Precise attitude rate estimation using star images obtained by mission telescope for satellite missions. Issue 4 (15th February 2015)

• Record Type: Journal Article
• Authors: Inamori, Takaya; Hosonuma, Takayuki; Ikari, Satoshi; Saisutjarit, Phongsatorn; Sako, Nobutada; Nakasuka, Shinichi
• Is Part Of: Advances in space research. Volume 55:Issue 4(2015)
• Page Start: 1199
• Page End: 1210
• Publication Date: 2015-02-15
• Subjects: Space sciences -- Periodicals; Astronautics -- Periodicals; Geophysics -- Periodicals; 500.505
• DOI: 10.1016/j.asr.2014.10.008
• Languages: English
• ISSNs: 0273-1177

Abstract

<abstract xml:lang="en" abstract-type="author" id="ab005"> <title id="st045">Abstract</title> <sec> <p id="sp0005">Recently, small satellites have been employed in various satellite missions such as astronomical observation and remote sensing. During these missions, the attitudes of small satellites should be stabilized to a higher accuracy to obtain accurate science data and images. To achieve precise attitude stabilization, these small satellites should estimate their attitude rate under the strict constraints of mass, space, and cost. This research presents a new method for small satellites to precisely estimate angular rate using star blurred images by employing a mission telescope to achieve precise attitude stabilization. In this method, the angular velocity is estimated by assessing the quality of a star image, based on how blurred it appears to be. Because the proposed method utilizes existing mission devices, a satellite does not require additional precise rate sensors, which makes it easier to achieve precise stabilization given the strict constraints possessed by small satellites. The research studied the relationship between estimation accuracy and parameters used to achieve an attitude rate estimation, which has a precision greater than 1 × 10<sup>−6</sup> rad/s. The method can be applied to all attitude sensors, which use optics systems such as sun sensors and star trackers (STTs). Finally, the method is applied to the nano astrometry satellite Nano-JASMINE, and we investigate the problems that are expected to arise with real small satellites by performing numerical simulations.</p> </sec> </abstract>