Function | Orbital launch vehicle |
---|---|
Manufacturer |
Boeing (design, manufacturing and assembly) Mitsubishi Heavy Industries (extended kerosene tank and H-II-based upper stage manufacturing) |
Country of origin | United States |
Size | |
Height | 35 m (115 ft) |
Diameter | 4 m (13 ft) |
Mass | 301,450 kg (664,580 lb) |
Stages | 2 |
Capacity | |
Payload to LEO | |
Mass | 8,290 kg (18,280 lb) [1] |
Payload to GTO | |
Mass | 3,810 kg (8,400 lb) [1] |
Associated rockets | |
Family | Delta |
Launch history | |
Status | Retired |
Launch sites | SLC-17, Cape Canaveral |
Total launches | 3 |
Success(es) | 0 |
Failure(s) | 2 |
Partial failure(s) | 1 |
First flight | August 26, 1998 |
Last flight | August 23, 2000 |
Boosters | |
No. boosters | 9 GEM 46 |
Maximum thrust | 628.3 kN (141,200 lbf) |
Specific impulse | 273 seconds (2.68 km/s) |
Burn time | 75 seconds |
Propellant | HTPB mix, similar to PBAN |
First stage | |
Powered by | 1 Rocketdyne RS-27A |
Maximum thrust | 1,085.79 kN (244,100 lbf) |
Specific impulse | 254 seconds (2.49 km/s) |
Burn time | 260 seconds [2] |
Propellant | LOX/ RP-1 |
Second stage | |
Powered by | 1 Pratt & Whitney RL10B |
Maximum thrust | 110.03 kN (24,740 lbf) |
Specific impulse | 462 seconds (4.53 km/s) [3] |
Burn time | 700 seconds [2] |
Propellant | LOX/ LH2 |
Third stage (Optional) | |
Powered by | 1 Thiokol Star 48B |
Maximum thrust | 66.723 kN (15,000 lbf) |
Specific impulse | 286 seconds (2.80 km/s) |
Burn time | 87 seconds |
Propellant | HTPB |
Delta III was an expendable launch vehicle made by Boeing. The first Delta III launch was on August 26, 1998. [4] Of its three flights, the first two were failures, and the third, though declared successful, reached the low end of its targeted orbit range and carried only a dummy (inert) payload. The Delta III could deliver up to 8,400 pounds (3,800 kilograms) to geostationary transfer orbit, twice the payload of its predecessor, the Delta II. [1] Under the four-digit designation system from earlier Delta rockets, the Delta III is classified as the Delta 8930.
Flight Number | Date / time ( UTC) | Rocket Configuration |
Launch site | Payload | Payload mass | Orbit | Customer | Launch outcome |
---|---|---|---|---|---|---|---|---|
1 | August 27, 1998 01:17 |
Delta III 8930 | CCAFS SLC-17B | Galaxy 10 | 1,543 pounds (700 kilograms) | GTO | PanAmSat / Intelsat | Failure |
Maiden flight of Delta III 8930, Destroyed by range safety after control problems and depletion of hydraulic fluid, Communications satellite. | ||||||||
2 | May 5, 1999 01:00 |
Delta III 8930 | CCAFS SLC-17B | Orion 3 | 9,480 pounds (4,300 kilograms) | GTO | Loral | Failure [5] |
Second stage engine failure. Payload placed in too low a LEO, Loral declared satellite lost. Communications satellite. | ||||||||
3 | August 23, 2000 11:05 |
Delta III 8930 | CCAFS SLC-17B | DM-F3 | 9,663 pounds (4,383 kilograms) | GTO | US Air Force | Partial failure [6] |
Reached lower than planned orbit, final flight of Delta III 8930, Demosat. |
{{
cite web}}
: CS1 maint: unfit URL (
link)
Function | Orbital launch vehicle |
---|---|
Manufacturer |
Boeing (design, manufacturing and assembly) Mitsubishi Heavy Industries (extended kerosene tank and H-II-based upper stage manufacturing) |
Country of origin | United States |
Size | |
Height | 35 m (115 ft) |
Diameter | 4 m (13 ft) |
Mass | 301,450 kg (664,580 lb) |
Stages | 2 |
Capacity | |
Payload to LEO | |
Mass | 8,290 kg (18,280 lb) [1] |
Payload to GTO | |
Mass | 3,810 kg (8,400 lb) [1] |
Associated rockets | |
Family | Delta |
Launch history | |
Status | Retired |
Launch sites | SLC-17, Cape Canaveral |
Total launches | 3 |
Success(es) | 0 |
Failure(s) | 2 |
Partial failure(s) | 1 |
First flight | August 26, 1998 |
Last flight | August 23, 2000 |
Boosters | |
No. boosters | 9 GEM 46 |
Maximum thrust | 628.3 kN (141,200 lbf) |
Specific impulse | 273 seconds (2.68 km/s) |
Burn time | 75 seconds |
Propellant | HTPB mix, similar to PBAN |
First stage | |
Powered by | 1 Rocketdyne RS-27A |
Maximum thrust | 1,085.79 kN (244,100 lbf) |
Specific impulse | 254 seconds (2.49 km/s) |
Burn time | 260 seconds [2] |
Propellant | LOX/ RP-1 |
Second stage | |
Powered by | 1 Pratt & Whitney RL10B |
Maximum thrust | 110.03 kN (24,740 lbf) |
Specific impulse | 462 seconds (4.53 km/s) [3] |
Burn time | 700 seconds [2] |
Propellant | LOX/ LH2 |
Third stage (Optional) | |
Powered by | 1 Thiokol Star 48B |
Maximum thrust | 66.723 kN (15,000 lbf) |
Specific impulse | 286 seconds (2.80 km/s) |
Burn time | 87 seconds |
Propellant | HTPB |
Delta III was an expendable launch vehicle made by Boeing. The first Delta III launch was on August 26, 1998. [4] Of its three flights, the first two were failures, and the third, though declared successful, reached the low end of its targeted orbit range and carried only a dummy (inert) payload. The Delta III could deliver up to 8,400 pounds (3,800 kilograms) to geostationary transfer orbit, twice the payload of its predecessor, the Delta II. [1] Under the four-digit designation system from earlier Delta rockets, the Delta III is classified as the Delta 8930.
Flight Number | Date / time ( UTC) | Rocket Configuration |
Launch site | Payload | Payload mass | Orbit | Customer | Launch outcome |
---|---|---|---|---|---|---|---|---|
1 | August 27, 1998 01:17 |
Delta III 8930 | CCAFS SLC-17B | Galaxy 10 | 1,543 pounds (700 kilograms) | GTO | PanAmSat / Intelsat | Failure |
Maiden flight of Delta III 8930, Destroyed by range safety after control problems and depletion of hydraulic fluid, Communications satellite. | ||||||||
2 | May 5, 1999 01:00 |
Delta III 8930 | CCAFS SLC-17B | Orion 3 | 9,480 pounds (4,300 kilograms) | GTO | Loral | Failure [5] |
Second stage engine failure. Payload placed in too low a LEO, Loral declared satellite lost. Communications satellite. | ||||||||
3 | August 23, 2000 11:05 |
Delta III 8930 | CCAFS SLC-17B | DM-F3 | 9,663 pounds (4,383 kilograms) | GTO | US Air Force | Partial failure [6] |
Reached lower than planned orbit, final flight of Delta III 8930, Demosat. |
{{
cite web}}
: CS1 maint: unfit URL (
link)