Titan 3E
| Status | retired |
|---|---|
| Rocket family | Titan |
| Country | United States |
| Manufacturer | Martin Marietta |
| Number of launches | 7 |
| First launch | 1974-02-11 |
| Last launch | 1977-09-05 |
Launches by year:
Launches:
| Launch date | Launch site | Rocket / Variant | Payload | Status |
|---|---|---|---|---|
| 1977-09-05 | Cape Canaveral | Titan 3E Titan-3E / Centaur-D1T | Star-37E / Voyager 1 | success |
| 1977-08-20 | Cape Canaveral | Titan 3E Titan-3E / Centaur-D1T | Star-37E / Voyager 2 | success |
| 1976-01-15 | Cape Canaveral | Titan 3E Titan-3E / Centaur-D1T | Helios 2 | success |
| 1975-09-09 | Cape Canaveral | Titan 3E Titan-3E / Centaur-D1T | Viking 2 | success |
| 1975-08-20 | Cape Canaveral | Titan 3E Titan-3E / Centaur-D1T | Viking 1 | success |
| 1974-12-10 | Cape Canaveral | Titan 3E Titan-3E / Centaur-D1T | Helios 1 | success |
| 1974-02-11 | Cape Canaveral | Titan 3E Titan-3E / Centaur-D1T | SPHINX / Viking-DS | failure |
Variants:
(This section is under construction)Titan 3E Titan-3E / Centaur-D1T (Titan-Centaur)
| First launch | 1974-02-11 |
|---|---|
| Upper stage | Centaur-D1T |
| Mass | 632.97 t |
| Height | 48 m |
Payload capacity:
| LEO | 15400 kg to 185 km |
|---|
Titan 3E consists of a two-stage, liquid propellant core vehicle, with two 3 m (120-inch) diameter five-segment solid rocket motors (SRMR) attached to form "Stage O". Strap-on SRMs used as the initial stage of the Titan 3 vehicles are referred to as Stage 0 in order to retain the Stage 1 and 2 nomenclature for the common core.
The core vehicle consists of two stages evolved from the Titan 2 ICBM. Both stages use storable propellants which can be left aboard the launch-ready vehicle over extended periods. The fuel is a 50/50 mixture of hydrazine and unsymmetrical dimethyl hydrazine (UDMH). The oxidizer is nitrogen tetroxide. These propellants are hypergolic, they burn spontaneously when mixed, requiring no igniter.
The Titan 3E was 30 m (98 feet) tall without the Centaur upper stage. Because of the parallel Stage 0 arrangement, Titan 3E was a broad vehicle, measuring slightly more than 9 m (30 feet) across at the extreme. The vehicle weighs approximately 620 t (1,368,000 pounds) when all stages are fully fueled.
The combination of Titan 3E and Centaur D-lT, also called Titan/Centaur. The Titan/Centaur inter stage adapter supports the Centaur atop the Titan 3E and remains with the Titan 3E at Centaur separation. The Centaur standard shroud covers the spacecraft, which is mounted to its adapter, the Centaur vehicle, and part of the interstage adapter.
Centaur D-1T was a high-energy upper stage. Liquid hydrogen/oxygen propellants and pressurized stainless steel structureprovide a top performance vehicle. The Centaur D-1 T is 9.6 m (31.5 feet) tall (including truss adapter) without the interstage adapter and Centaur standard shroud, and 3 m (10 feet) in diameter. The vehicle weighs approximately 15.4 t (34,000 pounds) when filled with propellants and has a jettison weight of approximately 2 t (4400 pounds), depending on the mission.
The Centaur standard shroud (CSS) is a large volume, biconical/cylindrical metal structure which encloses the payload, Centaur D-1T vehicle, and part of the ISA.
Titan 3E/Centaur D-1T Systems Summary, September 1973