![]() 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 |
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.
© MMXXIII Rich X Search. We shall prevail. All rights reserved. Rich X Search