Delta B
Delta B prior to the launch of TIROS-8 | |
| Function | Expendable launch system |
|---|---|
| Country of origin | United States |
| Capacity | |
| Payload to LEO | |
| Altitude | 350 nautical miles (650 km; 400 mi) |
| Mass | 800 pounds (360 kg) |
| Payload to Earth escape trajectory | |
| Mass | 130 pounds (59 kg) |
| Launch history | |
| Status | Retired |
| Launch sites | Cape Canaveral LC-17 |
| Total launches | 9 |
| Success(es) | 8 |
| Failure(s) | 1 |
| First flight | 13 December 1962 |
| Last flight | 19 March 1964 |
The Delta B, or Thor-Delta B was an American expendable launch system used for nine orbital launches between 1962 and 1964. A derivative of the Thor-Delta, it was a member of the Delta family of rockets.
The first stage was a Thor missile in the DM-21 configuration, and the second stage was the AJ10-118, which was derived from the earlier Delta-A. An Altair solid rocket motor was used as a third stage.
All nine launches occurred from Cape Canaveral Air Force Station Launch Complex 17. Most of the launches carried communications satellites, including Syncom-1 and Syncom-2. Syncom-1 was intended to be the first satellite to be placed into a geosynchronous orbit, however the spacecraft malfunctioned prior to reaching this orbit. Syncom-2 subsequently became the first geosynchronous satellite, and was placed at 55° west of the Greenwich Meridian. The final launch failed due to third stage underperformance, all other launches were successful.