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Track TDRS 6 Satellite in Real Time

Detailed information about TDRS 6 satellite

Designator id: 1993-003B

Description of TDRS 6 Satellite:

TDRS-F was the fifth successful launch of the Tracking and Data Relay Satellite series. TDRS-F was used in combination with other TDRS spacecraft and a ground communications system to form the Tracking and Data Relay Satellite System (TDRSS). The objective of the TDRSS program was to provide and maintain improved tracking and data acquisition services to spacecraft in low-Earth orbit. In order to fulfill this objective, TDRSS required at least two fully operational TDRS in orbit with one or more additional spacecraft serving as system spares. Each TDRS was a three-axis, momentum-biased satellite. The bus section of the spacecraft was hexagonal with an approximate diameter of 3 m. Power was provided by two opposing, three-section solar array panels, 4.0 x 3.8 m in dimension, at the end of 3.25 m booms. Perpendicular to the solar arrays were the two 4.9 m diameter, K- and S-band, single-access (SA) antennae. With the solar panels and SA antennae deployed, TDRS measured 17.3 x 14.2 m. TDRS was comprised of three functional modules: payload, spacecraft, and antenna. The payload module consisted of two single-access compartments, the multiple access antenna platform, and a main payload module. The main payload module had six panels which formed an integral part of the main bus structure and housed the principle elements of the TDRS payload. The spacecraft module contained the thermal control, electrical power, attitude control, propulsion, and tracking, telemetry, and command systems. The antenna module consisted of the two SA dish antennae, the 2.0 m K-band Space-to-Ground Link (SGL) antenna, and, on the bus of the spacecraft, the 30 helical element, multiple access (MA) antenna array, a C-band antenna, and an S-band omnidirectional SGL antenna. In addition to changes made to previous TDRS spacecraft subsequent to TDRS-A, TDRS-F had its S-band return parametric amplifiers replaced with solid-state, low-noise amplifiers.

Technical data:

Launch Date: 1993-01-13
Launch Vehicle: Shuttle
Launch Site: Cape Canaveral, United States
Mass: 2108.0 kg
Nominal Power: 1700.0 W
Funding Agencies:

NASA-Office of Tracking and Data Acquisition (United States)



Source: Nasa

Two Line Element Set (TLE):
1 22314U 93003B   12339.13962463 -.00000279  00000-0  10000-3 0  2041
2 22314 011.8441 043.2076 0008905 315.1545 063.0952 01.00273610 72881

Last TLE update on :2012-12-04

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