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LM- 2E Launch Vehicle
* History 
LM-2E
launch vehicle is developed on the basis of the flight proven technology
of LM-2C. Its conceptual design began in 1986. After its successful
test flight in July, 1990, LM-2E was introduced into the world launch
services market. At the very beginning, the LM-2E was selected by
customers to launch Australian communications satellites. After
5 successful launches with LM-2E for commercial satellites and with
necessary modifications, LM-2F, an upgraded version of LM-2E, was
developed. And on November 20,1999 it performed a successful test flight
for a China's unmanned spacecraft.
* Technical Data
LM-2E
is a 2-stage liquid propellant launch vehicle with 4 boosters trapped
on to the first stage developed on the basis of LM-2C. It is specially
dedicated for launching different spacecraft for LEO, SSO and GTO
missions.
Its launch
capability for LEO mission is 9,500 kg. With a perigee kick
motor - EPKM, its capability for GTO mission is 3,500 kg.
To accommodate mobile communications satellite market, the LM-2E
with a three-axis stabilized upper stage - ETS is capable of launching
multiple satellites into different LEO. The static envelope diameter
of the LM-2E fairing is 3,800 mm.
Note:
1. EPKM - 2E Perigee
Kick Motor
2. ETS -- 2E Top Stage
| |
1stStage |
2ndStage |
3rdStage |
| Diameter(m) |
3.35 |
3.35 |
1.7 |
| Mass of propellant(t) |
186.3 |
84.8 |
529Kg |
| Propellant |
N2O4/UDMH |
HTPB |
| Engine |
DaYF6-2
(4¡ÁYF5-1) |
DaYF20-1
(Main) "
DaYF21-1 (Vernier) |
|
| Engine Thrust (KN) |
2962
740.4¡Á4 |
742
(Main)
11.8¡Á4 (Vernier) |
|
Engine Specific
Impulse
(N¡¤Sec / kg) |
2556.5
2556.2 |
2922
(Main)
2834.1 (Vernier) |
292Kg/s |
| Booster |
4 |
| Lift-off Mass(t) |
460 |
| Overall Length (m) |
49.7 |
| Fairing Diameter
(m) |
4.20 |
Launch Record: As of December 2004
| No. |
Launch Vehicle |
Launch Date |
Payload |
Mission |
Launch Center |
Result |
| 01 |
LM-2E F01 |
Jul.16, 1990 |
DP/BADR-A |
LEO |
XSLC** |
Success |
| 02 |
LM-2E F02 |
Aug.14, 1992 |
Aussat-B1 |
LEO |
XSLC |
Success |
| 03 |
LM-2E F03 |
Dec.21, 1992 |
Optus-B2 |
LEO |
XSLC |
Failure |
| 04 |
LM-2E F04 |
Aug.28, 1994 |
Optus-B3 |
LEO |
XSLC |
Success |
| 05 |
LM-2E F05 |
Jan.26, 1995 |
APSTAR-II |
LEO |
XSLC |
Failure |
| 06 |
LM-2E F06 |
Nov.28, 1995 |
AsiaSat-2 |
LEO |
XSLC |
Success |
| 07 |
LM-2E F07 |
Dec.28, 1995 |
EchoStar-1 |
LEO |
XSLC |
Success |
| 08 |
LM-2F****
F08 |
Nov.20, 1999 |
First manned spacecraft
test flight |
LE0 |
JSLC*** |
Success |
09 |
LM-2F F09 |
Jan.10, 2001 |
Shenzhou 2 |
LEO |
JSLC |
Success |
10 |
LM-2F F10 |
Mar.25, 2002 |
Shenzhou 3 |
LEO |
JSLC |
Success |
11 |
LM-2F F11 |
Dec.30, 2002 |
Shenzhou 4 |
LEO |
JSLC |
Success |
12 |
LM-2F F12 |
Oct.15, 2003 |
Shenzhou 5 |
LEO |
JSLC |
Success |
Note:
* Piggybacked with Pakistan
science & experimental satellite
** Xichang Satellite
Launch Center
*** Jiuquan Satellite
Launch Center
**** LM-2F is a more
liable upgraded version of LM-2E dedicated for launching manned
spacecraft.
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