Receiver Time Misalignment Correction for GPS-based Attitude Determination

A prerequisite for a Global Positioning System (GPS) attitude determination is to calculate baselines between antennae with accuracy at the millimetre level simultaneously. However, in order to have a low cost attitude determination system, a set of Commercial-OffThe-Shelf (COTS) receivers with separate clocks are used. In this case, if the receiver clocks are not precisely synchronized, the baseline vector between antennae will be calculated from the GPS signals received at different times. This can be a significant error source for high-kinematic applications. In this paper, two equivalent and effective approaches are developed to compensate this significant bias for baseline estimation and attitude determination. Test results using real airborne GPS data demonstrate that the receiver time misalignment between the two receivers can result in a 5 cm baseline offset for an aircraft with a 50 m/s velocity; the corresponding attitude errors can reach about 0·50° in yaw and 0·10° in pitch respectively for the attitude determination system with a baseline length of 3·79 m. With the proposed methods, these errors can be effectively eliminated.

[1]  Huangqi Sun,et al.  ASSESSMENT OF A NON-DEDICATED GPS RECEIVER SYSTEM FOR PRECISE AIRBORNE ATTITUDE DETERMINATION , 1994 .

[2]  Mark Kuhl,et al.  Three-Dimensional Attitude Determination with the Ashtech 3DF 24-Channel GPS Measurement System , 1991 .

[3]  Yan-hua Zhang,et al.  Improved ambiguity function method based on analytical resolution for GPS attitude determination , 2007 .

[4]  Zhou Zebo,et al.  Heading Determination Algorithm with Single Epoch Dual-Frequency GPS Data , 2007 .

[5]  Gérard Lachapelle,et al.  Low-Cost GPS Receivers and Their Feasibility for Attitude Determination , 2002 .

[6]  Gang Lu,et al.  Development of a GPS multi-antenna system for attitude determination , 1995 .

[7]  Gabriele Giorgi,et al.  Testing of a new single-frequency GNSS carrier phase attitude determination method: land, ship and aircraft experiments , 2011 .

[8]  Yan Xu,et al.  GPS: Theory, Algorithms and Applications , 2003 .

[9]  Fei Guo,et al.  Real-time clock jump compensation for precise point positioning , 2013, GPS Solutions.

[10]  Sandra Verhagen,et al.  Functional model for spacecraft formation flying using non-dedicated GPS/Galileo receivers , 2010, 2010 5th ESA Workshop on Satellite Navigation Technologies and European Workshop on GNSS Signals and Signal Processing (NAVITEC).

[11]  Oliver Montenbruck,et al.  GPS-Based Attitude Determination for Microsatellites , 2007 .

[12]  Peter J. Buist,et al.  SINGLE-EPOCH, SINGLE-FREQUENCY, STANDALONE FULL ATTITUDE DETERMINATION: EXPERIMENTAL RESULTS , 2008 .

[13]  Peter Teunissen,et al.  GPS Observation Equations and Positioning Concepts , 1998 .

[14]  R. Langley,et al.  Instantaneous Real-time Cycle-slip Correction of Dual-frequency GPS Data , 2022 .

[15]  Yong Li,et al.  ATTITUDE DETERMINATION USING GPS VECTOR OBSERVATIONS , 2005 .

[16]  Hee-Sung Kim,et al.  Elimination of Clock Jump Effects in Low-Quality Differential GPS Measurements , 2012 .

[17]  Honglei Qin,et al.  New method for single epoch, single frequency land vehicle attitude determination using low-end GPS receiver , 2011, GPS Solutions.

[18]  P. Teunissen The least-squares ambiguity decorrelation adjustment: a method for fast GPS integer ambiguity estimation , 1995 .

[19]  Chaochao Wang,et al.  Development of a Low-cost GPS-based Attitude Determination System , 2003 .

[20]  Peter Teunissen,et al.  Testing a new multivariate GNSS carrier phase attitude determination method for remote sensing platforms , 2010 .

[21]  Craig Underwood,et al.  The Use of Commercial Technology for Spaceborne GPS Receiver Design , 1998 .

[22]  Oliver Montenbruck,et al.  GPS for Microsatellites – Status and Perspectives , 2008 .