A real-time kinematic GPS sensor for spacecraft relative navigation

Montenbruck, Oliver; Ebinuma, Takuji; Lightsey, E. Glenn; Leung, Siu N.

doi:10.1016/s1270-9638(02)01185-9

Cited by 49 publications

(29 citation statements)

References 4 publications

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“…Normalizing the magnitude of and , the unit vectors of the magnetic field are calculated such that . Then, the above equation is expressed as follows: (4) where and are unit vectors. From (2), unit length coordinates on -plane with respect to ECI are expressed as follows:…”

Section: B Determination Of the Body Axes In Eci Framementioning

confidence: 99%

“…Navigation methods using magnetometers and other sensors have been suggested in many literatures, which show that the earth gravity [2], the solar array direction [3], the earth sensor, 1545-598X/$20.00 © 2005 IEEE the sun sensor, the GPS [4], the gyroscope [5], and the accelerometer, all with magnetometer, can be used for attitude estimation. However, they all implemented either the Kalman Filter [6]- [8] or the TRIAD/QUEST algorithm [9] by using two or more than two three-axis measurement data.…”

Section: Introductionmentioning

confidence: 99%

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Gyroless Attitude Estimation of Sun-Pointing Satellites Using Magnetometers

Ahn

Lee

2005

IEEE Geosci. Remote Sensing Lett.

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Deterministic attitude estimation methods based on vector observations are used for the coarse-attitude calculation of the sun-pointing satellites. The objective of the deterministic attitude estimation is to get the direction cosine matrix without considering the stochastic noises. The existing deterministic attitude estimation methods require two complete (three-axis) vector observations corresponding to two known reference vectors. This letter suggests a new deterministic attitude estimation method using only geomagnetic-field measurements on two axes for sun-pointing satellites in the sun-acquisition mode.

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Section: B Determination Of the Body Axes In Eci Framementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Gyroless Attitude Estimation of Sun-Pointing Satellites Using Magnetometers

Ahn

Lee

2005

IEEE Geosci. Remote Sensing Lett.

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“…Based on these, we conducted various test including flight model (FM) performance test, system integration and EMI/EMC (Montenbruck et al 2005). We are also performing researches, based on the results, on the operation strategies for the individual scenarios for the IGOR operation.…”

Section: Introductionmentioning

confidence: 99%

Operation of the Radio Occultation Mission in KOMPSAT-5

Choi¹,

Lee²,

Cho³

et al. 2010

Journal of Astronomy and Space Sciences

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Korea multi-purpose satellite-5 (KOMPSAT-5) is a low earth orbit (LEO) satellite scheduled to be launched in 2010. To satisfy the precision orbit determination (POD) requirement for a high resolution synthetic aperture radar image of KOMPSAT-5, KOMPSAT-5 has atmosphere occultation POD (AOPOD) system which consists of a space-borne dual frequency global positioning system (GPS) receiver and a laser retro reflector array. A space-borne dual frequency GPS receiver on a LEO satellite provides position data for the POD and radio occultation data for scientific applications. This paper describes an overview of AOPOD system and operation concepts of the radio occultation mission in KOMPSAT-5. We showed AOPOD system satisfies the requirements of KOMPSAT-5 in performance and stability.

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Section: Introductionmentioning

confidence: 99%

“…One then refers to relative GPS [5] - [7]. However, rather than using the conventional differencing and double differencing method [5] - [7], in this paper a stochastic modeling framework is used where the common errors are explicitly acknowledged and treated as parameters to be estimated. The use of multiple GPS receivers which are connected by a two way data link and centralized processing of the measurements using statistical methods of parameter estimation has the potential of significantly improving the quality of the navigation solution.…”

Section: Introductionmentioning

confidence: 99%

Stochastic Modeling Based DGPS Estimation Algorithm

Pachter

Nguyen

2007

Navigation

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A Kinematic Differential GPS algorithm is presented. Specifically, the accurate relative (and absolute) positioning of a team, or formation, of mobile vehicles is considered and a general navigation web concept is advanced. The measurement situation is modeled under a stochastic framework, and, rather than differencing and double differencing, as is current practice in conventional DGPS, the common errors are explicitly acknowledged and a centralized position estimation algorithm is derived. In addition, the predicted covariance of the team members' position estimation errors is obtained. Also, treating the common errors as parameters to be estimated yields estimates of the clocks' relative errors. Extensive simulations are performed to validate the Kinematic DGPS algorithm. The results are compared to conventional DGPS scenarios, where the reference stations are stationary or there is only one available observation epoch. The positioning accuracy improvements achieved are gauged against the performance of conventional DGPS.

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A real-time kinematic GPS sensor for spacecraft relative navigation

Cited by 49 publications

References 4 publications

Gyroless Attitude Estimation of Sun-Pointing Satellites Using Magnetometers

Gyroless Attitude Estimation of Sun-Pointing Satellites Using Magnetometers

Operation of the Radio Occultation Mission in KOMPSAT-5

Stochastic Modeling Based DGPS Estimation Algorithm

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