstruction ◽

Principal Axis ◽

Estimation Method ◽

Attitude Estimation

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About the Efficient Scheme of Initial Attitude Estimation Using Low Accuracy Micro-Electro-Mechanical Sensors

Russian Aeronautics ◽

10.3103/s106879981903005x ◽

2019 ◽

Vol 62 (3) ◽

pp. 387-393

Author(s):

T. Yu. Gainutdinova ◽

A. V. Gainutdinova ◽

V. G. Gainutdinov

Keyword(s):

Attitude Estimation ◽

Efficient Scheme ◽

Initial Attitude ◽

Mechanical Sensors

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Method of large acceleration change for in-flight alignment of projectiles based on double-vector observations

Transactions of the Institute of Measurement and Control ◽

10.1177/0142331218811468 ◽

2018 ◽

Vol 41 (10) ◽

pp. 2782-2788

Author(s):

Yun Xu ◽

Zhen Hong ◽

Yan Su ◽

Xin-hua Zhu

Keyword(s):

Error Analysis ◽

Rate Equation ◽

Simulation Experiment ◽

Attitude Estimation ◽

Flight Time ◽

Initial Attitude ◽

Misalignment Error ◽

Short Flight

Aiming at the problem that the purposive maneuver of the guided projectile is difficult to be realized during its short flight time, a method based on large acceleration change using double-vector observations for the in-flight alignment was proposed. First, according to the navigation velocity rate equation, double-vector observations were derived, and the Request algorithm was introduced for the initial attitude estimation. Then, error analysis was discussed, which puts forward a large acceleration change for the in-flight alignment. Simulation experiment analyzed and discussed the effectiveness of the proposed large acceleration change for the in-flight alignment. The simulation result indicated that the in-flight alignment can be achieved quickly, and the heading misalignment error is about 0.3°, the pitch and rolling misalignment errors are less than 0.2°.

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