Share Email Print
cover

Proceedings Paper

Effects of solar radio flux on payload pointing variation for the Earth observation spacecraft
Author(s): Hu Jiang; Lei Deng; Jinpei Yu; Zhiming Cai; Yuesheng Jiang
Format Member Price Non-Member Price
PDF $17.00 $21.00

Paper Abstract

For most Earth observation spacecrafts (EOS), repeating sun-synchronous orbit is a preferred working orbit for the Earth observation spacecraft. Repeating ground trace can provide an ideal observation geometry for space-crafts devoted to Earth observation missions. Sun-synchronous orbit can provide an ideal supply of solar power for the space-crafts. Payloads for EOS usually need demanding pointing stability. One of the main factors which may lead to the variation of payload pointing is the solar radio flux. In different year, the solar radio flux varies. This paper focuses on the characteristics of payload pointing stability due to the variation of the solar radio flux. As historic dataset, solar radio flux shows periodic change of 11 years. In 11 years, solar radio flux experiences the maximal and the minimal solar flux units (sfu). In the case of the payload beam boresight, the simulation results indicate that during the year of severe solar activity with 230sfu, 4 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ±2 deg, and that during the year of severe solar activity with 230 sfu, 2 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ±0.5 deg. And the simulations also indicate that during the year of average solar activity with 150sfu, 4 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ±0.5 deg, and that during the year of average solar activity with 150sfu, 2 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ±0.1 deg; In the case of the payload beam edge, the simulation results indicate that during the year of severe solar activity with 230sfu, 4 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ±5 deg, and that during the year of severe solar activity with 230 sfu, 2 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ± deg. And the simulations also indicate that during the year of average solar activity with 150sfu, 4 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ±2 deg, and that during the year of average solar activity with 150sfu, 2 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ±0.5 deg; The simulations provide an effective constraint of orbit maneuver scenario planning, and further boost the feasibility of space-crafts engineering.

Paper Details

Date Published: 18 December 2019
PDF: 5 pages
Proc. SPIE 11338, AOPC 2019: Optical Sensing and Imaging Technology, 1133802 (18 December 2019); doi: 10.1117/12.2538251
Show Author Affiliations
Hu Jiang, Shanghai Engineering Ctr. for Microsatellites (China)
Innovation Academy for Microsatellites (China)
Key Lab. of Microsatellites (China)
Lei Deng, Shanghai Engineering Ctr. for Microsatellites (China)
Innovation Academy for Microsatellites (China)
Key Lab. of Microsatellites (China)
Jinpei Yu, Shanghai Engineering Ctr. for Microsatellites (China)
Innovation Academy for Microsatellites (China)
Key Lab. of Microsatellites (China)
Zhiming Cai, Shanghai Engineering Ctr. for Microsatellites (China)
Innovation Academy for Microsatellites (China)
Key Lab. of Microsatellites (China)
Yuesheng Jiang, Shanghai Polytechnic Univ. (China)


Published in SPIE Proceedings Vol. 11338:
AOPC 2019: Optical Sensing and Imaging Technology
John E. Greivenkamp; Jun Tanida; Yadong Jiang; HaiMei Gong; Jin Lu; Dong Liu, Editor(s)

© SPIE. Terms of Use
Back to Top
PREMIUM CONTENT
Sign in to read the full article
Create a free SPIE account to get access to
premium articles and original research
Forgot your username?
close_icon_gray