GPS/INS Kalman filter design for spacecraft operating in the proximity of the international space station

David Gaylor, E. Glenn Lightsey

Research output: Chapter in Book/Report/Conference proceedingConference contribution

22 Citations (Scopus)

Abstract

The next generation reusable launch vehicle will operate in five flight phases: ascent, on-orbit, proximity operations, re-entry and landing. Navigation during each of these flight phases presents unique challenges. The Space Shuttle addresses these challenges by the use of a number of navigation sensors. However, an integrated GPS/INS navigation system may be able to meet the navigation requirements of all flight phases. Integrated GPS/INS systems have been built and demonstrated for the ascent, re-entry and landing phases and their performance is known. However, the same cannot be said for integrated GPS/INS systems for the on-orbit and proximity operations flight phases. Therefore, this research examines the performance of GPS/INS navigation during a rendezvous with the ISS. Error models for INS and GPS navigation sensors operating in the vicinity of the ISS have been developed. The GPS error model includes the effects of GPS signal blockage and multipath near the ISS. These error models have been used to develop an integrated GPS/INS extended Kalman filter. A simulation of the filter has been developed and the first test case shows position errors of less than 1 meter and velocity errors of less than 0.02 m/s in each axis. The second test case shows the position errors grow to approximately 47.5 meters and the velocity errors grow to 0.13 m/s during a ten minute GPS outage. Finally, the third test case shows that the GPS/INS EKF performance is not significantly degraded by GPS signal blockage due to the ISS during a simulated rendezvous with the ISS.

Original languageEnglish (US)
Title of host publicationAIAA Guidance, Navigation, and Control Conference and Exhibit
StatePublished - 2003
Externally publishedYes
EventAIAA Guidance, Navigation, and Control Conference and Exhibit 2003 - Austin, TX, United States
Duration: Aug 11 2003Aug 14 2003

Other

OtherAIAA Guidance, Navigation, and Control Conference and Exhibit 2003
CountryUnited States
CityAustin, TX
Period8/11/038/14/03

Fingerprint

Space stations
Kalman filters
Spacecraft
Global positioning system
Navigation
Reentry
Landing
Orbits
Launch vehicles
Space shuttles
Sensors
Extended Kalman filters
Navigation systems
Outages

ASJC Scopus subject areas

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

Cite this

Gaylor, D., & Lightsey, E. G. (2003). GPS/INS Kalman filter design for spacecraft operating in the proximity of the international space station. In AIAA Guidance, Navigation, and Control Conference and Exhibit

GPS/INS Kalman filter design for spacecraft operating in the proximity of the international space station. / Gaylor, David; Lightsey, E. Glenn.

AIAA Guidance, Navigation, and Control Conference and Exhibit. 2003.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Gaylor, D & Lightsey, EG 2003, GPS/INS Kalman filter design for spacecraft operating in the proximity of the international space station. in AIAA Guidance, Navigation, and Control Conference and Exhibit. AIAA Guidance, Navigation, and Control Conference and Exhibit 2003, Austin, TX, United States, 8/11/03.
Gaylor D, Lightsey EG. GPS/INS Kalman filter design for spacecraft operating in the proximity of the international space station. In AIAA Guidance, Navigation, and Control Conference and Exhibit. 2003
Gaylor, David ; Lightsey, E. Glenn. / GPS/INS Kalman filter design for spacecraft operating in the proximity of the international space station. AIAA Guidance, Navigation, and Control Conference and Exhibit. 2003.
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