| 词条 | Delta 4000 |
| 释义 |
|image = Delta 4925.jpg |caption = Launch of a Delta 4925 |imsize = 150px |name = Delta 4000 |function = Launch vehicle |manufacturer = McDonnell Douglas |country-origin = United States |pcost = |cpl = {{US$|34.22 million}} in 1985 (4925 variant)[1] |alt-cpl = {{US$|79.99 million}} in 2018 |height = {{convert|34|m|abbr=on}} |diameter = {{convert|2.44|m|abbr=on}} |width = |mass = {{convert|200,740|kg|abbr=on}} |stages = 2 or 3 |capacities = |location = LEO |kilos = {{convert|3,400|kg|abbr=on}} }} {{Infobox rocket/payload|location = GTO |kilos = {{convert|1,200|kg|abbr=on}} |family = Delta |derivatives = |comparable = Delta 5000, Delta II |status = Retired |sites = Cape Canaveral SLC-17 Vandenberg AFB SLC-2W |launches = 2 |success = 2 |other_outcome = |first = 28 August 1989 |last = 12 June 1990 |only = |payloads = |stagedata = |type = booster |diff = |stageno = |name = Castor 4A |number = 9 |length = {{convert|9.12|m|abbr=on}} |diameter = {{convert|1.02|m|abbr=on}} |width = |empty = {{convert|1,529|kg|abbr=on}} |gross = {{convert|11,743|kg|abbr=on}} |propmass = |engines = Solid |solid = yes |thrust = {{convert|478.3|kN|abbr=on}} |total = |SI = {{plainlist|
}} |burntime = 56 s |propellant = Aluminum fuel, ammonium perchlorate oxidizer in an HTPB binder }} {{Infobox rocket/stage|type = stage |diff = |stageno = First |name = Thor/Delta ELT |number = |length = {{convert|22.4|m|abbr=on}} |diameter = {{convert|2.44|m|abbr=on}} |width = |empty = {{convert|4,059|kg|abbr=on}} |gross = {{convert|84,067|kg|abbr=on}} |propmass = |engines = 1 MB-3 |solid = |thrust = {{convert|760.6|kN|abbr=on}} |total = |SI = {{plainlist|
}} |burntime = 222 s |fuel = LOX / RP-1 }} {{Infobox rocket/stage|type = stage |diff = |stageno = Second |name = Delta K |number = |length = {{convert|5.89|m|abbr=on}} |diameter = {{convert|2.44|m|abbr=on}} |width = |empty = {{convert|950|kg|abbr=on}} |gross = {{convert|6,954|kg|abbr=on}} |propmass = |engines = 1 AJ10-118K |solid = |thrust = {{convert|43.6|kN|abbr=on}} |total = |SI = 319 s |burntime = 431 s |fuel = {{N2O4}} /Aerozine 50 }} {{Infobox rocket/stage|type = stage |diff = |stageno = Third |name = PAM-D (optional) |number = |length = {{convert|2.03|m|abbr=on}} |diameter = {{convert|1.25|m|abbr=on}} |width = |empty = {{convert|128|kg|abbr=on}} |gross = {{convert|2137|kg|abbr=on}} |propmass = |engines = Star 48B |solid = yes |thrust = {{convert|66|kN|abbr=on}} |total = |SI = 286 s |burntime = 87 s |propellant = Aluminum fuel, ammonium perchlorate oxidizer in an HTPB binder }} The Delta 4000 series was an American expendable launch system which was used to conduct two orbital launches in 1989 and 1990. It was a member of the Delta family of rockets. Although several variants were put forward, only the Delta 4925 was launched. The designations used a four digit numerical code to store information on the configuration of the rocket. It was built from a combination of spare parts left over from earlier Delta rockets, which were being retired, and parts from the Delta II 6000-series, which was just entering service. The first stage was the MB-3-III powered Extended Long Tank Thor, previously flown on the 1000-series. Nine Castor-4A solid rocket boosters were attached to increase thrust at lift-off, replacing the less powerful Castor-4 boosters used on the 3000 series. The Delta-K was used as a second stage. A Star-48B PAM-D was used as a third stage, to boost payloads into geosynchronous transfer orbit. Both Delta 4000 launches occurred from Launch Complex 17B at Cape Canaveral. The first launched Marco Polo 1 for BSkyB, and the second launched INSAT 1D for the Indian Space Research Organisation. Both were successful. References{{refbegin}}
1 : Delta (rocket family) |
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