DLR-Tubsat
| Names | TUBSAT-C TUBSAT |
|---|---|
| Mission type | Experimental |
| Operator | Technische Universität Berlin |
| COSPAR ID | 1999-029C |
| SATCAT no. | 25758 |
| Range | 713 kilometres (443 mi) |
| Apogee | 732 kilometres (455 mi) |
| Spacecraft properties | |
| Spacecraft | DLR-Tubsat |
| Manufacturer | Technische Universität Berlin & DLR |
| Launch mass | 45 kg (99 lb) |
| Dimensions | 32 x 32 x 32 cm |
| Power | 120 W |
| Start of mission | |
| Launch date | 06:22, May 26, 1999 (UTC) |
| Rocket | PSLV-C2 |
| Launch site | Sriharikota Launching Range |
| Contractor | ISRO |
| End of mission | |
| Deactivated | Not known |
| Orbital parameters | |
| Reference system | Sun-synchronous orbit |
| Regime | Low Earth orbit |
| Inclination | 98.36° |
| Period | 99.24 minutes |
DLR-Tubsat (a.k.a. TUBSAT) was a German remote sensing microsatellite, developed in a joint venture between Technische Universität Berlin (TUB) and German Aerospace Center (DLR). TU Berlin was responsible for the satellite bus and DLR was responsible for the payload.[1] The satellite was launched into orbit on 26 May 1999, on the fifth mission of the PSLV program PSLV-C2. The launch took place in the Sriharikota Launching Range.[2][3] The satellite had an expected life of one year.[4][5][6]
Mission objectives
The prime objective of DLR-Tubsat was to test the attitude control system (S/C attitude recovery from hibernation). The secondary objective of the mission was to test a TV camera system for disaster monitoring with the goal of the introduction of an interactive Earth observation concept, where the target is not identified in advance, a search action may be involved, or a particular target region has to be followed visually from orbit.[1][7][4]
Specifications
- Dimension: 32 x 32 x 32 cm
- Launch mass: 45 kg (99 lb)
- Solar panel: Four
- Batteries: Four NiH2
- Video camera: Three CCD
- 16 mm wide-angle camera with black-and-white chip
- 50 mm standard-angle camera with color CCD chip
- 1000 mm telephoto lens camera with black-and-white chip
- Attitude control system: Three wheel / gyro pairs
- Reaction wheels: Three
- Laser gyro: Three
- VHF / UHF TT & C system
- S band transmitter and antenna
See also
References
- ^ a b c "TUBSAT". eoportal.org. Retrieved 9 Jul 2016.
- ^ "DLR-Tubsat (COSPAR ID: 1999-029C)". NASA. Retrieved 9 Jul 2016.
- ^ "PSLV-C2". Indian Space Research Organisation. Archived from the original on 2 April 2016. Retrieved 9 Jul 2016.
- ^ a b c "Flight Experiences With DLR-Tubsat" (PDF). dlr.de. Retrieved 9 Jul 2016.
- ^ Steckling, M.; Renner, U.; Röser, H.-P. (1996). "DLR-TUBSAT, qualification of high precision attitude control in orbit". Acta Astronautica. 39 (9–12): 951. Bibcode:1996AcAau..39..951S. doi:10.1016/S0094-5765(97)00081-7.
- ^ "DLR-TUBSAT: a microsatellite for interactive Earth observation". Retrieved 9 Jul 2016.
- ^ "DLR-Tubsat". skyrocket.de. Retrieved 9 Jul 2016.