Development of On-board orbit Development of On-board orbit determination system for Low determination system for Low Earth Orbit (LEO) satellite Using Earth Orbit (LEO) satellite Using Global Navigation Satellite Global Navigation Satellite System (GNSS) Receiver System (GNSS) Receiver Presented by, Mr. Sandip Aghav Mr. Sandip Aghav Department of Electronic Science, Department of Electronic Science, University of Pune, University of Pune, Pune Pune
25
Embed
Presented by, Mr. Sandip Aghav Department of Electronic Science, University of Pune, Pune
Development of On-board orbit determination system for Low Earth Orbit (LEO) satellite Using Global Navigation Satellite System (GNSS) Receiver. Presented by, Mr. Sandip Aghav Department of Electronic Science, University of Pune, Pune. Orbit Determination Techniques. Ground Based. - PowerPoint PPT Presentation
This document is posted to help you gain knowledge. Please leave a comment to let me know what you think about it! Share it to your friends and learn new things together.
Transcript
Development of On-board orbit Development of On-board orbit determination system for Low Earth Orbit determination system for Low Earth Orbit (LEO) satellite Using Global Navigation (LEO) satellite Using Global Navigation Satellite System (GNSS) ReceiverSatellite System (GNSS) Receiver
Presented by,
Mr. Sandip AghavMr. Sandip Aghav
Department of Electronic Science,Department of Electronic Science,
University of Pune,University of Pune,
PunePune
Introduction
Doppler Measurement
Orbit Determination Techniques
Ground Based
Laser Ranging
Sun sensor, star sensor
Space borne
GNSS Measurements
Classification of Orbit determination techniques
Problem Definition
A method is proposed to use onboard GPS Receiver stand-alone with a direct measurement of position, velocity and acceleration data for orbit determination instead of using differential technique and combined observational technique.
Use of Simplified force models for orbit determination and reduce the extra Burdon from hardware.
Fig:1: Orbital Elements with Pure Keplerian Equations
Fig:2: Orbital Elements with J2 Effect
Fig: Effect of Secular variation J2 ,J3, J4 on orbit geometry
-1-0.5
00.5
1
x 104
-1-0.5
0
0.51
x 104
-4000
-2000
0
2000
4000
-1-0.5
00.5
1
x 104
-1
-0.5
0
0.5
1
x 104
-4000
-2000
0
2000
4000
-1-0.5
00.5
1
x 104
-1
-0.5
0
0.5
1
x 104
-4000
-2000
0
2000
4000
x[Km]y[Km]
z[km
]
(a) Pure Keplerian
(b) J2
(a) J2,J3,J4
Conclusion Orbit Integration using Kepler’s and Newton’s Laws of
motion. GPS RINEX data file decoding. Extended Kalman Filter Representation Calculation of Jacobian Matrix for system equation. Calculation of Jacobian Matrix for system equation from
actual measurement (RINEX data file). Calculation of System Matrix. Calculation of initial Noise matrix and error covariance