Delta 4000

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.

This article is about the rocket designated Delta 4000 under the old designation system. For the new system, see Delta IV.
Delta 4000
Launch of a Delta 4925
FunctionLaunch vehicle
ManufacturerMcDonnell Douglas
Country of originUnited States
Cost per launchUS$34.22 million in 1985 (4925 variant)[1] (US$79.99 million in 2018)
Size
Height34 m (112 ft)
Diameter2.44 m (8 ft 0 in)
Mass200,740 kg (442,560 lb)
Stages2 or 3
Capacity
Payload to LEO
Mass3,400 kg (7,500 lb)
Payload to GTO
Mass1,200 kg (2,600 lb)
Associated rockets
FamilyDelta
ComparableDelta 5000, Delta II
Launch history
StatusRetired
Launch sitesCape Canaveral SLC-17
Vandenberg AFB SLC-2W
Total launches2
Success(es)2
First flight28 August 1989
Last flight12 June 1990
Boosters – Castor 4A
No. boosters9
Height9.12 m (29.9 ft)
Diameter1.02 m (3 ft 4 in)
Empty mass1,529 kg (3,371 lb)
Gross mass11,743 kg (25,889 lb)
Powered bySolid
Maximum thrust478.3 kN (107,500 lbf)
Specific impulse
    • Sea level: 237 seconds
    • Vacuum: 266 seconds
Burn time56 s
First stage – Thor/Delta ELT
Height22.4 m (73 ft)
Diameter2.44 m (8 ft 0 in)
Empty mass4,059 kg (8,949 lb)
Gross mass84,067 kg (185,336 lb)
Powered by1 MB-3
Maximum thrust760.6 kN (171,000 lbf)
Specific impulse
    • Sea level: 250 seconds
    • Vacuum: 285 seconds
Burn time222 s
PropellantLOX / RP-1
Second stage – Delta K
Height5.89 m (19.3 ft)
Diameter2.44 m (8 ft 0 in)
Empty mass950 kg (2,090 lb)
Gross mass6,954 kg (15,331 lb)
Powered by1 AJ10-118K
Maximum thrust43.6 kN (9,800 lbf)
Specific impulse319 s
Burn time431 s
PropellantN2O4 /Aerozine 50
Third stage – PAM-D (optional)
Height2.03 m (6 ft 8 in)
Diameter1.25 m (4 ft 1 in)
Empty mass128 kg (282 lb)
Gross mass2,137 kg (4,711 lb)
Powered byStar 48B
Maximum thrust66 kN (15,000 lbf)
Specific impulse286 s
Burn time87 s

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.[2][3][4]

References
  1. "Delta 4000". Archived from the original on September 16, 2016. Retrieved September 8, 2018.
  2. Wade, Mark. "Delta". Archived from the original on 2008-07-24.
  3. Krebs, Gunter. "Thor Family". Gunter's Space Page. Archived from the original on 2007-08-06. Retrieved 2021-12-21.
  4. "Delta 4000". Archived from the original on September 16, 2016. Retrieved September 8, 2018.
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