[논문]Characteristics of Relative Navigation Algorithms Using Laser Measurements and Laser-GPS Combined Measurements

Kang, Dae-Eun; Park, Sang-Young; Son, Jihae

doi:10.5140/jass.2018.35.4.287

Characteristics of Relative Navigation Algorithms Using Laser Measurements and Laser-GPS Combined Measurements 원문보기

Journal of astronomy and space sciences, v.35 no.4, 2018년, pp.287 - 293

Kang, Dae-Eun (Department of Astronomy, Yonsei University) , Park, Sang-Young (Department of Astronomy, Yonsei University) , Son, Jihae (Department of Astronomy, Yonsei University)

Abstract ▼ AI-Helper

This paper presents a satellite relative navigation strategy for formation flying, which chooses an appropriate navigation algorithm according to the operating environment. Not only global positioning system (GPS) measurements, but laser measurements can also be utilized to determine the relative positions of satellites. Laser data is used solely or together with GPS measurements. Numerical simulations were conducted to compare the relative navigation algorithm using only laser data and laser data combined with GPS data. If an accurate direction of laser pointing is estimated, the relative position of satellites can be determined using only laser measurements. If not, the combined algorithm has better performance, and is irrelevant to the precision of the relative angle data between two satellites in spherical coordinates. Within 10 km relative distance between satellites, relative navigation using double difference GPS data makes more precise relative position estimation results. If the simulation results are applied to the relative navigation strategy, the proper algorithm can be chosen, and the relative position of satellites can be estimated precisely in changing mission environments.

주제어

표/그림 (12)

그림 Fig. 1. Chief-centered relative coordinate systems: Position of the deputy satellite is represented with RSW coordinates and spherical coordinates.
표 Table 1. Technical characteristics of the algorithms
그림 Fig. 2. Elements of the state vector in Algorithm 1: They are represented in spherical coordinates.
그림 Fig. 3. Concept of the single diference of GPS in Algorithm 2: Pseudorange values of the chief nd the deputy satellites have the same ionospheric path delay error.
그림 Fig. 4. Concept of the double difference of GPS in Algorithm 3.
표 Table 2. Initial position and velocity of the satellites in ECEF coordinates
표 Table 3. 3D RMS error of the relative position according to the conditions, inter-satellite range, and attitude determination error
그림 Fig. 5. 3D RMS error of the relative position according to inter-satellite range using Algorithm 1–3 when the attitude determination error is 1″.
그림 Fig. 6. 3D RMS error of the relative position according to inter-satellite range using Algorithm 1–3 when the attitude determination error is 0.001°.
그림 Fig. 7. 3D RMS error of the relative position according to inter-satellite range using Algorithm 1–3 when the attitude determination error is 0.005°.
그림 Fig. 8. 3D RMS error of the relative position according to inter-satellite range using Algorithm 1–3 when the attitude determination error is 0.01°.
표 Table 4. Characteristics of the relative navigation algorithms based on the simulation results

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제안 방법

In this research, real-time relative navigation algorithms using the laser and GPS measurement data were assessed. Software simulation was conducted to compare the performance of the algorithms using various inter-satellite range and precision of attitude determination.
In this study, the performance of the previous algorithms (Jung et al. 2012; Lee et al. 2015; Oh et al. 2016) is compared under various conditions and with improved laser measurement data that includes the hardware properties of the instrument. Numerical simulations are conducted on hardware-in-the-loop simulator (HILS) developed by Park et al.
In this research, real-time relative navigation algorithms using the laser and GPS measurement data were assessed. Software simulation was conducted to compare the performance of the algorithms using various inter-satellite range and precision of attitude determination. For numerical evaluation, the simulation results were represented as 3D RMS error.

데이터처리

Software simulation was conducted to compare the performance of the algorithms using various inter-satellite range and precision of attitude determination. For numerical evaluation, the simulation results were represented as 3D RMS error. If the high-precision attitude determination system is guaranteed, the algorithm that uses only the laser measurements can have the best navigation result.
The factor of the drift is x. The error levels of the measurement data were determined by laser distance specification and attitude-determination error. The estimation result in spherical coordinates is d related to the measurement error.

참고문헌 (18)

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