Official name DOUBLESTAR (TC-2)
Alternative name Tan Ce 2 (TC-2) (Doublestar 2)
Cospar ID 2004-029A
Norad ID 28382
Launch date 2004-07-25
Launch site TSC
Launch vehicle CZ-2C (2) CTS
Country/Organization China
Type application Science, magnetosphere
Operator CNSA, ESA
RCS size LARGE
Decay date ON ORBIT
Period (min) 569.91
Inclination (deg) 87.75
Perigee (km) 404
Apogee (km) 32380
Eccentricity 0.97535383113714
Mean motion (revs. per day) 2.52671474443333
Semi-Major axis (km) 22770.135
Raan (deg) 243.4327
Arg of perigee (deg) 209.6933
Shape Cyl + 2 Arm
Mass (kg) 343
Diameter (m) 1.4
Height (m) 2.1
Span (m^2) 10
Power Solar cells, batteries

The Double Star spacecraft, called also Tan Ce (TC) which in Chinese means ‘Probe‘, is a joint Chinese and ESA mission to study the effect of the Sun on the Earth's environment. The polar spacecraft (TC-2) will monitor the energy input from the solar wind into the polar ionosphere. The equatorial spacecraft (TC-1) will investigate the so-called substorm process, when it is in the Earth's magnetotail, and the entry of solar particle on the front side of the magnetosphere.

The geomagnetic substorm is a process by which energy is stored and released in the magnetosphere resulting in serious disturbances in the Earth environment. The two TC spacecraft located near the Earth and Cluster located further down the tail will help to locate the starting point of the substorm and the physical mechanism responsible for it.

The Double Star orbits have been designed such as to get the best conjunctions with Cluster in the key scientific regions.

Double Star's scientific objectives are to:

  • Study the magnetic reconnection at the magnetopause and in the magnetotail
  • Understand and locate the trigger mechanism for magnetospheric storms and substorms
  • Study physical processes such as particle acceleration, diffusion, injection, and up-flowing ions during storms
  • Study temporal variations of field-aligned currents and the coupling between tail current and auroral current.

The orbit of the DSP equatorial satellite (TC-1) is planned to have a perigee at 550 kilometers and apogee at 66 970 kilometers; the orbit of the DSP polar satellite (TC-2) is planned to have a perigee at 700 kilometers and apogee at 39 000 kilometers. The equatorial satellite of DSP will detect the physical processes of geospace storms in the near-Earth magnetotail and the energy transfer from the solar wind to the magnetosphere. The polar satellite of DSP will detect energy transfer from solar wind to magnetosphere via dayside magnetopause. The polar satellite of DSP will detect energy transfer from solar wind and near-earth magnetotail to polar ionosphere and upper atmosphere, as well as to detect ionised-particle transfer from ionosphere to magnetosphere.

The two DSP satellites will operate in the near-Earth equatorial region, the main active regions of magnetospheric storms, substorms, and particle events that are not covered by the current International Solar-Terrestrial Programme missions. The combination of two satellites forms an independent unique constellation-like exploring system that can explore the generation mechanism and evolving process of geospace storms. Cluster and DSP satellites will operate simultaneously and form for the first time a mini-constellation with 6 points in the magnetosphere.

Satellite COSPAR Date LS Launch Vehicle Remarks
DOUBLESTAR (TC-1) 2003-061A 2003-12-29 XSC CZ-2C (2) CTS
DOUBLESTAR (TC-2) 2004-029A 2004-07-25 TSC CZ-2C (2) CTS