CubeSail
Mission typeTechnology
Websitewww.surrey.ac.uk/surrey-space-centre/missions/cubesail
Mission duration1 year (planned)
Spacecraft properties
Spacecraft type3U CubeSat
ManufacturerSurrey Satellite Technology / Astrium
BOL mass3 kg (6.6 lb)[1]
DimensionsSail: 5 m × 5 m
Bus: 10 cm x 10 cm x 34 cm
Start of mission
Launch dateTBD
Orbital parameters
Reference systemGeocentric
RegimeLow Earth orbit
 

CubeSail is a proposed nanosatellite project by the Surrey Space Centre (SSC) in England. The spacecraft is to be a 3U CubeSat propelled by a 25 m² solar sail. The project is financed and technically supported by aerospace manufacturers Astrium and Surrey Satellite Technology.

The first successful solar sail spacecraft was the Japanese IKAROS mission, launched on 21 May 2010.[2][3][4]

Overview

The project is further developing technologies first tested on their STRaND-1 CubeSat, launched in February 2013.[5] CubeSail will deploy a 25 m2 solar sail, which will be used to demonstrate the propulsive effect of solar radiation pressure and the de-orbiting capabilities of the sail as a drag augmentation device.[6][7]

Attitude control

CubeSail will be a three-axis stabilised solar sail satellite.[5] Attitude control (orientation) is necessary because the orientation of the sail relative to the Sun direction will determine the propulsion force. Full three-axis attitude control will be performed by means of a centre of mass/centre of pressure offset technique, complemented by three magnetorquers and a reaction wheel.[5] Attitude control can be enhanced by using the solar radiation pressure force on the sail to generate rotation torques.[8] The radiation pressure can also be used to induce a change of altitude as well as orbital inclination.[8]

The spacecraft will be deployed in a low Earth orbit (800 km altitude) on a Sun-synchronous orbit.[8]

Configuration

The CubeSail nanosatellite is a CubeSat of the 3U format.[9] The satellite bus occupies approximately 1U, and the remaining 2U house the two-axis translation stage and sail-deployment subsystem.[9]

Objectives

The objectives of the CubeSail mission are to demonstrate the concept of solar sail propulsion of a 3-axis stabilised 25 m2 solar sail for one year while in low Earth orbit; and to demonstrate the use of gossamer structures (very light gauze-like fabric) as a drag augmentation device for satellite de-orbiting.[5]

See also

References

  1. ↑ CubeSail: A low cost CubeSat based solar sail demonstration mission. V. Lappas, et al. Advances in Space Research. vol 48, issue, 11. 1 December 2011.pp: 1890-1901. doi:10.1016/j.asr.2011.05.033
  2. ↑ Stephen Clark (20 May 2010). "H-2A Launch Report – Mission Status Center". Spaceflight Now. Retrieved 21 May 2010.
  3. ↑ Samantha Harvey (21 May 2010). "Solar System Exploration: Missions: By Target: Venus: Future: Akatsuki". NASA. Archived from the original on 10 April 2010. Retrieved 21 May 2010.
  4. ↑ "Launch Day of the H-IIA Launch Vehicle No. 17(H-IIA F17)". JAXA. 3 March 2010. Archived from the original on 3 June 2013. Retrieved 7 May 2010.
  5. 1 2 3 4 "CUBESAIL". University of Surrey. Surrey Space Center, UK. 2016. Archived from the original on 2017-09-25. Retrieved 2017-09-24.
  6. ↑ Surrey Space Centre – UK CubeSail Satellite. AMSAT-UK. 11 July 2014.
  7. ↑ CubeSail Archived 2019-07-06 at the Wayback Machine. University of Surrey. Accessed on 6 July 2019.
  8. 1 2 3 CubeSail - Sailing Archived 2017-09-24 at the Wayback Machine. University of Surrey, UK
  9. 1 2 CubeSail - Satellite Archived 2017-09-24 at the Wayback Machine. University of Surrey, UK
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