Hostname: page-component-78c5997874-4rdpn Total loading time: 0 Render date: 2024-11-09T05:34:56.676Z Has data issue: false hasContentIssue false
  • English
  • Français

Precise Spacecraft Relative Positioning using Single-Frequency Pseudorange Measurements

Published online by Cambridge University Press:  22 December 2008

Marc-Philippe Rudel  and
Pini Gurfil
Marc-Philippe Rudel*
Affiliation:
(Technion, Israel Institute of Technology)
Pini Gurfil
Affiliation:
(Technion, Israel Institute of Technology)
*
(Email: [email protected])
Get access Rights & Permissions [Opens in a new window]

Abstract

The ranging accuracy provided by pseudorange-only techniques is usually no better than a few metres when no differential corrections are applied. Carrier-phase algorithms, on the other hand, yield higher-precision estimates – down to a few millimetres – but are prone to ambiguities difficult to resolve. An easier-to-implement method, using single-frequency pseudorange measurements only, is presented. It allows for a decimetre-level relative positioning accuracy. Results, derived from the GPS Relative Positioning Equations, are validated with actual satellite data from the Gravity Recovery and Climate Experiment (GRACE) mission.

Keywords

Relative Positioning EquationsGRACEGNSSRGDOP
Type
Research Article
Information
The Journal of Navigation , Volume 62 , Issue 1 , January 2009 , pp. 119 - 134
Copyright
Copyright © The Royal Institute of Navigation 2008

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

REFERENCES

[1]Kroes, R. and Montenbruck, O. (2004). High Accuracy Kinematic Spacecraft Relative Positioning using Dual-Frequency GPS Carrier Phase Data. Institute of Navigation National Technical Meeting, San Diego, CA.Google Scholar
[2]Kroes, R. (2006). Precise Relative Positioning of Formation Flying Spacecraft using GPS. Nederlandse Commissie voor Geodesie.CrossRefGoogle Scholar
[3]Psiaki, M.L. and Mohiuddin, S. (2005). GPS Integer Ambiguity Resolution Using Factorized Least-Squares Techniques. Flight Mechanics Symposium, NASA Goddard Spaceflight Center, Greenbelt, MD.Google Scholar
[4]Misra, P. and Enge, P. (2006). Global Positioning System, Signals, Measurements and Performance. Ganga-Jamuna Press, Second Edition.Google Scholar
[5]Rudel, M.P. and Baldwin, J. (1997). GPS Relative Accuracy for Collision Avoidance. Institute of Navigation National Technical Meeting, Santa Monica, CA.Google Scholar
[6]Global Positioning System Standard Positioning Service Signal Specification, Second Edition (1995).Google Scholar
[7]Milliken, R.J. and Zoller, C.J., “Principle of Operation of NAVSTAR and System Characteristics”, Navigation, Vol. 25, No. 2, 1978.CrossRefGoogle Scholar
[8]Bancroft, S. (1985). An Algebraic Solution of the GPS Equations. IEEE Transactions on Aerospace and Electronic Systems, Vol. 21, No. 7.Google Scholar
[9]Svehla, D. and Rothacher, M. (2004). Kinematic and Dynamic Precise Orbit Determination of Low-Earth Orbiters. 2nd International GOCE User Workshop, Munich, Germany.Google Scholar
[10]Alfriend, K.T., Vadali, S.R., Gurfil, P. and How, J.P. (2007) Spacecraft Formation Flying: Dynamics, Control & Navigation, Elsevier Science, Oxford, UK.Google Scholar
[11]Montenbruck, O., Ebinuma, T., Lightsey, E.G. and Leung, S. (2002). A Real-Time Kinematic GPS Sensor for Spacecraft Relative Navigation. Aerospace, Science and Technology.CrossRefGoogle Scholar
[12]Jäggi, A., Hugentobler, U., Bock, H. and Beutler, G. (2007). Precise Orbit Determination for GRACE using Undifferenced or Doubly-Differenced GPS Data. Aerospace, Science and Technology.Google Scholar
[13]Wu, S.C. and Bar-Sever, Y.E. (2006). Real-Time Sub-cm Differential Orbit Determination of Two Low-Earth Orbiters with GPS Bias Fixing. Jet Propulsion Laboratory, National Aeronautics and Space Administration.Google Scholar
[14]Montenbruck, O., Kirschner, M., D'Amico, S. and Bettadpur, S. (2006). E/I-Vector Separation for Safe Switching of the GRACE Formation. Aerospace, Science and Technology.CrossRefGoogle Scholar
[15]Mohiuddin, S. and Psiaki, M.L. (2007). High-Altitude Satellite Relative Navigation Using Carrier-Phase Differential Global Positioning System Techniques. Journal of Guidance, Control and Dynamics, Vol. 30, No. 5.CrossRefGoogle Scholar