Long March 2E

Rendering of Long March 2E
FunctionCarrier rocket
ManufacturerCALT
Country of originChina
Size
Height49.70 metres (163.1 ft)[1]
Diameter3.35 metres (11.0 ft)[1]
Mass460,000 kilograms (1,010,000 lb)[1]
Stages3
Capacity
Payload to LEO
Mass9,500 kilograms (20,900 lb)[1]
Payload to Geosynchronous transfer orbit
Mass3,500 kilograms (7,700 lb)[1]
Associated rockets
FamilyLong March
Derivative workLong March 2F
Launch history
StatusRetired
Launch sitesXSLC, LA-2
Total launches7
Success(es)4
Failure(s)1
Partial failure(s)2
First flight16 July 1990
Last flight28 December 1995
Boosters
No. boosters4
Height15.33 metres (50.3 ft)
Diameter2.25 metres (7 ft 5 in)
Empty mass3,000 kilograms (6,600 lb)
Gross mass40,754 kilograms (89,847 lb)
Propellant mass37,754 kilograms (83,233 lb)
Powered by1 YF-20B
Maximum thrust740.4 kilonewtons (166,400 lbf)
Specific impulse2,556.2 metres per second (260.66 s)
Burn time127 seconds
PropellantN2O4 / UDMH
First stage
Height28.47 metres (93.4 ft)
Diameter3.35 metres (11.0 ft)
Empty mass12,550 kilograms (27,670 lb)
Gross mass198,825 kilograms (438,334 lb)
Propellant mass186,280 kilograms (410,680 lb)
Powered by4 YF-20B
Maximum thrust2,961.6 kilonewtons (665,800 lbf)
Specific impulse2,556.2 metres per second (260.66 s)
Burn time160 seconds
PropellantN2O4 / UDMH
Second stage
Height14.22 metres (46.7 ft)
Diameter3.35 metres (11.0 ft)
Empty mass4,955 kilograms (10,924 lb)
Gross mass91,414 kilograms (201,533 lb)
Propellant mass84,759 kilograms (186,862 lb)
Powered by1 YF-24B
(1 x YF-22B (main))
(4 x YF-23B (vernier))
Maximum thrust738.4 kilonewtons (166,000 lbf) (main)
47.1 kilonewtons (10,600 lbf) (vernier)
Specific impulse2,922.4 metres per second (298.00 s) (main)
2,834.1 metres per second (289.00 s) (vernier)
Burn time301 seconds
PropellantN2O4 / UDMH
Third stage – EPKM (optional)
Height2.936 metres (9 ft 7.6 in)
Diameter1.7 metres (5 ft 7 in)
Empty mass557 kilograms (1,228 lb)
Gross mass6,001 kilograms (13,230 lb)
Propellant mass5,444 kilograms (12,002 lb)
Powered by1 FG-46
Maximum thrust190 kilonewtons (43,000 lbf)
Specific impulse2,870 metres per second (293 s)
Burn time87 seconds
PropellantHTPB

The Long March 2E, also known as the Chang Zheng 2E, CZ-2E and LM-2E, was a Chinese orbital carrier rocket from the Long March 2 family. The Long March 2E was a three-stage carrier rocket that was designed to launch commercial communications satellites into geosynchronous transfer orbit. Launches took place from launch complex 2 at the Xichang Satellite Launch Center.

The Long March 2E made its maiden flight on 16 July 1990. However, the rocket had compatibility flaws with the American-made satellites that caused one launch failures and one partial failure in just 7 missions. The rocket was retired on 28 December 1995 in favor of the Long March 3B. The Long March 2E forms the basis of the Long March 2F, used to launch crewed Shenzhou missions. The booster rockets have also been used on the Long March 3B and Long March 3C.

  1. ^ a b c d e Mark Wade. "CZ-2E". Encyclopedia Astronautica. Archived from the original on 2008-07-06. Retrieved 2008-05-02.

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