PICOSAT 1 & 2 [TETHERE
Satellite information PICOSAT 1 & 2 [TETHERE
| Spacetrack Directory Name | PICOSAT 1 & 2 [TETHERE |
| Follow PICOSAT 1 & 2 [TETHERE | PICOSAT 1 & 2 [TETHERE Tracker |
| Pass predictions PICOSAT 1 & 2 [TETHERE | Pass predictions PICOSAT 1 & 2 [TETHERE |
| Orbit launches |
2000-01-27 (26 years ago)
|
| Days in orbit | 9707 |
| Country/organisation of origin | USA (US) |
| Starting point | AFWTR (Vandenberg Air Force Base, USA) |
| WWW | Here |
| Perigee | 725 km |
| Apogee | 770 km |
| Orbit slope (inclination) | 100.21° |
| Laps per day | 14 |
| Height PICOSAT 1 & 2 [TETHERE | 744.67 km |
Additional information PICOSAT 1 & 2 [TETHERE
To demonstrate the basic functional elements of a low-power LEO ?swarm? or formation PICOSAT array. To communicate from space using node-type radios and to report the results of MEMS-switched tests. Validate MEMS radio frequency switches. The two orbiting picosats are to be tethered because they will communicate via micropower radios. The tether will keep them within range of each other for crosslink purposes.
satellite PICOSAT 1 & 2 [TETHERE Date of exalting 27.01.2000y. Average height of ISS PICOSAT 1 & 2 [TETHERE hundred 744.67 km. Average velocity PICOSAT 1 & 2 [TETHERE is 26942.23 km/h. Inclination PICOSAT 1 & 2 [TETHERE satellite 100.21°.TLE
Average orbit height PICOSAT 1 & 2 [TETHERE
Average velocity PICOSAT 1 & 2 [TETHERE
Average inclination PICOSAT 1 & 2 [TETHERE
Mean right ascension of the ascending node (RAAN) PICOSAT 1 & 2 [TETHERE
Mean argument of perigee PICOSAT 1 & 2 [TETHERE
Mean semi-major axis of the orbit PICOSAT 1 & 2 [TETHERE
Mean orbital eccentricity PICOSAT 1 & 2 [TETHERE
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