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LM-2D
Long March 2D Launch Vehicle (LM-2D) is a two-stage liquid propelled launch vehicle. It is mainly used to launch satellites for various purposes to sun-synchronous orbit (SSO) and low-earth orbit (LEO). Development of LM-2D launch vehicle started in February 1990, and the first successful launch took place on August 9, 1992. LM-2D was designed based on the principles of high reliability and cost effective. It supports a variety of launch types including dual launch (with the two satellites in parallel or in tandem configuration), and piggyback launch satisfying different customer’s requirement. Besides, when combined with the YuanZheng-3 (YZ-3) upper stage under development, it will achieve higher payload capability to high orbits and better capability to deploy multiple satellites into different orbits.
Main Characters
|
PLF diameter |
3.35m |
3.8m |
|
|
PLF height |
6.983m |
9.275m |
|
|
Overall length |
41.056m |
43.350m |
|
|
Lift-off mass |
About 250t |
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|
Lift-off thrust |
2961.6kN |
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|
Stage-1 一级 |
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Diameter直径 |
3.35m |
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Propellant |
N2O4/UDMH |
||
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Thrust at sea level |
2961.6kN |
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Ground specific impulse |
2550m/s |
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Stage-2 二级 |
|||
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Diameter |
3.35m |
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Propellant |
N2O4/UDMH |
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|
Engine |
Main engine |
Vernier engine |
|
|
|
YF-22C |
YF-23C |
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Main engine thrust |
742.04kN |
47.1kN |
|
|
Specific impulse in vacuum |
2942m/s |
2834m/s |
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LM-2D Configuration
|
Layout of dedicated launch |
Two Parallel Satellites launch |
Piggyback launch |
|
Two Tandem Satellites Launchx |
Combined with the Upper stage Launch |
|
The injection accuracy ( 3σ) of typical mission is as follows:
- Semi-major axis deviation(△a): ±5km
- Orbit eccentricity deviation(△e): ±0.003
- Inclination deviation(△i): ±0.08°
- Lead time T0 + 15 months
T0 + 6 months for piggyback
|
|
NO. |
Launch Vehicle |
Time |
Satellite |
Orbit |
|---|---|---|---|---|
|
1 |
LM-2D_Y1 |
1992-8-9 |
Returnable Yaogan 2-01 |
LEO |
|
2 |
LM-2D_Y2 |
1994-7-3 |
ReturnableYaogan 2-02 |
LEO |
|
3 |
LM-2D_Y3 |
1996-10-20 |
Returnable Yaogan 2-03 |
LEO |
|
4 |
LM-2D_Y4 |
2003-11-3 |
Returnable Yaogan 3-01 |
LEO |
|
5 |
LM-2D_Y5 |
2004-9-27 |
Returnable Yaogan 3-02 |
LEO |
|
6 |
LM-2D_Y7 |
2005-7-6 |
Shijian-7 |
SSO |
|
7 |
LM-2D_Y6 |
2005-8-29 |
Returnable Yaogan 3-03 |
LEO |
|
8 |
LM-2D_Y8 |
2007-5-25 |
Yaogan-2 |
SSO |
|
9 |
LM-2D_Y12 |
2008-11-5 |
Chuangxin 1-02/Shiyan-3 |
SSO |
|
10 |
LM-2D_Y9 |
2008-12-1 |
Yaogan-4 |
SSO |
|
11 |
LM-2D_Y10 |
2009-12-9 |
Yaogan-7 |
SSO |
|
12 |
LM-2D_Y15 |
2010-6-15 |
Shijian-12 |
SSO |
|
13 |
LM-2D_Y14 |
2010-8-24 |
Tianhui 1-01 |
SSO |
|
14 |
LM-2D_Y11 |
2010-9-22 |
Yaogan-11 |
SSO |
|
15 |
LM-2D_Y19 |
2011-11-20 |
Chuangxin1-03/Shiyan-4 |
SSO |
|
16 |
LM-2D_Y17 |
2012-5-6 |
Tianhui 1-02 |
SSO |
|
17 |
LM-2D_Y16 |
2012-9-29 |
VRSS-1 |
SSO |
|
18 |
LM-2D_Y22 |
2012-12-19 |
GK-2 |
SSO |
|
19 |
LM-2D_Y18 |
2013-4-26 |
Gaofen-1 |
SSO |
|
20 |
LM-2D_Y23 |
2013-11-25 |
Shiyan-5 |
SSO |
|
21 |
LM-2D_Y25 |
2014-9-4 |
Chuangxin 1-04 |
SSO |
|
22 |
LM-2D_Y24 |
2014-11-20 |
Yaogan-24 |
SSO |
|
23 |
LM-2D_Y21 |
2015-9-14 |
Gaofen-9 |
SSO |
|
24 |
LM-2D_Y37 |
2015-10-7 |
Jilin-1 |
SSO |
|
25 |
LM-2D_Y26 |
2015-10-26 |
Tianhui-1 |
SSO |
|
26 |
LM-2D_Y31 |
2015-12-17 |
Dark matter particle explorer satellite |
SSO |
|
27 |
LM-2D_Y36 |
2016-4-6 |
Shijian-10 |
LEO |
|
28 |
LM-2D_Y27 |
2016-5-15 |
Yaogan-30 |
SSO |
|
29 |
LM-2D_Y32 |
2016-8-16 |
Quantum Science Experimental Satellite |
SSO |
|
30 |
LM-2D_Y34 |
2016-11-12 |
Yunhai 1-01 |
SSO |
|
31 |
LM-2D_Y33 |
2016-12-22 |
Carbon dioxide monitoring science satellite |
SSO |
|
32 |
LM-2D_Y39 |
2016-12-28 |
Superview-1 01/02 |
SSO |
|
33 |
LM-2D_Y30 |
2017-10-9 |
VRSS-2 |
SSO |
|
34 |
LM-2D_Y47 |
2017-12-3 |
Land exploration-1 |
SSO |
|
35 |
LM-2D_Y48 |
2017-12-23 |
Land exploration-2 |
SSO |
|
36 |
LM-2D_Y40 |
2018-1-9 |
Superview-1 03\04 |
SSO |
|
37 |
LM-2D_Y49 |
2018-1-13 |
Land exploration satellite No.3 |
SSO |
|
38 |
LM-2D_Y50 |
2018 |
Satellite |
SSO |
|
39 |
LM-2D_51 |
2018 |
Satellite |
SSO |
|
40 |
LM-2D_52 |
2018 |
Satellite |
SSO |