Long March 2E

Rendering of Long March 2E
Function	Carrier rocket
Manufacturer	CALT
Country of origin	China
Size
Height	49.70 metres (163.1 ft)[1]
Diameter	3.35 metres (11.0 ft)[1]
Mass	460,000 kilograms (1,010,000 lb)[1]
Stages	3
Capacity
Payload to LEO
Mass	9,500 kilograms (20,900 lb)[1]
Payload to Geosynchronous transfer orbit
Mass	3,500 kilograms (7,700 lb)[1]
Associated rockets
Family	Long March
Derivative work	Long March 2F
Launch history
Status	Retired
Launch sites	XSLC, LA-2
Total launches	7
Success(es)	4
Failure(s)	1
Partial failure(s)	2
First flight	16 July 1990
Last flight	28 December 1995
Boosters
No. boosters	4
Height	15.33 metres (50.3 ft)
Diameter	2.25 metres (7 ft 5 in)
Empty mass	3,000 kilograms (6,600 lb)
Gross mass	40,754 kilograms (89,847 lb)
Propellant mass	37,754 kilograms (83,233 lb)
Powered by	1 YF-20B
Maximum thrust	740.4 kilonewtons (166,400 lbf)
Specific impulse	2,556.2 metres per second (260.66 s)
Burn time	127 seconds
Propellant	N2O4 / UDMH
First stage
Height	28.47 metres (93.4 ft)
Diameter	3.35 metres (11.0 ft)
Empty mass	12,550 kilograms (27,670 lb)
Gross mass	198,825 kilograms (438,334 lb)
Propellant mass	186,280 kilograms (410,680 lb)
Powered by	4 YF-20B
Maximum thrust	2,961.6 kilonewtons (665,800 lbf)
Specific impulse	2,556.2 metres per second (260.66 s)
Burn time	160 seconds
Propellant	N2O4 / UDMH
Second stage
Height	14.22 metres (46.7 ft)
Diameter	3.35 metres (11.0 ft)
Empty mass	4,955 kilograms (10,924 lb)
Gross mass	91,414 kilograms (201,533 lb)
Propellant mass	84,759 kilograms (186,862 lb)
Powered by	1 YF-24B (1 x YF-22B (main)) (4 x YF-23B (vernier))
Maximum thrust	738.4 kilonewtons (166,000 lbf) (main) 47.1 kilonewtons (10,600 lbf) (vernier)
Specific impulse	2,922.4 metres per second (298.00 s) (main) 2,834.1 metres per second (289.00 s) (vernier)
Burn time	301 seconds
Propellant	N2O4 / UDMH
Third stage – EPKM (optional)
Height	2.936 metres (9 ft 7.6 in)
Diameter	1.7 metres (5 ft 7 in)
Empty mass	557 kilograms (1,228 lb)
Gross mass	6,001 kilograms (13,230 lb)
Propellant mass	5,444 kilograms (12,002 lb)
Powered by	1 FG-46
Maximum thrust	190 kilonewtons (43,000 lbf)
Specific impulse	2,870 metres per second (293 s)
Burn time	87 seconds
Propellant	HTPB
[edit on Wikidata]

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.