Lunar satellite orbit determination analysis and quality assessment from Lunar Prospector tracking data and SELENE simulations

2007 ◽  
Vol 40 (1) ◽  
pp. 43-50 ◽  
Author(s):  
Sander Goossens ◽  
Koji Matsumoto
Keyword(s):  
Quality Assessment ◽  
Orbit Determination ◽  
Satellite Orbit ◽  
Tracking Data ◽  
Lunar Prospector ◽  
Lunar Satellite

Lunar satellite orbit determination by a classical binary star method.

AIAA Journal ◽  
1966 ◽  
Vol 4 (7) ◽  
pp. 1287-1293 ◽  
Author(s):  
RICHARD E. BATEMAN ◽  
JOSEPH N. BENEZRA ◽  
FRANK J. PLACEK
Keyword(s):  
Orbit Determination ◽  
Binary Star ◽  
Satellite Orbit ◽  
Lunar Satellite

Validation of Geostationary Satellite Orbit Determination Using Single-Station Antenna Tracking Data

2013 ◽  
Vol 50 (6) ◽  
pp. 1248-1255 ◽  
Author(s):  
Yoola Hwang ◽  
Byoung-Sun Lee ◽  
Bang-Yeop Kim ◽  
Hae-Yeon Kim ◽  
Haedong Kim
Keyword(s):  
Orbit Determination ◽  
Satellite Orbit ◽  
Geostationary Satellite ◽  
Tracking Data ◽  
Single Station

scholarly journals Comparisons of CODE and CNES/CLS GPS satellite bias products and applications in Sentinel-3 satellite precise orbit determination

GPS Solutions ◽  
2021 ◽  
Vol 25 (4) ◽  
Author(s):  
Bingbing Duan ◽  
Urs Hugentobler
Keyword(s):  
Linear Combination ◽  
Orbit Determination ◽  
Fractional Part ◽  
Precise Orbit Determination ◽  
Satellite Orbit ◽  
Satellite Orbits ◽  
Satellite Clock ◽  
Analysis Center ◽  
Wide Lane ◽  
Total Difference

AbstractTo resolve undifferenced GNSS phase ambiguities, dedicated satellite products are needed, such as satellite orbits, clock offsets and biases. The International GNSS Service CNES/CLS analysis center provides satellite (HMW) Hatch-Melbourne-Wübbena bias and dedicated satellite clock products (including satellite phase bias), while the CODE analysis center provides satellite OSB (observable-specific-bias) and integer clock products. The CNES/CLS GPS satellite HMW bias products are determined by the Hatch-Melbourne-Wübbena (HMW) linear combination and aggregate both code (C1W, C2W) and phase (L1W, L2W) biases. By forming the HMW linear combination of CODE OSB corrections on the same signals, we compare CODE satellite HMW biases to those from CNES/CLS. The fractional part of GPS satellite HMW biases from both analysis centers are very close to each other, with a mean Root-Mean-Square (RMS) of differences of 0.01 wide-lane cycles. A direct comparison of satellite narrow-lane biases is not easily possible since satellite narrow-lane biases are correlated with satellite orbit and clock products, as well as with integer wide-lane ambiguities. Moreover, CNES/CLS provides no satellite narrow-lane biases but incorporates them into satellite clock offsets. Therefore, we compute differences of GPS satellite orbits, clock offsets, integer wide-lane ambiguities and narrow-lane biases (only for CODE products) between CODE and CNES/CLS products. The total difference of these terms for each satellite represents the difference of the narrow-lane bias by subtracting certain integer narrow-lane cycles. We call this total difference “narrow-lane” bias difference. We find that 3% of the narrow-lane biases from these two analysis centers during the experimental time period have differences larger than 0.05 narrow-lane cycles. In fact, this is mainly caused by one Block IIA satellite since satellite clock offsets of the IIA satellite cannot be well determined during eclipsing seasons. To show the application of both types of GPS products, we apply them for Sentinel-3 satellite orbit determination. The wide-lane fixing rates using both products are more than 98%, while the narrow-lane fixing rates are more than 95%. Ambiguity-fixed Sentinel-3 satellite orbits show clear improvement over float solutions. RMS of 6-h orbit overlaps improves by about a factor of two. Also, we observe similar improvements by comparing our Sentinel-3 orbit solutions to the external combined products. Standard deviation value of Satellite Laser Ranging residuals is reduced by more than 10% for Sentinel-3A and more than 15% for Sentinel-3B satellite by fixing ambiguities to integer values.

Quality assessment of FORMOSAT-3/COSMIC and GRACE GPS observables: analysis of multipath, ionospheric delay and phase residual in orbit determination

GPS Solutions ◽  
2009 ◽  
Vol 14 (1) ◽  
pp. 121-131 ◽  
Author(s):  
Cheinway Hwang ◽  
Tzu-Pang Tseng ◽  
Ting-Jung Lin ◽  
Dražen Švehla ◽  
Urs Hugentobler ◽  
...  
Keyword(s):  
Quality Assessment ◽  
Orbit Determination ◽  
Ionospheric Delay

Application of the GPS system for preliminary satellite orbit determination

1997 ◽  
Vol 19 (11) ◽  
pp. 1671-1675
Author(s):  
A.P.M Chiaradia ◽  
S da Silva Fernandes ◽  
R.Vilhena de Moraes
Keyword(s):  
Orbit Determination ◽  
Satellite Orbit ◽  
Gps System

Autonomous navigation algorithm based on AUKF filter about fusion of geomagnetic and sunlight directions

2018 ◽  
Vol 11 (4) ◽  
pp. 471-485 ◽  
Author(s):  
Bing Hua ◽  
Zhiwen Zhang ◽  
Yunhua Wu ◽  
Zhiming Chen
Keyword(s):  
Orbit Determination ◽  
Geomagnetic Field ◽  
Autonomous Navigation ◽  
Unscented Kalman Filter ◽  
Satellite Orbit ◽  
Field Vector ◽  
Low Earth Orbit ◽  
Fusion Algorithm ◽  
Content Type ◽  
Navigation Algorithm

Purpose The geomagnetic field vector is a function of the satellite’s position. The position and speed of the satellite can be determined by comparing the geomagnetic field vector measured by on board three-axis magnetometer with the standard value of the international geomagnetic field. The geomagnetic model has the disadvantages of uncertainty, low precision and long-term variability. Therefore, accuracy of autonomous navigation using the magnetometer is low. The purpose of this paper is to use the geomagnetic and sunlight information fusion algorithm to improve the orbit accuracy. Design/methodology/approach In this paper, an autonomous navigation method for low earth orbit satellite is studied by fusing geomagnetic and solar energy information. The algorithm selects the cosine value of the angle between the solar light vector and the geomagnetic vector, and the geomagnetic field intensity as observation. The Adaptive Unscented Kalman Filter (AUKF) filter is used to estimate the speed and position of the satellite, and the simulation research is carried out. This paper also made the same study using the UKF filter for comparison with the AUKF filter. Findings The algorithm of adding the sun direction vector information improves the positioning accuracy compared with the simple geomagnetic navigation, and the convergence and stability of the filter are better. The navigation error does not accumulate with time and has engineering application value. It also can be seen that AUKF filtering accuracy is better than UKF filtering accuracy. Research limitations/implications Geomagnetic navigation is greatly affected by the accuracy of magnetometer. This paper does not consider the spacecraft’s environmental interference with magnetic sensors. Practical implications Magnetometers and solar sensors are common sensors for micro-satellites. Near-Earth satellite orbit has abundant geomagnetic field resources. Therefore, the algorithm will have higher engineering significance in the practical application of low orbit micro-satellites orbit determination. Originality/value This paper introduces a satellite autonomous navigation algorithm. The AUKF geomagnetic filter algorithm using sunlight information can obviously improve the navigation accuracy and meet the basic requirements of low orbit small satellite orbit determination.

scholarly journals Local gravity from Lunar Prospector tracking data: Results for Mare Serenitatis

2005 ◽  
Vol 57 (11) ◽  
pp. 1127-1132 ◽  
Author(s):  
S. Goossens ◽  
P. N. A. M. Visser ◽  
K. Heki ◽  
B. A. C. Ambrosius
Keyword(s):  
Tracking Data ◽  
Lunar Prospector ◽  
Local Gravity ◽  
Mare Serenitatis
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