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LM- 2C/CTS Launch Vehicle

* History

Based on the flight proven technology of LM-1 and LM-2, the development of LM-2C launch vehicle was started in 1970. After its successful test flight in 1975, LM-2 was renamed to LM-2C. Later it became the main force to launch China's recoverable satellites. With 14 successes out of 14 launches for LEO missions, this launch vehicle was selected by Motorola, Inc in April of 1993 to provide multiple launches for the Iridium communications satellites. According to the Iridium launch mission requirement, some necessary modifications were made. It included two upgraded stages based on LM-2C and a smart dispenser (SD) developed with flight proven technology and hardware. The renamed launch vehicle --- LM-2C/SD, as of December 31,1999, has achieved six successful launch missions for Motorola, sending 12 Iridium communications satellites into pre-defined orbit. As of April 30, 2005, the LM-2C has conducted 26 launches with 100% successful rate. After some improvements, the LM-2C/SD was renamed LM-2C/CTS.

* Technical Data

LM-2C/CTS is a launch vehicle with two liquid propellant stages plus a smart dispenser as its third stage developed on the basis of LM-2 and LM-2C. It is specially dedicated for launching different spacecraft for LEO missions.

LM-2C's launch capability for LEO mission is 3366 kg. LM-2C/CTS's capability for Iridium mission is 1456 kg. The fairing static envelope is 3 meters. To accommodate mobile communications satellite market, the LM-2C/CTS, with the successful Iridium program experiences, is capable of launching multiple satellites into different LEO.

 

1stStage

2ndStage

CTS*

Stage Diameter (m)

3.35

3.35

2.7

Stage Length (m)

25.720

7.757

1.5

Mass of propellant (kg)

162706

54667

125/50

Propellant

UDMH /N2O4

HTPB/Hydrazine

Engine

 

DaYF6-2

DaYF20-1(Main)
YF21-1 (Vernier)

Solid Motor / RCS (Reaction Control System)

Thrust (KN)

2961.6

741.4 (Main)
11.8x4 (Vernier)

10.78(solid motor)

Engine Specific Impulse
(NĄ¤Sec / kg)

2556.5

(on ground)

2922.37 (Main)
2834.11 (Vernier)

(in vacuum)

2804

(solid motor)

Lift-off Mass (t)

233

Overall Length (m)

42

Fairing Diameter (m)

3.35

LEO or SSO Launch Capability (kg)

(h=900km, SSO)

1456

*CTS is a three-axis stabilized upper stage compatible with two-stage LM-2C. CTS consists of spacecraft adapter and orbital maneuver system. LM-2C/CTS can deliver the spacecraft into the LEO (h>500km)or SSO.

Launch Record

No.

Launch Vehicle

Launch Date

Payload

Mission

LaunchCenter

Result

01

LM-2C F01

26 Nov. 1975

FHW

LEO

JSLC

Success

02

LM-2C F02

7 Dec. 1976

FHW

LEO

JSLC

Success

03

LM-2C F03

26 Jan. 1978

FHW

LEO

JSLC

Success

04

LM-2C F04

9 Sept. 1982

FHW

LEO

JSLC

Success

05

LM-2C F05

19 Aug. 1983

FHW

LEO

JSLC

Success

06

LM-2C F06

12 Sept. 1984

FHW

LEO

JSLC

Success

07

LM-2C F07

21 Oct. 1985

FHW

LEO

JSLC

Success

08

LM-2C F08

6 Oct.1986

FHW

LE0

JSLC

Success

09

LM-2C F09

5 Aug.1987

FHW/Piggyback

LE0

JSLC

Success

10

LM-2C F10

9 Sept.1987

FHW

LE0

JSLC

Success

11

LM-2C F11

5 Aug.1988

FHW/Piggyback

LE0

JSLC

Success

12

LM-2C F12

5 Oct.1990

FHW

LE0

JSLC

Success

13

LM-2C F13

6 Oct.1992

Freja/FHW-2***

LE0

JSLC

Success

14

LM-2C F14

8 Oct. 1993

FHW

LE0

JSLC

Success

15

LM-2C/SD F15

1 Sept. 1997

Motorola****

LE0

TSLC*****

Success

16

LM-2C/SD F16

8 Dec.1997

Motorola

LE0

JSLC

Success

17

LM-2C/SD F17

26 Mar. 1998

Motorola

LE0

JSLC

Success

18

LM-2C/SD F18

2 May 1998

Motorola

LE0

JSLC

Success

19

LM-2C/SD F19

20 Aug.1998

Motorola

LE0

JSLC

Success

20

LM-2C/SD F20

19 Dec.1998

Motorola

LE0

JSLC

Success

21

LM-2C/SD F21

12 June 1999

Motorola

LE0

JSLC

Success

22

LM-2C/SM F22

30 Dec.2003

TC-1

LEO

XSLC

Success

23

LM-2C/CTS F23

18 April 2004

Experiment Satllite-1/ Nano Satellite-1

SSO

XSLC

Success

24

LM-2C/SM F24

25 July 2004

TC-2

LEO

TSLC

Success

25

LM-2CF25

29 Aug. 2004

FHW

LEO

JSLC

Success

26

LM-2CF26

18Nov. 2004

Experiment Satellite-2

LEO

XSLC

Success

Note:
* China's recoverable satellite
** Jiuquan Satellite Launch Center
*** FHW with a piggybacked Swedish scientific satellite -- Freja
**** Test flight with 2 mockup satellites for Iridium mission
***** Taiyuan Satellite Launch Center

 

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