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{{Use British English|date=March 2020}}
{{Use dmy dates|date=March 2020}}
{{Infobox rocket
{{Infobox rocket
|image = Image:CZ-3C.svg
|image = Image:CZ-3C.svg
|caption = Drawing of Long March 3C
|caption = Drawing of Long March 3C
|function = [[Carrier rocket]]
|function = [[Carrier rocket]]
|manufacturer = [[China Academy of Launch Vehicle Technology|CALT]]
|manufacturer = [[China Academy of Launch Vehicle Technology|CALT]]
|country-origin= China
|country-origin = China
|status = Active
|status = Active
|sites = [[Xichang Launch Area 2|LA-2]] & [[Xichang Launch Area 3|LA-3]], [[Xichang Satellite Launch Center|XSLC]]
|sites = [[Xichang Launch Area 2|LA-2]] & [[Xichang Launch Area 3|LA-3]], [[Xichang Satellite Launch Center|XSLC]]
|height = {{convert|54.8|m|ft}}<ref name="EA">{{cite web|url=http://www.astronautix.com/lvs/cz3c.htm|title=CZ-3C|author=Mark Wade|publisher=[[Encyclopedia Astronautica]]|accessdate=2008-04-26|url-status=dead|archiveurl=https://web.archive.org/web/20080601181331/http://www.astronautix.com/lvs/cz3c.htm|archivedate=2008-06-01}}</ref>
|height = {{convert|54.8|m|ft}} <ref name="EA">{{cite web|url=http://www.astronautix.com/lvs/cz3c.htm|title=CZ-3C|author=Mark Wade|publisher=[[Encyclopedia Astronautica]]|accessdate=2008-04-26|url-status=dead|archiveurl=https://web.archive.org/web/20080601181331/http://www.astronautix.com/lvs/cz3c.htm|archivedate=2008-06-01}}</ref>
|diameter = {{convert|3.35|m|ft}}<ref name="EA" />
|diameter = {{convert|3.35|m|ft}} <ref name="EA"/>
|mass = {{convert|345000|kg|lb}}<ref name="EA" />
|mass = {{convert|345000|kg|lb}} <ref name="EA"/>
|stages = 3
|stages = 3
|launches = 17<!-- UPDATE after each launch -->
|launches = 17<!-- UPDATE after each launch -->
|success = 17<!-- UPDATE after each launch -->
|success = 17<!-- UPDATE after each launch -->
|first = 25 April 2008
|first = 25 April 2008
|last = <!-- UPDATE after each launch -->
|last = <!-- UPDATE after each launch -->
|capacities =
|capacities =
{{Infobox Rocket/Payload
{{Infobox Rocket/Payload
|location=[[Geosynchronous transfer orbit|GTO]]
|location=[[Geosynchronous transfer orbit|GTO]]
|kilos = '''3C:''' {{convert|3800|kg|lb}}<ref name="CGWIC_User_Manual">{{cite web|url=http://www.cgwic.com/LaunchServices/Download/manual/LM-3A%20Series%20Launch%20Vehicles%20User's%20Manual%20Issue%202011.pdf|title=LM-3A Series Launch Vehicle User's Manual - Issue 2011|publisher=China Great Wall Industries Corporation|accessdate=2015-08-09}}</ref><ref name="GSP">{{cite web|url=http://space.skyrocket.de/doc_lau_det/cz-3c.htm|title=CZ-3C (Chang Zheng-3C)|author=Gunter Krebs|publisher=Gunter's Space Page|accessdate=2008-04-26}}</ref><br />'''3C/E:''' {{convert|3900|kg|lb}}
|kilos = '''3C:''' {{convert|3800|kg|lb}} <ref name="CGWIC_User_Manual">{{cite web|url=http://www.cgwic.com/LaunchServices/Download/manual/LM-3A%20Series%20Launch%20Vehicles%20User's%20Manual%20Issue%202011.pdf|title=LM-3A Series Launch Vehicle User's Manual - Issue 2011|publisher=China Great Wall Industries Corporation|accessdate=2015-08-09}}</ref><ref name="GSP">{{cite web|url=http://space.skyrocket.de/doc_lau_det/cz-3c.htm|title=CZ-3C (Chang Zheng-3C)|author=Gunter Krebs|publisher=Gunter's Space Page|accessdate=2008-04-26}}</ref><br />'''3C/E:''' {{convert|3900|kg|lb}}
}}
}}
{{Infobox Rocket/Payload
{{Infobox Rocket/Payload
|location=[[Heliocentric orbit|HCO]]
|location = [[Heliocentric orbit|HCO]]
|kilos = {{convert|2400|kg|lb}}<ref name="CGWIC_User_Manual"/><ref name="GSP" />
|kilos = {{convert|2400|kg|lb}} <ref name="CGWIC_User_Manual"/><ref name="GSP"/>
}}
}}
|family = [[Long March rocket|Long March]]
|family = [[Long March rocket|Long March]]
|stagedata = {{Infobox rocket/stage
|stagedata = {{Infobox rocket/stage
|type = booster
|type = booster
|diff = 3C
|diff = 3C
|number = 2
|number = 2
|length = {{convert|15.33|m|abbr=on}}
|length = {{convert|15.33|m|abbr=on}}
|diameter = {{convert|2.25|m|abbr=on}}
|diameter = {{convert|2.25|m|abbr=on}}
|empty = <!--{{convert|3200|kg}}-->
|empty = <!--{{convert|3200|kg}}-->
|gross = <!--{{convert|41000|kg}}-->
|gross = <!--{{convert|41000|kg}}-->
|propmass = {{convert|37700|kg|abbr=on}}
|propmass = {{convert|37700|kg|abbr=on}}
|engines = 1 [[YF-20|YF-25]]
|engines = 1 [[YF-20|YF-25]]
|thrust = {{convert|740.4|kN|abbr=on}}
|thrust = {{convert|740.4|kN|abbr=on}}
|SI = {{convert|2556.2|m/s|isp|abbr=on}}
|SI = {{convert|2556.2|m/s|isp|abbr=on}}
|burntime = 127 s
|burntime = 127 seconds
|fuel = [[N2O4|N<sub>2</sub>O<sub>4</sub>]] / [[UDMH]]
|fuel = [[N2O4|N<sub>2</sub>O<sub>4</sub>]] / [[UDMH]]
}}
}}
{{Infobox rocket/stage
{{Infobox rocket/stage
|type = booster
|type = booster
|diff = 3C/E
|diff = 3C/E
|number = 2
|number = 2
|length = {{convert|16.1|m|abbr=on}}
|length = {{convert|16.1|m|abbr=on}}
|diameter = {{convert|2.25|m|abbr=on}}
|diameter = {{convert|2.25|m|abbr=on}}
|empty =
|empty =
|gross =
|gross =
|propmass = {{convert|41100|kg|abbr=on}}
|propmass = {{convert|41100|kg|abbr=on}}
|engines = 1 [[YF-20|YF-25]]
|engines = 1 [[YF-20|YF-25]]
|thrust = {{convert|740.4|kN|abbr=on}}
|thrust = {{convert|740.4|kN|abbr=on}}
|SI = {{convert|2556.2|m/s|isp|abbr=on}}
|SI = {{convert|2556.2|m/s|isp|abbr=on}}
|burntime = 140 s
|burntime = 140 seconds
|fuel = [[N2O4|N<sub>2</sub>O<sub>4</sub>]] / [[UDMH]]
|fuel = [[N2O4|N<sub>2</sub>O<sub>4</sub>]] / [[UDMH]]
}}
}}
{{Infobox rocket/stage
{{Infobox rocket/stage
|type = stage
|type = stage
|stageno = First
|stageno = First
|diff = 3C
|diff = 3C
|length = {{convert|23.27|m|abbr=on}}
|length = {{convert|23.27|m|abbr=on}}
|diameter = {{convert|3.35|m|abbr=on}}
|diameter = {{convert|3.35|m|abbr=on}}
|empty = <!--{{convert|9000|kg}}-->
|empty = <!--{{convert|9000|kg}}-->
|gross = <!--{{convert|179000|kg}}-->
|gross = <!--{{convert|179000|kg}}-->
|propmass = {{convert|171800|kg|abbr=on}}
|propmass = {{convert|171800|kg|abbr=on}}
|engines = 4 [[YF-20|YF-21C]]
|engines = 4 [[YF-20|YF-21C]]
|thrust = {{convert|2961.6|kN|abbr=on}}
|thrust = {{convert|2961.6|kN|abbr=on}}
|SI = {{convert|2556.5|m/s|isp|abbr=on}}
|SI = {{convert|2556.5|m/s|isp|abbr=on}}
|burntime = 145 s
|burntime = 145 seconds
|fuel = [[N2O4|N<sub>2</sub>O<sub>4</sub>]] / [[UDMH]]
|fuel = [[N2O4|N<sub>2</sub>O<sub>4</sub>]] / [[UDMH]]
}}
}}
{{Infobox rocket/stage
{{Infobox rocket/stage
|type = stage
|type = stage
|stageno = First
|stageno = First
|diff = 3C/E
|diff = 3C/E
|length = {{convert|24.76|m|abbr=on}}
|length = {{convert|24.76|m|abbr=on}}
|diameter = {{convert|3.35|m|abbr=on}}
|diameter = {{convert|3.35|m|abbr=on}}
|empty = <!--{{convert|9000|kg}}-->
|empty = <!--{{convert|9000|kg}}-->
|gross = <!--{{convert|179000|kg}}-->
|gross = <!--{{convert|179000|kg}}-->
|propmass = {{convert|186200|kg|abbr=on}}
|propmass = {{convert|186200|kg|abbr=on}}
|engines = 4 [[YF-20|YF-21C]]
|engines = 4 [[YF-20|YF-21C]]
|thrust = {{convert|2961.6|kN|abbr=on}}
|thrust = {{convert|2961.6|kN|abbr=on}}
|SI = {{convert|2556.5|m/s|isp|abbr=on}}
|SI = {{convert|2556.5|m/s|isp|abbr=on}}
|burntime = 158 s
|burntime = 158 seconds
|fuel = [[N2O4|N<sub>2</sub>O<sub>4</sub>]] / [[UDMH]]
|fuel = [[N2O4|N<sub>2</sub>O<sub>4</sub>]] / [[UDMH]]
}}
}}
{{Infobox rocket/stage
{{Infobox rocket/stage
|type = stage
|type = stage
|stageno = Second
|stageno = Second
|length = {{convert|12.92|m|abbr=on}}
|length = {{convert|12.92|m|abbr=on}}
|diameter = {{convert|3.35|m|abbr=on}}
|diameter = {{convert|3.35|m|abbr=on}}
|empty = <!--{{convert|5000|kg}}-->
|empty = <!--{{convert|5000|kg}}-->
|gross = <!--{{convert|55000|kg}}-->
|gross = <!--{{convert|55000|kg}}-->
|propmass = {{convert|49400|kg|abbr=on}}
|propmass = {{convert|49400|kg|abbr=on}}
|engines = 1 [[YF-20|YF-24E]] (YF-22E (Main) <br/>4 x YF-23C (Vernier))
|engines = 1 [[YF-20|YF-24E]] (YF-22E (Main)<br/>4 x YF-23C (Vernier))
|thrust = {{convert|742|kN|abbr=on}} (Main)<br/>{{convert|47.1|kN|abbr=on}} (Vernier)
|thrust = {{convert|742|kN|abbr=on}} (Main)<br/>{{convert|47.1|kN|abbr=on}} (Vernier)
|SI = {{convert|2922.57|m/s|isp|abbr=on}} (Main)<br/>{{convert|2910.5|m/s|isp|abbr=on}} (Vernier)
|SI = {{convert|2922.57|m/s|isp|abbr=on}} (Main)<br/>{{convert|2910.5|m/s|isp|abbr=on}} (Vernier)
|burntime = 185 s
|burntime = 185 seconds
|fuel = [[N2O4|N<sub>2</sub>O<sub>4</sub>]] / [[UDMH]]
|fuel = [[N2O4|N<sub>2</sub>O<sub>4</sub>]] / [[UDMH]]
}}
}}
{{Infobox rocket/stage
{{Infobox rocket/stage
|type = stage
|type = stage
|stageno = Third
|stageno = Third
|length = {{convert|12.38|m|abbr=on}}
|length = {{convert|12.38|m|abbr=on}}
|diameter = {{convert|3.0|m|abbr=on}}
|diameter = {{convert|3.0|m|abbr=on}}
|empty = <!--{{convert|2800|kg}}-->
|empty = <!--{{convert|2800|kg}}-->
|gross = <!--{{convert|21000|kg}}-->
|gross = <!--{{convert|21000|kg}}-->
|propmass = {{convert|18200|kg|abbr=on}}
|propmass = {{convert|18200|kg|abbr=on}}
|engines = 1 [[YF-75]]
|engines = 1 [[YF-75]]
|thrust = {{convert|167.17|kN|abbr=on}}
|thrust = {{convert|167.17|kN|abbr=on}}
|SI = {{convert|4295|m/s|isp|abbr=on}}
|SI = {{convert|4295|m/s|isp|abbr=on}}
|burntime = 478 s
|burntime = 478 seconds
|fuel = [[LH2|LH<sub>2</sub>]] / [[LOX]]
|fuel = [[LH2|LH<sub>2</sub>]] / [[LOX]]
}}
}}
}}
}}
Line 118: Line 120:


==Launches==
==Launches==
It made its maiden flight on 25 April 2008, at 15:35 GMT. The payload for the first launch was the [[Tianlian-1]] data relay [[communications satellite]]. The second carried the [[BeiDou Navigation Satellite System|Compass-G2]] navigation satellite, and was conducted on 14 April 2009. The third launch was made on 16 January 2010, with the [[BeiDou Navigation Satellite System|Compass-G1]] satellite. The fourth carrying the [[BeiDou Navigation Satellite System|Compass-G3]] navigation satellite was launched on 2 June 2010. On 1 October 2010, it successfully launched China's second lunar probe, [[Chang'e 2]].
It made its maiden flight on 25 April 2008, at 15:35 UTC. The payload for the first launch was the [[Tianlian-1]] data relay [[communications satellite]]. The second carried the [[BeiDou Navigation Satellite System|Compass-G2]] navigation satellite and was conducted on 14 April 2009. The third launch was made on 16 January 2010, with the [[BeiDou Navigation Satellite System|Compass-G1]] satellite. The fourth carrying the [[BeiDou Navigation Satellite System|Compass-G3]] navigation satellite was launched on 2 June 2010. On 1 October 2010, it successfully launched China's second lunar probe, [[Chang'e 2]].


An enhanced version of the Long March 3C rocket debuted during the launch of [[Chang'e 5-T1]] on 23 October 2014.<ref>{{cite web|last1=Barbosa|first1=Rui C.|title=China launches lunar sample return test mission|url=http://www.nasaspaceflight.com/2014/10/china-lunar-sample-return-test-mission/|publisher=[[NASASpaceflight.com]]|date=23 October 2014|accessdate=10 August 2015}}</ref> On 30 March 2015 the [[Yuanzheng-1]] upper stage was used on top of a Long March 3C rocket for the first time.<ref>{{cite web|last1=Barbosa|first1=Rui C.|title=Long March 3C in secretive launch with new Upper Stage|url=http://www.nasaspaceflight.com/2015/03/long-march-3c-launch-new-upper-stage/|publisher=NASASpaceflight.com|date=30 March 2015|accessdate=10 August 2015}}</ref>
An enhanced version of the Long March 3C rocket debuted during the launch of [[Chang'e 5-T1]] on 23 October 2014.<ref>{{cite web|last1=Barbosa|first1=Rui C.|title=China launches lunar sample return test mission|url=http://www.nasaspaceflight.com/2014/10/china-lunar-sample-return-test-mission/|publisher=[[NASASpaceflight.com]]|date=23 October 2014|accessdate=10 August 2015}}</ref> On 30 March 2015, the [[Yuanzheng-1]] upper stage was used on top of a Long March 3C rocket for the first time.<ref>{{cite web|last1=Barbosa|first1=Rui C.|title=Long March 3C in secretive launch with new Upper Stage |url=http://www.nasaspaceflight.com/2015/03/long-march-3c-launch-new-upper-stage/|publisher=NASASpaceflight.com|date=30 March 2015|accessdate=10 August 2015}}</ref>


==List of launches==
==List of launches==

Revision as of 22:29, 9 April 2020

Drawing of Long March 3C
FunctionCarrier rocket
ManufacturerCALT
Country of originChina
Size
Height54.8 metres (180 ft) [1]
Diameter3.35 metres (11.0 ft) [1]
Mass345,000 kilograms (761,000 lb) [1]
Stages3
Capacity
Payload to GTO
Mass3C: 3,800 kilograms (8,400 lb) [2][3]
3C/E: 3,900 kilograms (8,600 lb)
Payload to HCO
Mass2,400 kilograms (5,300 lb) [2][3]
Associated rockets
FamilyLong March
Launch history
StatusActive
Launch sitesLA-2 & LA-3, XSLC
Total launches17
Success(es)17
First flight25 April 2008
Boosters (3C)
No. boosters2
Height15.33 m (50.3 ft)
Diameter2.25 m (7 ft 5 in)
Propellant mass37,700 kg (83,100 lb)
Powered by1 YF-25
Maximum thrust740.4 kN (166,400 lbf)
Specific impulse2,556.2 m/s (260.66 s)
Burn time127 seconds
PropellantN2O4 / UDMH
Boosters (3C/E)
No. boosters2
Height16.1 m (53 ft)
Diameter2.25 m (7 ft 5 in)
Propellant mass41,100 kg (90,600 lb)
Powered by1 YF-25
Maximum thrust740.4 kN (166,400 lbf)
Specific impulse2,556.2 m/s (260.66 s)
Burn time140 seconds
PropellantN2O4 / UDMH
First stage (3C)
Height23.27 m (76.3 ft)
Diameter3.35 m (11.0 ft)
Propellant mass171,800 kg (378,800 lb)
Powered by4 YF-21C
Maximum thrust2,961.6 kN (665,800 lbf)
Specific impulse2,556.5 m/s (260.69 s)
Burn time145 seconds
PropellantN2O4 / UDMH
First stage (3C/E)
Height24.76 m (81.2 ft)
Diameter3.35 m (11.0 ft)
Propellant mass186,200 kg (410,500 lb)
Powered by4 YF-21C
Maximum thrust2,961.6 kN (665,800 lbf)
Specific impulse2,556.5 m/s (260.69 s)
Burn time158 seconds
PropellantN2O4 / UDMH
Second stage
Height12.92 m (42.4 ft)
Diameter3.35 m (11.0 ft)
Propellant mass49,400 kg (108,900 lb)
Powered by1 YF-24E (YF-22E (Main)
4 x YF-23C (Vernier))
Maximum thrust742 kN (167,000 lbf) (Main)
47.1 kN (10,600 lbf) (Vernier)
Specific impulse2,922.57 m/s (298.019 s) (Main)
2,910.5 m/s (296.79 s) (Vernier)
Burn time185 seconds
PropellantN2O4 / UDMH
Third stage
Height12.38 m (40.6 ft)
Diameter3.0 m (9.8 ft)
Propellant mass18,200 kg (40,100 lb)
Powered by1 YF-75
Maximum thrust167.17 kN (37,580 lbf)
Specific impulse4,295 m/s (438.0 s)
Burn time478 seconds
PropellantLH2 / LOX
[edit on Wikidata]

The Long March 3C (simplified Chinese: 长征三号丙火箭; traditional Chinese: 長征三號丙火箭; pinyin: Chángzhēng Sānhào Bǐng Huǒjiàn), also known as the Changzheng 3C, CZ-3C and LM-3C, is a Chinese orbital carrier rocket. It is launched from Launch Complex 2 at the Xichang Satellite Launch Centre. A 3-stage rocket with two strapon liquid rocket boosters, it is a member of the Long March 3 rocket family, and was derived from the Long March 3B. It was designed to fill a gap in payload capacities between the Long March 3A and 3B.

Launches

It made its maiden flight on 25 April 2008, at 15:35 UTC. The payload for the first launch was the Tianlian-1 data relay communications satellite. The second carried the Compass-G2 navigation satellite and was conducted on 14 April 2009. The third launch was made on 16 January 2010, with the Compass-G1 satellite. The fourth carrying the Compass-G3 navigation satellite was launched on 2 June 2010. On 1 October 2010, it successfully launched China's second lunar probe, Chang'e 2.

An enhanced version of the Long March 3C rocket debuted during the launch of Chang'e 5-T1 on 23 October 2014.[4] On 30 March 2015, the Yuanzheng-1 upper stage was used on top of a Long March 3C rocket for the first time.[5]

List of launches

Main article: List of Long March launches
Flight number Date (UTC) Launch site Version Payload Orbit Result
1 April 25, 2008
15:35 		LA-2, XSLC 3C Tianlian I-01 GTO Success
2 April 14, 2009
16:16 		LA-2, XSLC 3C Compass-G2 GTO Success
3 January 16, 2010
16:12 		LA-2, XSLC 3C Compass-G1 GTO Success
4 June 2, 2010
15:53 		LA-2, XSLC 3C Compass-G3 GTO Success
5 October 1, 2010
10:59 		LA-2, XSLC 3C Chang'e 2 LTO Success
6 October 31, 2010
16:26 		LA-2, XSLC 3C Compass-G4 GTO Success
7 July 11, 2011
15:41 		LA-2, XSLC 3C Tianlian I-02 GTO Success
8 February 24, 2012
16:12 		LA-2, XSLC 3C Compass-G5 GTO Success
9 July 25, 2012
15:43 		LA-2, XSLC 3C Tianlian I-03 GTO Success
10 October 25, 2012
15:33 		LA-2, XSLC 3C Compass-G6 GTO Success
11 October 23, 2014
18:00 		LA-2, XSLC 3C/E Chang'e 5-T1 LTO Success
12 March 30, 2015
13:52 		LA-2, XSLC 3C/YZ-1 BDS I1-S GSO Success
13 February 1, 2016
07:29 		LA-2, XSLC 3C/YZ-1 BDS M3-S MEO Success
14 June 12, 2016
15:30 		LA-3, XSLC 3C/E Compass-G7 GTO Success
15 November 22, 2016
15:24 		LA-2, XSLC 3C/E Tianlian I-04 GTO Success
16 December 24, 2018
16:53 		LA-3, XSLC 3C/E TJSW-3 GTO Success
17 May 17, 2019
15:48 		LA-2, XSLC 3C/E Compass-G8 GTO Success

References

  1. ^ a b c Mark Wade. "CZ-3C". Encyclopedia Astronautica. Archived from the original on 1 June 2008. Retrieved 26 April 2008.
  2. ^ a b "LM-3A Series Launch Vehicle User's Manual - Issue 2011" (PDF). China Great Wall Industries Corporation. Retrieved 9 August 2015.
  3. ^ a b Gunter Krebs. "CZ-3C (Chang Zheng-3C)". Gunter's Space Page. Retrieved 26 April 2008.
  4. ^ Barbosa, Rui C. (23 October 2014). "China launches lunar sample return test mission". NASASpaceflight.com. Retrieved 10 August 2015.
  5. ^ Barbosa, Rui C. (30 March 2015). "Long March 3C in secretive launch with new Upper Stage". NASASpaceflight.com. Retrieved 10 August 2015.


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