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Hipparcos [ESA]

The scientific goals of the Hipparcos (High Precision Paralax Collecting Satellite) mission were the accurate measurement of the trigonometric parallaxes, proper motions, and positions of 100,000 selected stars, mostly fainter than 10th magnitude.

The spacecraft consisted of two platforms and six vertical panels, all made of aluminum honeycomb. The solar array consisted of three deployable sections. Antennas were located on the top and bottom of the spacecraft. An attitude and orbit-control subsystem ensured correct dynamic attitude control and determination during the 2.5 year planned lifetime. The spacecraft spun around its Z-axis at the rate of 12 rev/day at an angle of 43 degrees to the sun. The Z-axis rotated about the sun-satellite line at 6.4 rev/year. The spacecraft carried a single telescope which, in the focal plane, superimposed two fields of view 58 degrees apart. The attitude of the spacecraft about its center of gravity was controlled to scan the celestial sphere in a regular movement. The telescope used a system of grids, at the focal surface, composed of alternate opaque and transparent bands. Behind these grids, an image-dissector tube converted the modulated light into a sequence of photon counts from which the phase of the entire pulse train from a star could be derived. The apparent angle between two stars in the combined fields of view was obtained from the phase difference of the two star pulse trains. The telescope was an all-reflective eccentric Schmidt system. A complex mirror was employed which consisted of two mirrors tilted in opposite directions, each occupying half of the rectangular entrance pupil. The unvignetted field of view was 94 arc-min by 54 arc-min. An additional photomultiplier system, known as Tycho, viewed a beam splitter in the optical path and was used to gather photometric and astrometric data of 400,000 stars down to 11th magnitude. Measurements were made in two broad bands corresponding to B and V in the Johnson BUV system. The positions of these latter stars were to be determined to a precision of 0.05 arc-s, which is a factor of 25 less than the main mission stars. The mission was a facility type in which guest investigators propose particular research programs, and selected stars were incorporated into the overall observing strategy.

The Mage-2 apogee motor failed and left the satellite in GTO, but the mission was nevertheless successfully completed. On 15 August 1993, after more than three years of successful operations, communications with ESA's scientific satellite Hipparcos were terminated.

Nation: Europe
Type / Application: Astrometry
Operator: ESA
Contractors: Matra Marconi Space (satellite prime, payload), Alenia Spazio (co-prime: spacecraft procurement)
Propulsion: Mage-2
Power: 3 deployable fixed solar arrays, batteries
Lifetime: 2.5 years
Mass: 1025 kg
Orbit: 223 km × 35632 km, 6.8 (GEO planned)
Satellite COSPAR Date LS Launch Vehicle Remarks
Hipparcos 1989-062B 08.08.1989 Ko ELA-2 Ariane-44LP H10 with TV-Sat 2

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