" Delta 2000 " ( Eng. Delta-2000 ) - an American two - stage launch vehicle of the middle class, the Delta family, developed by McDonnell Douglas (now - Boeing ).
| Launch Delta 2000 | |
|---|---|
 Launch Delta 2914 J-8 | |
| General information | |
| A country |  USA |
| Family | Delta |
| Appointment | middle class booster |
| Developer | Boeing |
| Manufacturer | Boeing |
| Launch cost | USD 28.520 million (in 1985 prices) |
| Main characteristics | |
| Number of steps | 3 |
| Length (with GP) | 35 m [1] |
| Diameter | 2.44 m |
| Starting weight | 130.392 t |
| Type of fuel | liquid |
| Launch history | |
| condition | decommissioned |
| Launch locations | Vandenberg SLC-2W Canaveral SLC-17 |
| Number of starts | 44 |
| • successful | 43 |
| • unsuccessful | one |
| First start | January 19, 1974 |
| Last run | October 6, 1981 |
| Accelerator (Step 0) | |
| Number of Accelerators | 9 |
| Length | 6.04 m |
| Diameter | 0.79 m |
| Dry weight | 695 kg |
| Starting weight | 4,424 t |
| Sustainer engine | TX-354-3 |
| Thrust | 258.915 kN |
| Specific impulse | 262 s |
| Working hours | 37 s |
| First Stage - Delta Tor RS27 | |
| Length | 22.37 m |
| Diameter | 2.44 m |
| Dry weight | 4,360 t |
| Starting weight | 84.368 t |
| Sustainer engine | LRE RS-27 |
| Thrust | 1,030.218 kN |
| Specific impulse | 296 s |
| Working hours | 223 s |
| Fuel | RP-1 / LOX |
| Fuel | kerosene RP-1 |
| Oxidizing agent | liquid oxygen |
| Second stage - Delta-P (TR-201) | |
| Length | 5.97 m |
| Diameter | 1.38 m |
| Dry weight | 820 t |
| Starting weight | 5,434 t |
| Sustainer engine | LRE TR-201 |
| Thrust | 41.923 kN |
| Specific impulse | 301 s |
| Working hours | 322 s |
| Fuel | A-50 / AT |
| Fuel | Aerosin |
| Oxidizing agent | Amyl |
| Third Stage - Burner 2 | |
| Length | 0.84 m |
| Diameter | 0.66 m |
| Dry weight | 774 t |
| Starting weight | 116 t |
| Sustainer engine | RDTT Star-37 |
| Thrust | 43.551 kN |
| Specific impulse | 285 s (115 s at sea level) |
| Working hours | 42 s |
The first launch of the Delta-2000 launch vehicle was performed on January 19, 1974 at 01:38:47 UTC from the launch pad LC-17B of the Canaveral Cosmodrome, during which the Skynet IIA spacecraft was successfully launched, during the launch the Delta- launch vehicle modification was used 2313 with the number 587 / D100.
In the period from 1974 to 1975, 44 launches were made, of which one (January 19, 1974) was unsuccessful - the Skynet-2A satellite was put into the wrong orbit. The cost of each launch was estimated at an average of 28.52 million US dollars in 1985 prices and depended on the combination of the launch vehicle.
Content
Creation History
Design
Launch History
See also
- Antares
- Athena
- Comparison of mid-range launch vehicles
- Minotaur
- Museum of Aviation and Cosmonautics (Paris)
Notes
- ↑ Encyclopedia Astronautica .
Literature
Articles
Links
- Wade, Mark. Delta 2000 Encyclopedia Astronautica.