Diadème (D 1C, 1D)
Diadème [CNES]
Diadème 1 and Diadème 2 were launched one week apart in February 1967 into elliptical orbits. Both Diadème satellites were geodetic missions. These satellites are magnetically stabilized which limit their trackability in the southern hemisphere. Diademe has the following instrumentation onboard:
- Dual frequency Doppler transmitters
- Retroreflector array consisting of 2 flattened truncated cones with 77 cube corners per cone for a total of 144 cube corners.
| Nation: | France |
|---|---|
| Type / Application: | Geodesy |
| Operator: | CNES |
| Contractors: | CNES |
| Equipment: | 144 retro reflectors |
| Configuration: | |
| Propulsion: | None |
| Power: | 4 deployable fixed solar arrays, batteries |
| Lifetime: | |
| Mass: | 23 kg |
| Orbit: | 569 km × 1350 km, 39.98° (#1); 591 km × 1881 km, 39.45° (#2) |
| Satellite | Date | LS | Launch Vehicle | Remarks | |
|---|---|---|---|---|---|
| Diadème 1 (D 1C) | 08.02.1967 | Ha | P | Diamant-A | |
| Diadème 2 (D 1D) | 15.02.1967 | Ha | Diamant-A |
