English (United Kingdom)

https://curated-unify.zendy.io/wp-json/zendy-region/v1/featured_content/oa?rat=en

https://curated-unify.zendy.io/wp-json/zendy-region/v1/highlighted_journal/

Global: Zendy Plus annual

Presents the access of premium content as premium feature

Premium Content

Presents the keyphrase highlighting as premium feature

Keyphrase Highlighting

Presents the summarisation as premium feature

Summarisation

Insights

Presents the pdf analysis as premium feature

PDF Analysis

Presents the zaia usage as premium feature

ZAIA

Global: Zendy Plus monthly

Global: Zendy Tools annual

Global: Zendy Tools monthly

Global: Zendy Free Plan

Attitude estimation or determination is a fundamental task for satellites toremain effectively operational. This task is furthermore complicated on smallsatellites by the limited space and computational power available on-board.This, coupled with a usually low budget, restricts small satellites from usinghigh precision sensors for its especially important task of attitudeestimation. On top of this, small satellites, on account of their size andweight, are comparatively more sensitive to environmental or orbitaldisturbances as compared to their larger counterparts. Magnetic disturbanceforms the major contributor to orbital disturbances on small satellites inLower Earth Orbits (LEO). This magnetic disturbance depends on the ResidualMagnetic Moment (RMM) of the satellite itself, which for higher accuracy shouldbe determined in real-time. This paper presents a method for in-orbitestimation of the satellite magnetic dipole using a Random Walk Model in orderto circumnavigate the inaccuracy arising due to unknown orbital magneticdisturbances. It is also ensured that the dipole as well as attitude estimationof the satellite is done using only a magnetometer as the sensor.

Attitude and In-orbit Residual Magnetic Moment Estimation of Small Satellites Using only Magnetometer