[논문]Angles-Only Initial Orbit Determination of Low Earth Orbit (LEO) Satellites Using Real Observational Data

Hwang, Hyewon; Park, Sang-Young; Lee, Eunji

doi:10.5140/jass.2019.36.3.187

[국내논문] Angles-Only Initial Orbit Determination of Low Earth Orbit (LEO) Satellites Using Real Observational Data 원문보기

Journal of astronomy and space sciences, v.36 no.3, 2019년, pp.187 - 197

Hwang, Hyewon (Astrodynamics and Control Lab., Department of Astronomy, Yonsei University) , Park, Sang-Young (Astrodynamics and Control Lab., Department of Astronomy, Yonsei University) , Lee, Eunji (Astrodynamics and Control Lab., Department of Astronomy, Yonsei University)

Abstract ▼ AI-Helper

The Optical Wide-field patroL-Network (OWL-Net) is a Korean optical space surveillance system used to track and monitor objects in space. In this study, the characteristics of four Initial Orbit Determination (IOD) methods were analyzed using artificial observational data from Low Earth Orbit satellites, and an appropriate IOD method was selected for use as the initial value of Precise Orbit Determination using OWL-Net data. Various simulations were performed according to the properties of observational data, such as noise level and observational time interval, to confirm the characteristics of the IOD methods. The IOD results produced via the OWL-Net observational data were then compared with Two Line Elements data to verify the accuracy of each IOD method. This paper, thus, suggests the best method for IOD, according to the properties of angles-only data, for use even when the ephemeris of a satellite is unknown.

주제어

표/그림 (17)

표 Table 1. Information concerning the ground site used in numerical simulation
표 Table 2. The environment of the numerical simulation
표 Table 3. The properties of the artifcial orbits and the observed data
그림 Fig. 1. The distribution of RA and DEC data from the artifcial LEO satellites. RA, right ascension; DEC, declination, LEO, low Earth orbit.
그림 Fig. 2. The numerical results of the IOD methods with an observational time interval of 60 sec and a noise level of 50 arcsec. IOD, initial orbit determination.
그림 Fig. 3. The numerical results for noise level with an observational time interval of 10 sec. LEO, low Earth orbit.
그림 Fig. 4. The numerical results for noise level with an observational time interval of 60 sec. LEO, low Earth orbit.
그림 Fig. 5. The numerical results for observational time intervals (from 1 sec to 30 sec) when the noise level is 50 arcsec. LEO, low Earth orbit.
그림 Fig. 6. The numerical results for observational time intervals (from 30 sec to 120 sec) when the noise level is 50 arcsec. LEO, low Earth orbit.
그림 Fig. 7. The OWL-Net data of the Cryosat-2 satellite. The whole data set is on the left, and the second arc is on the right. OWL-Net, optical wide-feld patrol-network.
그림 Fig. 8. The OWL-Net data of the KOMPSAT-1 satellite. The whole data set is on the left, and the sixth arc is on the right. OWL-Net, optical wide-feld patrol-network.
표 Table 4. The IOD from Cryosat-2, excluding irregular data
그림 Fig. 9. The result of the Gauss method with Cryosat-2 data, excluding irregular data.
그림 Fig. 10. The result of the Gooding method with Cryosat-2 data, excluding irregular data.
그림 Fig. 11. The result of the Gauss method with KOMPSAT-1 data, excluding irregular data.
표 Table 5. IOD from KOMPSAT-1, excluding irregular data
그림 Fig. 12. The result of the Gooding method with KOMPSAT-1 data, excluding irregular data.

AI 본문요약
AI-Helper

* AI 자동 식별 결과로 적합하지 않은 문장이 있을 수 있으니, 이용에 유의하시기 바랍니다.

문제 정의

This study aims to find out the properties of the different IOD methods and to simulate IOD using OWLNet data to find an accurate initial value for Precise Orbit Determination (POD). As the POD converges at an initial orbit error of ~30 km (Lee at al.

제안 방법

The standard deviation of Gaussian distribution was set from 0 arcsec to 10 arcsec at 1 arcsec intervals, and from 20 arcsec to 100 arcsec at intervals of 10 arcsec. If noise was not included, the simulation was conducted once in order to analyze the performance of the IOD method itself. If random noise was included, simulations were conducted a hundred times to analyze the statistical performance of the IOD methods.
If noise was not included, the simulation was conducted once in order to analyze the performance of the IOD method itself. If random noise was included, simulations were conducted a hundred times to analyze the statistical performance of the IOD methods. In this case, the average of a hundred results(the position and velocity vectors at the middle observation point) was used as the result of the IOD, and the Root Mean Square (RMS) position and velocity errors were used as an indicator to demonstrate the accuracy of the IOD methods.
2017), four classical IOD methods were used rather than the improved IOD. In order to accurately apply the OWL-Net data, the simulation was initially conducted using artificial observation data with similar orbital characteristics to that of the real low Earth orbit (LEO) satellites Cryosat-2 and KOMPSAT-1. The simulations were performed by varying the properties such as the time interval and noise level of the observational data.
Optically observed data is in the form of topocentric RA and DEC which are derived from optical images. In this simulation, two types of artificial LEO satellite were generated to analyze the performance and property of the IOD methods. The orbital elements in the form of Two Line Elements (TLE) and observational time were set as similar to real satellites, after which the orbits were propagated for 600 sec and topocentric RA and DEC data were generated at intervals of 1 sec.
In this study, observational data from artificial LEO satellites was used to analyze the characteristics of method used for IOD, and real observational data from OWL-Net was then applied to verify the analysis.
Accurate prediction is important because the accuracy of the POD depends on the accuracy of the initial guess. In this study, we analyzed the characteristics of the IOD methods and applied observational data with various characteristics. It is therefore possible to improve the accuracy of IOD by selecting an appropriate method according to the characteristics of observational data such as noise level and time interval.
This section aims to verify which IOD method is the most appropriate, depending on the properties of observational data used. Since we need to decide which IOD method is the best for use with OWL-Net data, artificial orbits were produced that are similar to those of the Cryosat-2 and KOMPSAT-1 satellites, and artificial observation data were generated for the numerical simulations. Table 1 shows information concerning the observation ground sites, and Table 2 shows the environment simulated.
The simulations were performed by varying the properties such as the time interval and noise level of the observational data. The properties of the IOD methods were then assessed and confirmed, after which it was possible to determine which IOD method is the most appropriate according to the characteristics of the observational data. By using the various simulation results, the orbits of the Cryosat-2 and KOMPSAT-1 satellites can be determined using the most appropriate IOD method.
In order to accurately apply the OWL-Net data, the simulation was initially conducted using artificial observation data with similar orbital characteristics to that of the real low Earth orbit (LEO) satellites Cryosat-2 and KOMPSAT-1. The simulations were performed by varying the properties such as the time interval and noise level of the observational data. The properties of the IOD methods were then assessed and confirmed, after which it was possible to determine which IOD method is the most appropriate according to the characteristics of the observational data.
1 shows the distribution of the RA and DEC observation data from the artificial LEO satellites over time. Three sets of RA and DEC were selected from the generated data for IOD, after which the performance of each IOD method was analyzed depending on the noise level and the observational time interval. From these simulations, the Gooding method was found to be too sensitive to the initial guess of the range, so the range value was initially guessed based on the result of the Gauss method.
If IOD is conducted with data corrupted with noise, the accuracy of the determined orbit decreases. To assess the effects of noise on the results of IOD, we conducted a hundred Monte-Carlo simulations with artificial data that had been corrupted with Gaussian noise. The standard deviation of Gaussian distribution was set from 0 arcsec to 10 arcsec at 1 arcsec intervals, and from 20 arcsec to 100 arcsec at intervals of 10 arcsec.
We analyzed the properties of IOD methods by applying real observational data from two LEO satellites, Cryosat-2 and KOMPSAT-1, and then TLE data was used as a reference. The Laplace method was excluded from the analysis using real data because of the significant position errors, as mentioned in Section 3.

이론/모형

In this research, OWL-Net data for two LEO satellites, Cryosat-2 and KOMPSAT-1, were used to verify IOD methods. The file reporting OWL-Net data includes the name of the satellite and information concerning the ground site, the topocentric RA, the topocentric DEC, and the observational time.
The Earth gravity model (EGM96, 40 × 40), the gravity of Sun/Moon, and the atmospheric drag model (Jacchia-Roberts) were applied for orbit propagation.

성능/효과

These simulation results are similar to the results of the studies that the position errors of the IOD result of LEO satellites are about several ten kilometers (Der 2012), and the probability of the double-r method failing when the observation time interval is about 10 sec or more (Schaeperkoetter 2011), and the Gauss method error is small when the observation time interval is less than about 60 sec but the error is proportional to the interval when the interval is longer than about 60 sec (Karimi & Mortari 2011).
5 shows the results of IOD when the observational time interval is from 1 sec to 30 sec. Under these conditions, the results of the double-r method either did not converge or produced errors of several hundred km and the results of the Gooding method also did not converge accurately, so the double-r and Gooding method are thought to be less precise than the Gauss method. This is pronounced with observational time intervals of less than 10 sec.

참고문헌 (19)

10.1007/s10569-016-9694-z Armellin R, Di Lizia P, Zanetti R, Dealing with uncertainties in angles-only initial orbit determination, Celest. Mech. Dyn. Astron. 125, 435-450 (2016). 10.1007/s10569-016-9694-z

상세보기
10.1007/s10569-006-9022-0 Celletti A, Pinzari G, Dependence on the observational time intervals and domain of convergence of orbital determination methods, Celest. Mech. Dyn. Astron. 95, 327- 344 (2006). 10.1007/s10569-006-9022-0

상세보기
Choi J, Jo JH, Kim S, Yim HS, Choi EJ, et al., Integrity assessment and verification procedure of angle-only data for low earth orbit space objects with optical wide-field patroL-network (OWL-Net), J. Astron. Space Sci. 36, 35-43 (2019). 10.5140/JASS.2019.36.1.35
Coleman GD, Silny JF, Angles-only initial orbit determination (IOD), U.S. Patent, No. US9352858B2, 31 May 2016.
Der G, New Angles-only Algorithms for Initial Orbit Determination, in 2012 AMOS Conference, Maui, 11-14 Sep 2012.
Dolado JC, Yanez C, Anton A, On the performance analysis of Initial Orbit Determination algorithms, in 2016 IAC Conference, Mexico, 26-30 Sep 2016.
Escobal PR, Methods of Orbit Determination (Wiley, New York, 1965).
10.7446/jaesa.0401.04 Fadrique FM, Maté AÁ, Grau, JJ, Sánchez JF, García LA, Comparison of angles only initial orbit determination algorithms for space debris cataloquing, J. Aerosp. Eng. 4, 39- 51 (2012). 10.7446/jaesa.0401.04
10.1007/BF00049379 Gooding RH, A new procedure for the solution of the classical problem of minimal orbit determination from three lines of sight, Celest. Mech. Dyn. Astron. 66, 387-423 (1996).10.1007/BF00049379

상세보기
Henderson TA, Mortari D, Davis J, Modifications to the Gooding Algorithm for Angles-Only Initial Orbit Determination, in AAS/AIAA Space Flight Mechanics Meeting (2010).
10.1007/s10569-010-9321-3 Karimi RR, Mortari D, Initial orbit determination using multiple observations, Celest. Mech. Dyn. Astron. 109, 167-180 (2011).10.1007/s10569-010-9321-3

상세보기
10.5140/JASS.2017.34.1.19 Lee E, Park SY, Shin B, Cho S, Choi EJ, et al., Orbit determination of KOMPSAT-1 and Cryosat-2 satellites using optical wide-field patrol network (OWL-Net) data with batch least squares filter, J. Astron. Space Sci. 34, 19-30 (2017). 10.5140/JASS.2017.34.1.19

원문보기 상세보기
Long AC, Pajerski R, Luczak R, Goddard trajectory determination system (GTDS) mathematical theory (revision 1), National Aeronautics and Space Administration/Goddard Space Flight Center, FDD/552-89/001 and CSC/TR-89/6001 (1989).
10.1016/j.asr.2018.04.008 Park JH, Yim HS, Choi YJ, Jo JH, Moon HK, et al., OWL-Net: A global network of robotic telescopes for satellite observation, Adv. Space Res. 62, 152-163 (2018). 10.1016/j.asr.2018.04.008

상세보기
10.5140/JASS.2015.32.4.357 Park M, Jo JH, Cho S, Choi J, Kim CH, et al., Minimum number of observation points for LEO satellite orbit estimation by OWL network, J. Astron. Space Sci. 32, 357-366 (2015). 10.5140/JASS.2015.32.4.357

원문보기 상세보기
Schaeperkoetter AV, A comprehensive comparison between angles-only initial orbit determination techniques, PhD Dissertation, Texas A&M University (2011).
10.1086/113644 Taff LG, On initial orbit determination, Astron. J. 89, 1426-1428 (1984). 10.1086/113644
10.21236/ADA142994 Taff LG, Randall PM, Stansfield SA, Angles-only, ground-based, initial orbit determination, Massachusetts Inst of Tech Lexington Lincoln Lab, TR-1984-618 (1984).10.21236/ADA142994
Vallado DA, Fundamentals of Astrodynamics and Applications (Microcosm Press, El Segundo, 2001).

표제어: PCR

동의어: Packet Collision Rate

용어 설명 출처 목록 (6)

용어 설명: PCR은 세균 특이성이 있는 primer를 이용하여 적은 수의 세균이 있을지라도 쉽게 검출할 수 있는 유용한 방법이며, 이를 이용하여 구강 내 치면세균막이나 타액에서 직접 세균을 검출할 수 있게 되었다[8].

내보내기 구분	파일저장 인쇄 메일전송
구성항목	기본정보 상세정보 관리번호, 논문명, 저널/프로시딩명, 저자 , 발행년, 권, 호, 시작페이지, 끝페이지, 발행기관 관리번호, 논문명, 대등논문명, 저자 , 저널/프로시딩명, 발행기관, 발행년, 발행언어, 권, 호, 시작페이지, 끝페이지, ISBN, ISSN, 주제분야, 키워드, 초록(한글), 초록(영문), 저자(소속기관)
저장형식	Text(ASCII format) Excel format RefWorks Direct Export RIS format (for Reference Manager, ProCite, EndNote), Scholar's Aids, Mendeley
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	총 건의 자료가 검색되었습니다. 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오. ~ Text(ASCII format) Excel format

연합인증