Long March (Chang Zheng)

by Jean-Jacques Serra
listing by Gunter Krebs
After the rupture between China and USSR in June 1959 the Chinese started to develop a series a ballistic missiles powered with stockable propellant. The first of these was the CSS-1: a single stage rocket very close to the Soviet SS-3 which was 22 m in length and 1.65 m in diameter that could cover 1100 km. It was tested in the sixties and entered service in 1970. The first Chinese IRBM, the CSS-2 was also single staged. It was 23 m long, 2.23 m diameter and ranged 2500 km. The first in-flight tests were carried out on 1969 and was deployed in 1972. The CSS-3 version with 6500 km range was made by adding a second stage to the CSS-2 (with same diameter). It never entered operational service was was used as the basis of the first Chinese launcher: CZ-1.

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CZ-1 launchers

The CZ-1 rocket (Chang Zheng = Long March) was derived from the CSS-3 (also called DF-4 by the Chinese, Dong Feng = East Wind) which was added a solid fuel third stage. The first stage was 17.8 m long and weighed 64.1 tons including 60 tons of propellant (Nitric Acid and UDMH). It was powered by a YF-2A motor featuring 4 chambers of 1100 kN at ground level, burning during 130 seconds (ISp = 241 s). The 5.4 m second stage weighed 15.9 tons including 13.2 tons of ergols (NTO and UDMH). It used a YF-3 motor providing 294 kN thrust in vacuum during 126 seconds (ISp = 287 s). The spin-stabilized third stage required a GF=02 powder bloc weighing 1.8 tons which provides 29 kN thrust.

The full CZ-1 launcher was 29.45 m high for 81.6 tons at takeoff and could orbit a 300 kg payload at 440 km with 70° inclination. It launched the 2 first Chinese satellites from Juiquan in April 1970 and March 1971 after a failure in November 1969.

Enhanced version of this launcher: CZ-1C and CZ-1D completly Chinese and CZ-1M featuring an Italian 3rd stage (IRIS) were announced...

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Second generation launchers: FB-1 and CZ-2A/D

The first Chinese ICBM CSS-3 (or DF-5 in the Chinese jargon) was over 30 m high for 3.35 m diameter. It featured two liquid fuel stages (NTO and UDMH) and ranged 11000 km. In-flight tests were carried out in 1979 and only few exemplars (8 to 12 ?) were deployed after 1980.

Its development was carried out in the same time as two space launcher programs: FB-1 (Feng Bao = storm) and CZ-2. Very little is known on the FB-1 but it is probably similar to CZ-2 with lower performances (1.2 tons is LEO against 1.7 tons). Some sources believe the two launchers were developped by two different agencies (SBA (Shanghai Bureau of Astronautics) et la BWYIC (Beijing Wan Yuan Industry Corporation)) from the same specifications. It was launched successfully 4 times from Jiuquan between July 1975 and September 1981; 4 failures and 3 suborbital flights were also reported.

The most important launcher of the other series is the CZ-2C. The CZ-2A was indeed only fired once in November 1974 and the B designation used for the FB-1. The CZ-2C featured a L-140 first stage of 20.5 m long which weighed 151 tons including 142 tons of propellant. It was powered by 4 YF-20 motors of 696 kN thrust at ground level (ISp = 260 s) which burned during 132 seconds. The second stage (L-35) was 7.5 m long and 39 tons (35 tons for propellant). It was equipped with an YF-22 motor providing 762 kN in vacuum (ISp = 290 s) associated with 4 deployable YF-23 verniers providing a total of 44 kN. The main engine burned 110 seconds while the verniers 300 seconds.

The CZ-2C launcher is 32.6 to 35.1 m high (depending on the cap) and weighed about 191 tons. It can deliver 2 to 2.5 tons in LEO. From Juiquan it orbited 9 retrievable FSW-0 (Fanhui Shi Weixing) satellites between November 1975 and August 1987 and 5 FSW-1 since September 1987. An enhanced version named CZ-2D launched two FSW-2 satellites in August 1992 and July 1994.

Three-stage versions of the CZ-2C were announced . Only the CZ-2C/SD should be used for Iridium.

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CZ-3 launchers

The CZ-3 rocket is a 3-stage launcher which makes use of modified versions of the 2 first stages of CZ-2C (same performances) and adds a cryogenic third stage. This H-8 cryogenic stage is 7.5 m long for 2.25 m diameter. It weighs 10.5 tons including 8.5 tons of propellant (LH2 and LOX). it is equipped with a 4-chamber YF-73 motor providing 44 kN thurst in vacuum (ISp = 420 s). The reignitable motor is used for two burns during 500 and 300 seconds.

This launcher is 43.2 to 43.8 m high and weighs 202 tons. It can orbit 1.4 tons in GTO. It was used from Xichang from January 1984 on to launch Chinese telecommunication satellites of foreign spacecrafts. It should still be used even after the introduction of enhanced versions designated CZ-3A and CZ-3B.

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Third generation launchers: CZ-4, CZ-2E and CZ-3A/B

A new Chinese generation was introduced in the late eighties based on a streched L-180 first stage equipped with more powerful motors.

The first launcher to use those new elements was CZ-4 specialy designed for sunsynchronous orbits. The first stage is thus an L-180 with 24.7 m long carrying 138 tons propellant powered during 156 seconds by 4 YF-20 motors which unitary thrust was boosted to 735 kN. The second stage is an modified L-35 with 10.4 m long. Its main engine is a YF-25 of 766 kN assisted by 4 YF-23 verniers. The third stage (L-14) specific to the CZ-4 is 6.2 m long for 2.9 m diameter. It is equipped with a pair of YF-40 engines which burn NTO and UDMH. Their total thrust is 98 kN during 321 seconds (ISp = 303 s). This CZ-4 reaches 42 m high and 250 tons. It can deliver a 1.5 ton payload on sun-synchronous orbit at 900 km. It was used to launch 2 meteorological FY satellites from Taiyuan in Sep 1988 and Sep 1990. The CZ-4C is similar to CZ-4B, with the restart capability added.

The second launcher to use the L-180 and the enhanced motors is the CZ-2E devoted to heavy GEO payloads. The first stage is an L-180 with 23.7 m long (187 tons propellant) propulsed during 159 seconds by 4 YF-20 motors of 735 kN. It is assisted during 126 seconds by 4 LB-40 boosters of 15.6 m long and 2.25 m diameter (38 tons of propellant each) equipped with the same YF-20 engines. The second stage is an L-90 of 15.5 m long (86 tons ergols) with a YF-25 main engine of 831 kN. It is surrounded by 4 YF-23 verniers. The main engine burns during 300 seconds while the version 413 seconds.

The CZ-2E is 49.7 to 51.2 m high. It weighs 460 tons at takeoff. Its capacity reaches 8.8 tons in LEO but it is only used for geostationary satellites with a solid perigee stage. The first version with the American Thiokol Star-63F could place 3.14 tons in GTO. With the EPKM of the Chinese HCMC (Hexi Chemical & Manufacturing Corp) company used for the first time in Nov 1995 the performance reaches 3.46 tons. After a trial launch in July 1990 the CZ-2E was used to launch several telecommunications satellites from Xichang...

The third launcher based on the L-180 was the CZ-3A also devoted to heavy payloads aimed at GEO. The first stage is a 23 m long L-180 (170 tons of propellant) powered by four 735 kN YF-20 motors. The second stage is a L-35 of 11.5 m long (29.6 tons ergol) with an YF-25 main engine of 766 kN which burns during 110 seconds assited by 4 YF-23 verniers. The new H-18 cryogenic third stage is 8.8 m long and 3.0 m diameter (17.6 tons propellant). It features 2 YF-75 engines providing a total thrust of 157 kN (ISp = 425 s) during 470 seconds in 2 burns.

The CZ-3A has a total of 52.3 m high and 240 tons at takeoff. It can orbit 2.3 tons in GTO. After a trial launch in Feb 1994 to launched a 3rd generation telecommunication DFH satellite in Nov 1994.

The CZ-3B used the CZ-3A with 4 liquid boosters inherited from the CZ-2E. It then weighs 403 tons at takeoff and its capacity reaches 4.85 tons in GTO. It first launch failed in Feb 1996.

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CZ-1 launches

#	Launch id	Payload	Launch date	Type	Status/Comment (orbit in perigee x apogee x inc. x period)
1, CZ-1	n/a	R&D suborbital	10 Jan 1970
2, CZ-1	70034	DFH 01	24 Apr 1970
3, CZ-1	71018	DFH 02	3 Mar 1971

Notes: All launches from Juiquan.

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CZ-2, 3 & 4 launches

#	Launch id	Payload	Launch date	Site	Type	Status/Comment (orbit in perigee x apogee x inc. x period)
1, CZ-2	n/a	FSW 0	05 Nov 1974	Ji	A?	Failure: 1st stage control system failure
2, CZ-2	75111	FSW 0-1	26 Nov 1975	Ji	C
3, CZ-2	76116	FSW 0-2	07 Dec 1976	Ji	C
4, CZ-2	78011	FSW 0-3	26 Jan 1978	Ji	C
5, CZ-2	82090	FSW 0-4	09 Sep 1982	Ji	C
6, CZ-2	83086	FSW 0-5	19 Aug 1983	Ji	C
7, CZ-3	84008	STTW-T1	29 Jan 1984	Xi		Partial failure: 3rd stage failed to ignite
8, CZ-3	84035	STTW-T2	08 Apr 1984	Xi
9, CZ-2	84098	FSW 0-6	12 Sep 1984	Ji	C
10, CZ-2	85096	FSW 0-7	21 Oct 1985	Ji	C
11, CZ-3	86010	STTW 1	01 Feb 1986	Xi
12, CZ-2	86076	FSW 0-8	06 Oct 1986	Ji	C
13, CZ-2	87067	FSW 0-9	05 Aug 1987	Ji	C
14, CZ-2	87075	FSW 1-1	09 Sep 1987	Ji	C
15, CZ-3	88014	STTW 2	07 Mar 1988	Xi
16, CZ-2	88067	FSW 1-2	05 Aug 1988	Ji	C
17, CZ-4	88080	FY 1-1	06 Sep 1988	Ty
18, CZ-3	88111	STTW 3	22 Dec 1988	Xi
19, CZ-3	90011	STTW 4	04 Feb 1990	Xi
20, CZ-3	90030	Asiasat 1	07 Apr 1990	Xi
21, CZ-2	90059	Badr A	16 Jul 1990	Xi	E (PKM)	Failed to place the Optus model in GTO
22, CZ-4	90081	A: FY 1-2 B: DFH 31 C: DFH 32	03 Sep 1990	Ty
23, CZ-2	90089	FSW 1-3	05 Oct 1990	Ji	C
24, CZ-3	91088	STTW 5	28 Dec 1991	Xi		Partial failure: 3rd stage failed to ignite
25, CZ-2	92051	FSW 2-1	09 Aug 1992	Ji	D
26, CZ-2	92054	Optus B1	13 Aug 1992	Xi	E (Star-63F)
27, CZ-2	92064	A: Freja B: FSW 1-4	06 Oct 1992	Ji	C
28, CZ-2	92090	Optus B2	21 Dec 1992	Xi	E (Star-63F)	Partial failure: payload fairing collapsed
29, CZ-2	93063	FSW 1-5	08 Oct 1993	Ji	C
30, CZ-3	94010	A: SJ 4 B: DFH 3-0	08 Feb 1994	Xi	A
31, CZ-2	94037	FSW 2-2	3 Jul 1994	Ji	D
32, CZ-3	94043	Apstar 1	21 Jul 1994	Xi
33, CZ-2	94055	Optus B3	27 Aug 1994	Xi	E (Star-63F)
34, CZ-3	94080	DFH 3-1	29 Nov 1994	Xi	A
35, CZ-2	n/a	Apstar 2	25 Jan 1995	Xi	E (Star-63F)	Failure: vehicle destroyed due to wind shear
36, CZ-2	95064	Asiasat 2	28 Nov 1995	Xi	E (STPM-17)
37, CZ-2	95073	Echostar 1	28 Dec 1995	Xi	E (?)
38, CZ-3	n/a	Intelsat 708	14 Feb 1996	Xi	B	Failure: attitude control lost within seconds, due to an electrical failure
39, CZ-3	96039	Apstar 1A	03 Jul 1996	Xi		225 x 42184 km x 26.9°
40, CZ-3	96048	DFH 42	18 Aug 1996 at 10:27 UT	Xi		Partial failure: 3rd stage shutdown 48s early
41, CZ-2	96059	FSW 2-3	20 Oct 1996	Ji	D
42, CZ-3	97021	DFH 44	11 May 1997 at 16:17 UT	Xi	A
43, CZ-3	97029	DFH 45	10 Jun 1997 at 12:01 UT	Xi		206 x 35987 km x 28.4°
44, CZ-3	97042	Mabuhay 1	19 Aug 1997 at 17:30 UT	Xi	B	170 x 44499 km x 24.6°
45, CZ-2	97048	2 Iridium MFS (Mass Frequency Simulators) 650 kg each	1 Sep 1997 at 14:00 UT	Ty	C	First flight from Taiyan with Smart Dispenser upper stage
46, CZ-3	97062	Apstar 2R	16 Oct 1997 at 17:13 UT	Xi	B	201 x 47922 km x 24.4°
47, CZ-2	97077	A: Iridium 42 B: Iridium 44	8 Dec 1997 at 07:16 UT	Ty	C-3/SD	SD = Smart Dispenser
48, CZ-2	98018	A: Iridium 51 B: Iridium 61	25 Mar 1998 at 17:01 UT	Ty	C-3/SD
49, CZ-2	98026	A: Iridium 69 B: Iridium 71	2 May 1998	Ty	C-3/SD
50, CZ-3	98034	Chinastar 1	30 May 1998	Xi	B
51, CZ-3	98044	Sinosat 1	18 Jul 1998 at 09:20 UT	Xi	B
52, CZ-2	98048	A: Iridium 78 B: Iridium 76	19 Aug 1998 at 23:01 UT	Ty	C-3/SD
53, CZ-2	98074	A: Iridium 88 B: Iridium 89	19 Dec 1998 at 11:30 UT	Ty	C-3/SD
54, CZ-4	99025	A: FY 1C B: DFH 48	10 May 1999 at 01:33 UT	Ty	4B
55, CZ-2	99032	A: Iridium 14A B: Iridium 21A	11 Jun 1999 at 17:15 UT	Ty	C/SD
56, CZ-4	99057	A: CBERS 1 B: SACI 1	14 Oct 1999 at 03:15 UT	Ty	4B
57, CZ-2	99061	Shenzhou 1	19 Nov 1999 at 22:43 UT	Ji	2F
58, CZ-3	00003	DFH 48	25 Jan 2000 at 16:45 UT	Xi	A
59, CZ-3	00032	DFH 49	25 Jun 2000 at 11:50 UT	Xi
60, CZ-4	00050	DFH 50	1 Sep 2000 at 03:25 UT	Ty	4B
61, CZ-3	00069	DFH 51	30 Oct 2000 at 16:02 UT	Xi	3A
62, CZ-3	00082	DFH 52	21 Dec 2000 at 16:20 UT	Xi	3A
63, CZ-2	00101	Shenzhou 2	9 Jan 2001 at 17:00 UT	Ji	2F	First mission completed in winter, with temperature -13°C
64, CZ-2	02014	Shenzhou 3	25 Mar 2002 at 14:00 UT	Ji	2F	197 x 326 km x 42.4°
65, CZ-4	02024	A: DFH 53 B: DFH 54	15 May 2002 at 01:50 UT	Ty	4B
66, CZ-4	02049	DFH 55	27 Oct 2002 at 03:17 UT	Ty	4B
67, CZ-2	02061	Shenzhou 4	29 Dec 2002 at 16:40 UT	Ji	2F
68, CZ-3	03021	DFH 56	24 May 2003 at 16:34 UT	Xi	3A
69, CZ-2	03045	Shenzhou 5	15 Oct 2003 at 01:00 UT	Ji	2F	First manned mission for China
70, CZ-4	03049	A: CBERS 2 B: Chuangxin 1	21 Oct 2003 at 03:16 UT	Ty	4B
71, CZ-2	03051	DFH 57	03 Nov 2003 at 07:20 UT	Ji	2D
72, CZ-3	03052	DFH 58	14 Nov 2003 at 16:01 UT	Xi	3A	212 x 41981 km
73, CZ-2	03061	Tan Ce 1	29 Dec 2003 at 19:06 UT	Xi	2C/SM	550 x 66000 km x 28.5° Had an SM upper stage derived from the smart dispenser used for Iridium. First 2C launch from Xichang.
74, CZ-2	04012	A: Tansuo 1 B: Nazing 1	18 Apr 2004 at 15:59 UT	Xi	2C	Polar orbit
75, CZ-2	04029	Tan Ce 2	25 Jul 2004 at 07:05 UT	Xi	2C/SM	666 x 38566 km x 90.1°
76, CZ-2	04033	DFH 59	29 Aug 2004 at 07:50 UT	Ji	2C
77, CZ-4	04035	A: DFH 60 B: DFH 61	8 Sep 2004 at 23:14 UT	Ty	4B
78, CZ-2	04039	DFH 62	27 Sep 2004	Ji	2D
79, CZ-3	04042	DFH 63	19 Oct 2004 at 01:20 UT	Xi	3A
80, CZ-4	04044	DFH 64	6 Nov 2004 at 03:10 UT	Ty	4B
81, CZ-3	05012	Apstar 6	12 Apr 2005 at 12:00 UT	Xi	3B	209 x 49991 km x 26°
82, CZ-2	05024	DFH 65	5 Jul 2005 at 22:40 UT	Ji	2D	547 x 570 km x 97.6° First sun-synchronous launch from Jiuquan
83, CZ-2	05027	DFH 66	2 Aug 2005 at 07:30 UT	Ji	2C
84, CZ-2	05033	DFH 67	29 Aug 2005	Ji	2D
85, CZ-2	05040	Shenzhou 6	12 Oct 2005 at 01:00 UT	Ji	2F	Second manned mission 198 x 344 km x 42.4°
86, CZ-4	06015	A: Yaogan 1 B: picosat	26 Apr 2006 at 22:48 UT	Ty	4B	a 1kg object was also launched with, microelectronics experiment
87, CZ-2	06035	DFH 68	9 Sep 2006 at 07:00 UT	Ji	2C
88, CZ-3	06038	DFH 69	12 Sep 2006 at 16:02 UT	Xi	3A
89, CZ-4	06046	A: DFH 70 B: DFH 71	23 Oct 2006 at 23:43 UT	Ty	4B
90, CZ-3	06048	Sinosat 2	28 Oct 2006 at 16:20 UT	Xi	3C
91, CZ-3	06053	DFH 72	08 Dec 2006 at 00:53 UT	Xi	3A
92, CZ-3	07003	DFH 73	03 Feb 2007 at 16:28 UT	Xi	3A
93, CZ-2	07010	DFH 74	11 Apr 2007 at 03:27 UT	Ty	2C
94, CZ-3	07011	DFH 75	13 Apr 2007 at 20:11 UT	Xi	3A
95, CZ-3	07018	Nigcomsat 1	13 May 2007 at 16:01 UT	Xi	3B	200 x 41600 km x 25°
96, CZ-2	07019	Yaogan 2	25 May 2007 at 07:12 UT	Ji	2D
97, CZ-3	07021	Sinosat 3	31 May 2007 at 16:08 UT	Xi	3A
98, CZ-3	07031	Chinasat 6B	5 Jul 2007 at 12:08 UT	Xi	3B
99, CZ-4	07042	CBERS 2B	19 Sep 2007 at 03:26 UT	Xi	4B
100, CZ-3	07051	Chang'e 1	24 Oct 2007 at 10:05 UT	Xi	3A	Moon probe, non-earth orbit
101, CZ-4	07055	Yaogan 3	11 Nov 2007 at 22:48 UT	Ty	4C
102, CZ-3	08019	DFH 76	25 Apr 2008 at 22:16 UT	Xi	3C
103, CZ-4	08026	DFH 77	27 May 2008 at 03:02 UT	Ty	4C
104, CZ-3	08028	Chinasat 9	9 Jun 2008 at 12:15 UT	Xi	3B
105, CZ-2	08041	DFH 78 DFH 79	6 Sep 2008 at 03:25 UT	Ty	2C
106, CZ-2	08047	Shenzou 7 Bx 1 (unknown sub-satellite, 40 kg)	25 Sep 2008 at 13:10 UT	Ji	2F	Manned mission 200 x 344 km x 43°
107, CZ-4	08053	DFH 80 DFH 81	25 Oct 2008 at 00:15 UT	Ty	4B
108, CZ-3	08055	Venesat 1	29 Oct 2008 at 16:53 UT	Xi	3B
109, CZ-2	08056	A: DFH 82 B: Chuangxin 2	5 Nov 2008 at 00:15 UT	Ji	2D
110, CZ-2	08061	Yaogan 4	01 Dec 2008 at 04:42 UT	Ji	2D
111, CZ-4	08064	Yaogan 5	15 Dec 2008 at 03:22 UT	Ty	4B
112, CZ-3	08066	DFH 83	23 Dec 2008 at 00:54 UT	Xi	3A
113, CZ-3	09018	DFH 84	15 Apr 2009 at 16:16 UT	Xi	3C
114, CZ-2	09021	Yaogan 6	22 Apr 2009 at 02:55 UT	Ty	2C
115, CZ-3	09046	Palapa D	31 Aug 2009 at 09:28 UT	Xi	3B	Partial failure of the 3rd stage. Payload left in 225 x 21.160 km x 22°
116, CZ-2	09061	DFH 85	12 Nov 2009 at 02:45 UT	Ji	2C
117, CZ-2	09069	Yaogan 7	09 Dec 2009 at 08:42 UT	Ty	2D
118, CZ-4	09072	A: Yaogan 8 B: XiWang 1	15 Dec 2009 at 02:31 UT	Ty	4C
119, CZ-3	10001	DFH 86	16 Jan 2010 at 16:12 UT	Xi	3C
120, CZ-4	10009	A: Yaogan 9 B: Yaogan 9B C: Yaogan 9C	5 Mar 2010 at 04:55 UT	Ji	4C
121, CZ-3	10024	DFH 87	2 Jun 2010 at 15:53 UT	Xi	3C
122, CZ-2	10027	DFH 88	15 Jun 2010 at 01:39 UT	Ji	2D
123, CZ-3	10036	DFH 89	31 Jul 2010 at 21:30 UT	Xi	3A
124, CZ-4	10038	Yaogan 10	9 Aug 2010 at 22:49 UT	Ty	4C
125, CZ-2	10040	DFH 90	24 Aug 2010 at 07:10 UT	Ji	2D
126, CZ-3	10042	Sinosat 6	04 Sep 2010 at 16:14 UT	Xi	3B
127, CZ-2	10047	A: Yaogan 11 B: Zheda Pixing 1A-1 C: Zheda Pixing 1A-2	22 Sep 2010 at 02:42 UT	Ji	2D
128, CZ-3	10050	Chang'e 2	2 Oct 2010 at 10:59 UT	Xi	3C	Moon probe, non-earth orbit
129, CZ-4	10051	A: DFH 91 B: DFH 92	6 Oct 2010 at 00:49 UT	Ty	4B
130, CZ-3	10057	DFH 93	31 Oct 2010 at 16:26 UT	Xi	3C
131, CZ-4	10059	DFH 94	5 Nov 2010 at 18:37 UT	Ty	4C
132, CZ-3	10064	DFH 95	24 Nov 2010 at 16:09 UT	Xi	3A
133, CZ-3	10068	DFH 96	17 Dec 2010 at 20:20 UT	Xi	3A
134, CZ-3	11013	DFH 97	9 Apr 2011 at 20:47 UT	Xi	3A
135, CZ-3	11026	Sinosat 5	20 Jun 2011 at 16:13 UT	Xi	3B
131, CZ-2	11030	DFH 98	6 Jul 2011 at 04:28 UT	Ji	2C
132, CZ-3	11032	DFH 99	11 Jul 2011 at 15:41 UT	Xi	3C
133, CZ-3	11038	DFH 100	26 Jul 2011 at 21:44 UT	Xi	3A
134, CZ-2	11039	DFH 101	29 Jul 2011 at 07:42 UT	Ji	2C
135, CZ-3	11042	Paksat 1R	11 Aug 2011 at 16:15 UT	Xi	3B
136, CZ-4	11043	DFH 102	15 Aug 2011 at 22:57 UT	Ty	4B
137, CZ-2	n/a	DFH (Shijian 11-04)	18 Aug 2011 at 09:28 UT	Jq	2C	Failure: second stage did not ignite (failed connection between components)
138, CZ-3	11047	Chinasat 1A	18 Sep 2011 at 16:33 UT	Xi	3B/E
139, CZ-2	11052	Tiangong 1	29 Sep 2011 at 13:36 UT	Ji	2FT1	8500 kg, 10.4 m x 3.35 m diameter, first manned module
140, CZ-3	11057	Eutelsat W3C	7 Oct 2011 at 08:20 UT	Xi	3B/E
141, CZ-3	11063	Shenzhou 8	31 Oct 2011 at 21:58 UT	Ji	2F/H	To rendezvous with Tiangong 1
142, CZ-4	11066	A: DFH 103 B: Yaogan 12	09 Nov 2011 at 03:21 UT	Ty	4B
143, CZ-2	11068	A: Chuangxin 3 B: DFH 104	20 Nov 2011 at 00:15 UT	Ji	2D
144, CZ-2	11072	Yaogan 13	30 Nov 2011 at 18:50 UT	Ty	2C
145, CZ-3	11073	DFH 105	2 Dec 2011 at 21:07 UT	Xi	3A
146, CZ-3	11077	Nigcomsat 1R	19 Dec 2011 at 16:41 UT	Xi	3B
147, CZ-4	11079	CBERS 2C	22 Dec 2011 at 03:26 UT	Ty	4B
148, CZ-4	12001	A: DFH 106 B: Vesselsat 2	9 Jan 2012 at 03:17 UT	Ty	4B
149, CZ-3	12002	DFH 107	13 Jan 2012 at 00:56 UT	Xi	3A
150, CZ-3	12008	DFH 108	24 Feb 2012 at 16:12 UT	Xi	3C
151, CZ-3	12013	Apstar 7	31 Mar 2012 at 10:27 UT	Xi	3B/E
152, CZ-3	12018	DFH 109 DFH 110	29 Apr 2012 at 20:50 UT	Xi	3B
153, CZ-2	12020	DFH 111	6 May 2012 at 07:10 UT	Ji	2D
154, CZ-4	12021	A: Yaogan 14 B: DFH 112	10 May 2012 at 07:06 UT	Ty	4B
155, CZ-3	12028	Chinasat 2A	26 May 2012 at 15:56 UT	Xi	3B/E
156, CZ-4	12029	Yaogan 15	29 May 2012 at 07:31 UT	Ty	4C
157, CZ-2	12032	Shenzhou 9	16 Jun 2012 at 10:37 UT	Ji	2F
158, CZ-3	12040	DFH 113	25 Jul 2012 at 15:43 UT	Xi	3C
159, CZ-3	12050	DFH 114 DFH 115	18 Sep 2012 at 18:30 UT	Xi	3B/E
160, CZ-2	12052	VRSS 1	30 Sep 2012 at 04:12 UT	Ji	2D
161, CZ-2	12056	DFH 116 DFH 117	13 Oct 2012 at 03:25 UT	Ty	2C
162, CZ-3	12059	DFH 118	25 Oct 2012 at 15:35 UT	Xi	3C
163, CZ-2	12064	A: DFH 119 B: DFH 120 C: DFH 121	18 Nov 2012 at 22:53 UT	Ty	2C
164, CZ-4	12066	Yaogan 16	25 Nov 2012 at 04:06 UT	Ji	4C
165, CZ-3	12067	Chinasat 12	27 Nov 2012 at 10:13 UT	Xi	3B/E
166, CZ-2	12073	Gokturk 2	18 Dec 2012 at 16:12 UT	Ji	2D

Notes: Launch sites: Xi = Xichang, Ji = Jiuquan, Ty = Taiyuan

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FB-1 launches

#	Launch id	Payload	Launch date	Type	Status/Comment (orbit in perigee x apogee x inc. x period)
1, FB-1	n/a	R&D suborbital	10 Aug 1972
2, FB-1	n/a	JSSW?	18 Sep 1973		Failure
3, FB-1	n/a	JSSW?	14 Jul 1974		Failure: 2nd stage engine lost thrust
4, FB-1	75070	JSSW 1	26 Jul 1975
5, FB-1	75119	JSSW 2	16 Dec 1975
6, FB-1	76087	JSSW 3	30 Aug 1976
7, FB-1	n/a	JSSW?	10 Nov 1976		Failure
8, FB-1	n/a	(suborbital)	14 Sep 1977
9, FB-1	n/a	(suborbital)	16 Apr 1978
10, FB-1	n/a	SJ?	27 Jul 1979		Failure: 2nd stage thrusters failure
11, FB-1	81093	A: SJ 2 B: SJ 3A C: SJ 3B	19 Sep 1981

Notes: All launches from Juiquan.

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