Performance-Driven Design of Carrier Phase Differential Navigation Frameworks With Megaconstellation LEO Satellites

A navigation framework with carrier phase differential measurements from megaconstellation low Earth orbit (LEO) satellite signals is developed. The measurement errors due to ephemeris errors and ionospheric and tropospheric delays are derived and the statistics of the dilution of precision is characterized. Moreover, the joint probability density function of the megaconstellation LEO satellites' azimuth and elevation angles is derived to 1) enable performance characterization of navigation frameworks with LEO satellites in a computationally efficient way and 2) facilitate parameter design, namely, the differential baseline, to meet desired performance requirements. The Starlink constellation is used as a specific LEO megaconstellation example to demonstrate the developed carrier phase differential LEO (CD-LEO) navigation framework. Simulation results are presented demonstrating the efficacy of the proposed CD-LEO framework for an unmanned aerial vehicle (UAV) navigating for 15.1 km in 300 s, while using signals from 44 Starlink satellites, achieving a 3-D position root mean squared error (RMSE) of 2.2 m and a 2-D RMSE of 32.4 cm. Experimental results are presented showing UAV navigating for 2.28 km in 2 min over Aliso Viejo, CA, USA, using exclusively signals from only two Orbcomm LEO satellites, achieving an unprecedented position RMSE of 14.8 m.

Automated summary

A navigation framework using carrier phase differential measurements from megaconstellation low Earth orbit (LEO) satellite signals is developed. The measurement errors and dilution of precision statistics are derived to analyze the performance of the framework. The efficacy of the carrier phase differential LEO (CD-LEO) navigation framework is demonstrated using simulation and experimental results.