Taiyuan LC1 (original) (raw)

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Taiyuan LC1

Part of Taiyuan

CZ launch complex. Pad 1

Longitude: 111.61 deg. Latitude: 38.85 deg.

Country: China. Spacecraft: JB-3, CAST2000, CAST968, Phoenix Eye, SJ, FY-1, LM 700, SACI, ZY, HY-1, CX-1, SJ-6, JB-5. Launch Vehicles: Chang Zheng 4, Chang Zheng 2C-III/SD, Chang Zheng 4B, Chang Zheng 4C. Launch Sites: Taiyuan.

1988 September 6 - . 20:30 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4.

FY-1A - . Payload: Feng Yun 1A. Mass: 750 kg (1,650 lb). Nation: China. Agency: MAI. Class: Technology. Type: Weather technology satellite. Spacecraft: FY-1. USAF Sat Cat: 19467 . COSPAR: 1988-080A. Apogee: 895 km (556 mi). Perigee: 875 km (543 mi). Inclination: 98.80 deg. Period: 102.70 min. Experimental weather satellite. First use of new launch site and launch vehicle. Failed after 38 days due to problems with attitude control system..

1990 September 3 - . 00:53 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4.

FY-1B - . Payload: Feng Yun 1B. Mass: 881 kg (1,942 lb). Nation: China. Agency: MAI. Class: Technology. Type: Weather technology satellite. Spacecraft: FY-1. USAF Sat Cat: 20788 . COSPAR: 1990-081A. Apogee: 897 km (557 mi). Perigee: 875 km (543 mi). Inclination: 98.80 deg. Period: 102.70 min. Experimental weather satellite. Operated for over a year..
QQW 1 - . Payload: QQW 1A. Mass: 4.00 kg (8.80 lb). Nation: China. Agency: MAI. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SJ. Decay Date: 1991-03-11 . USAF Sat Cat: 20789 . COSPAR: 1990-081B. Apogee: 811 km (503 mi). Perigee: 789 km (490 mi). Inclination: 99.00 deg. Period: 100.90 min. QQW atmospheric balloon..
QQW 2 - . Payload: QQW 1B. Mass: 4.00 kg (8.80 lb). Nation: China. Agency: MAI. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SJ. Decay Date: 1991-07-24 . USAF Sat Cat: 20790 . COSPAR: 1990-081C. Apogee: 629 km (390 mi). Perigee: 596 km (370 mi). Inclination: 99.00 deg. Period: 97.00 min. QQW atmospheric balloon..

1997 September 1 - . 14:00 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 2C-III/SD.

Iridium - . Payload: Iridium s/n MFS 1. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 24925 . COSPAR: 1997-048A. Apogee: 633 km (393 mi). Perigee: 620 km (380 mi). Inclination: 86.34 deg. Period: 97.25 min. Plane 5. Ascending node 271.9 degrees. Dummy satellite..
Iridium - . Payload: Iridium s/n MFS 2. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 24926 . COSPAR: 1997-048B. Apogee: 634 km (393 mi). Perigee: 620 km (380 mi). Inclination: 86.34 deg. Period: 97.26 min. Plane 5. Ascending node 272 degrees. Dummy satellite..

1997 December 8 - . 07:16 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 2C-III/SD.

Iridium 42 - . Payload: Iridium s/n SV042. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25077 . COSPAR: 1997-077A. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 6. Ascending node 325.8 degrees..
Iridium 44 - . Payload: Iridium s/n SV044. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25078 . COSPAR: 1997-077B. Apogee: 780 km (480 mi). Perigee: 774 km (480 mi). Inclination: 86.39 deg. Period: 100.40 min. Plane 6. Ascending node 325.8 degrees. Not in service..

1998 March 25 - . 17:01 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 2C-III/SD.

Iridium 51 - . Payload: Iridium s/n SV051. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25262 . COSPAR: 1998-018A. Apogee: 756 km (469 mi). Perigee: 751 km (466 mi). Inclination: 86.45 deg. Period: 99.90 min. Plane 4. Ascending node 262.5 degrees. Not in service..
Iridium 61 - . Payload: Iridium s/n SV061. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25263 . COSPAR: 1998-018B. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 4. Ascending node 262.5 degrees..

1998 May 2 - . 09:16 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 2C-III/SD.

Iridium 69 - . Payload: Iridium s/n SV069. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25319 . COSPAR: 1998-026A. Apogee: 783 km (486 mi). Perigee: 777 km (482 mi). Inclination: 86.40 deg. Period: 100.46 min. Plane 2. Ascending node 199.4 degrees. Not in service..
Iridium 71 - . Payload: Iridium s/n SV071. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25320 . COSPAR: 1998-026B. Apogee: 778 km (483 mi). Perigee: 775 km (481 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 199.3 degrees. Not in service..

1998 August 19 - . 23:01 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 2C-III/SD.

Iridium 3 - . Payload: Iridium s/n SV078. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-02-08 . USAF Sat Cat: 25431 . COSPAR: 1998-048A. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 199.4 degrees..
Iridium 76 - . Payload: Iridium s/n SV076. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-08-28 . USAF Sat Cat: 25432 . COSPAR: 1998-048B. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 199.4 degrees..

1998 December 19 - . 11:39 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 2C-III/SD.

Iridium 11 - . Payload: Iridium s/n SV088?. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-10-22 . USAF Sat Cat: 25577 . COSPAR: 1998-074A. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 197 degrees. Parking orbit..
Iridium 20 - . Payload: Iridium s/n SV089?. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-10-22 . USAF Sat Cat: 25578 . COSPAR: 1998-074B. Apogee: 710 km (440 mi). Perigee: 709 km (440 mi). Inclination: 86.50 deg. Period: 99.00 min. Plane 2. Ascending node 197.2 degrees. Parking orbit..

1999 May 10 - . 01:33 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.

FY-1C - . Payload: Feng Yun 1C. Mass: 900 kg (1,980 lb). Nation: China. Agency: CASC. Manufacturer: Shanghai Institute of Satellite Engineering. Class: Earth. Type: Weather satellite. Spacecraft: FY-1. USAF Sat Cat: 25730 . COSPAR: 1999-025A. Apogee: 880 km (540 mi). Perigee: 846 km (525 mi). Inclination: 98.80 deg. Period: 102.20 min. Operational weather satellite. First launch of stretched CZ-4B booster. After retirement the satellite was destroyed in the first test of the Chinese ASAT weapon on 11 January 2007..
SJ-5 - . Payload: Shi Jian 5. Mass: 500 kg (1,100 lb). Nation: China. Agency: CASC. Manufacturer: Shanghai Institute of Satellite Engineering. Class: Earth. Type: Magnetosphere satellite. Spacecraft: CAST2000. USAF Sat Cat: 25731 . COSPAR: 1999-025B. Apogee: 865 km (537 mi). Perigee: 841 km (522 mi). Inclination: 98.90 deg. Period: 102.00 min. Research satellite carried as a secondary payload to study the radiation belts..

1999 June 11 - . 17:15 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 2C-III/SD.

Iridium 14A - . Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25777 . COSPAR: 1999-032A. Apogee: 711 km (441 mi). Perigee: 708 km (439 mi). Inclination: 86.50 deg. Period: 99.00 min.
Iridium 21A - . Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-05-24 . USAF Sat Cat: 25778 . COSPAR: 1999-032B. Apogee: 711 km (441 mi). Perigee: 708 km (439 mi). Inclination: 86.50 deg. Period: 99.00 min.

1999 October 14 - . 03:15 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.

CBERS-1 ZY-1 FM1 - . Payload: Zi Yuan 1. Mass: 1,450 kg (3,190 lb). Nation: China. Agency: SISE. Manufacturer: CAST, INP. Class: Earth. Type: Earth resources satellite. Spacecraft: Phoenix Eye. USAF Sat Cat: 25940 . COSPAR: 1999-057A. Apogee: 780 km (480 mi). Perigee: 773 km (480 mi). Inclination: 98.20 deg. Period: 100.40 min.
China-Brazil Earth Resources Satellite. China's first earth resources satellite, known as ZY-1, weighed 1,540 kilograms. Chief designer was Chen Yiyuan. The satellite, a joint project of China and Brazil, was designed to gather information on the environment, agriculture and urban planning through remote sensing images and data transmitted to China, Brazil and other countries. Planned lifetime was two years. The satellite circled the Earth 14 times a day and the groundtrack repeated after 26 days. By 23 February 2000 it had taken more than 20,000 high quality images. It was formally handed over for operational use on March 2 2000. The High Resolution CCD Camera had a resolution of 20 meters in the visible spectrum. The camera could point up to 32 degrees to either side of vertical, imaging the earth's surface stereoscopically. After 177 days the Wide Field Imager failed in early May 2000. Other devices, including the high resolution CCD camera, continue to work normally.
SACI 1 - . Nation: Brazil. Agency: SISE. Manufacturer: INPE. Class: Technology. Type: Navigation technology satellite. Spacecraft: SACI. USAF Sat Cat: 25941 . COSPAR: 1999-057B. Apogee: 731 km (454 mi). Perigee: 719 km (446 mi). Inclination: 98.70 deg. Period: 99.30 min. INPE experimental scientific satellite with a magnetometer, particle detectors and an atmospheric experiment. INPE reportedly lost contact with the satellite in mid-October..

2000 September 1 - . 03:25 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.

ZY-2C - . Payload: Zi Yuan 2. Mass: 2,600 kg (5,700 lb). Nation: China. Agency: SISE. Manufacturer: CAST. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Jianbing. Spacecraft: JB-3. Decay Date: 2016-03-11 . USAF Sat Cat: 26481 . COSPAR: 2000-050A. Apogee: 501 km (311 mi). Perigee: 489 km (303 mi). Inclination: 97.40 deg. Period: 94.43 min.
The ZY-2 (Ziyuan-2 ('Resource-2'), while disguised as a civilian earth monitoring system, was actually code-named Jianbing-3 and was China's first high-resolution military imaging satellite. The cover story of the official Xinhua news agency was that the civilian remote sensing system would be used primarily in territorial surveying, city planning, crop yield assessment, disaster monitoring and space science experimentation. However the satellite was placed at a much lower altitude than the ZY-1 satellite and US intelligence sources indicated that it was a photo-reconnaissance satellite for exclusively military purposes, such as targeting missiles at US and Taiwanese forces. The new satellite was believed to employ digital-imaging technology and to have a resolution of 2 m or less. The satellite was designed and built by the Chinese Academy of Space Technology and was developed indigenously. It was said to be more advanced than earlier sensing satellites and was expected to have an orbital life of two years. The camera provided more than three times the resolution of the ZY-1 earth resources satellite. The Zi Yuan 2 satellite may have used the CBERS Sino-Brazilian bus of the earlier ZY-1. However it was also said to be of new design and demonstrated the capability to maneuver in orbit, adjusting its orbit after launch. In October 2000 Chinese scientists denied that the ZY-2 satellite had a military mission. It was said to be a remote-sensing satellite equipped with CCD cameras and an infrared multispectral scanner that could only identify objects on the ground with a resolution of several dozen meters to 1 km.

2002 May 15 - . 01:50 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.

HY-1A - . Payload: Haiyang 1. Mass: 367 kg (809 lb). Nation: China. Agency: CASC. Class: Earth. Type: Earth resources satellite. Spacecraft: CAST968. USAF Sat Cat: 27430 . COSPAR: 2002-024A. Apogee: 799 km (496 mi). Perigee: 785 km (487 mi). Inclination: 98.40 deg. Period: 100.70 min.
The HY-1 (Haiyang-1) marine observation satellite separated shortly after the FY-1D. The 360 kg HY-1 was based on the SJ-5 bus and carried an IR radiometer and CCD imager for oceanographic studies. Between May 21 and May 26, HY-1 lowered its orbit to 793 x 799 km using on-board propulsion.
FY-1D - . Mass: 960 kg (2,110 lb). Nation: China. Agency: CASC. Class: Earth. Type: Weather satellite. Spacecraft: FY-1. USAF Sat Cat: 27431 . COSPAR: 2002-024B. Apogee: 873 km (542 mi). Perigee: 850 km (520 mi). Inclination: 98.70 deg. Period: 102.20 min.
The second stage separated six minutes after launch, putting the stack on a suborbital trajectory. After a brief coast up to 860 km the third stage fired at around 0200 UTC to circularize the orbit. FY-1D, a 950 kg weather satellite with a 10-channel radiometer, separated from the stack followed by a small adapter. The final stage was left in a slightly lower 812 x 883 km orbit.

2002 October 27 - . 03:17 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.

ZY-2B - . Payload: Zi Yuan 2-2. Mass: 2,500 kg (5,500 lb). Nation: China. Agency: CAST. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: Jianbing. Spacecraft: JB-3. Decay Date: 2015-01-22 . USAF Sat Cat: 27550 . COSPAR: 2002-049A. Apogee: 483 km (300 mi). Perigee: 470 km (290 mi). Inclination: 97.40 deg. Period: 94.10 min.
JB-3 2 was nominally a Chinese (PRC) remote sensing satellite, although US intelligence sources indicated it had primarily an intelligence imaging mission. JB-3 2 was the name adopted by the USSPACECOM. Most news reports from China and elsewhere use different names: ZY-2B (acronym for ZiYuan-2B, translated as Resource-2B), and Zhong Guo Zi Yuan Er Hao, translated as China Resource 2. No information was available on the instruments onboard the JB-3 2, but officially it was intended 'for territorial survey, environment monitoring and protection, urban planning, crop yield assessment, disaster monitoring, and space scientific experiments'. The initial orbital parameters of this sun-synchronous satellite were period 94.1 min, apogee 483 km, perigee 470 km, and inclination 97.4�.

2003 October 21 - . 03:16 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.

CBERS-2 ZY-1 FM2 - . Payload: Zi Yuan 1B. Mass: 1,450 kg (3,190 lb). Nation: China. Agency: CAS. Class: Earth. Type: Earth resources satellite. Spacecraft: Phoenix Eye. USAF Sat Cat: 28057 . COSPAR: 2003-049A. Apogee: 750 km (460 mi). Perigee: 731 km (454 mi). Inclination: 98.50 deg. Period: 99.60 min. Delayed from late 2001, September 3 2002, March 14 and September 2003. Second China-Brazil Earth Resources Satellite (CBERS 2)..
Chuangxin-1 - . Payload: Chuang Xin 1. Mass: 90 kg (198 lb). Nation: China. Agency: CAS. Class: Technology. Type: Communications technology satellite. Spacecraft: CX-1. USAF Sat Cat: 28058 . COSPAR: 2003-049B. Apogee: 759 km (471 mi). Perigee: 686 km (426 mi). Inclination: 98.50 deg. Period: 99.20 min.
Chuangxin-1 (or Innovation-1) was China's first experimental small satellite for store-and-forward short message data communications in low Earth orbit. With a mass less than 100 kg, the Chuangxin-1 was developed in light of national strategic demands. Starting from 1999 with support of the national Knowledge Innovation Program of the Chinese Academy of Sciences (CAS), the project was carried out jointly by researchers from the CAS Shanghai Institute of Microsystem Information Technology and the CAS Shanghai Institute of Technical Physics. The satellite used spread spectrum communication and subsystems included a communication transponder, onboard computer, attitude control, energy source, thermal control, and structure. The mission was to demonstrate data communications for such sectors as traffic and transportation, environment protection, oil and gas transportation, flood and drought control, detection of forest fire and earthquake monitoring.

2004 September 8 - . 23:14 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.

SJ-6-01A SJ-6A - . Payload: Shi Jian 6B. Mass: 800 kg (1,760 lb). Nation: China. Agency: SISE. Class: Technology. Type: Navigation technology satellite. Spacecraft: SJ-6. USAF Sat Cat: 28413 . COSPAR: 2004-035A. Apogee: 593 km (368 mi). Perigee: 578 km (359 mi). Inclination: 97.70 deg. Period: 96.40 min.
It was announced that the two satellites had a design life of at least two years, and would be used to probe the space environment, radiation and its effects, record space physical environment parameters, and conduct other related space experiments. The two satellites were built by the Shanghai Academy of Space Flight Technology and Dongfanghong Satellite Company under subcontract to the China Aerospace Science and Technology Corporation. The scientific instruments aboard the satellites were mainly manufactured by the China Electronics Technology Corporation. Some Western observors believed the mission of the satellites included electronic intelligence technology tests.
SJ-6-01B SJ-6B - . Payload: Shi Jian 6B. Mass: 800 kg (1,760 lb). Nation: China. Agency: SISE. Class: Technology. Type: Navigation technology satellite. Spacecraft: CAST2000. USAF Sat Cat: 28414 . COSPAR: 2004-035B. Apogee: 602 km (374 mi). Perigee: 593 km (368 mi). Inclination: 97.70 deg. Period: 96.60 min. CAST968 platform. Released one minute after SJ-6A..

2004 November 6 - . 03:10 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.

ZY-2C - . Mass: 2,600 kg (5,700 lb). Nation: China. Agency: SISE. Class: Earth. Type: Earth resources satellite. Spacecraft Bus: Jianbing. Spacecraft: JB-3. USAF Sat Cat: 28470 . COSPAR: 2004-044A. Apogee: 504 km (313 mi). Perigee: 479 km (297 mi). Inclination: 97.30 deg. Period: 94.40 min. Zi Yuan 2-3 was a low earth orbit digital imaging spacecraft used by the Chinese government, probably for both civilian and military reconnaissance purposes..

2006 April 26 - . 22:48 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4C.

Yaogan 1 - . Payload: Jianbing 5. Mass: 2,700 kg (5,900 lb). Nation: China. Agency: CNSA. Manufacturer: CASC. Class: Surveillance. Type: Military Radarsat. Spacecraft Bus: Jianbing. Spacecraft: JB-5. USAF Sat Cat: 29092 . COSPAR: 2006-015A. Apogee: 630 km (390 mi). Perigee: 627 km (389 mi). Inclination: 97.80 deg. Period: 97.30 min. Remote sensing satellite built by the Shanghai SAST Group. In reality it was the first Chinese synthetic aperture radar military surveillance satellite..

2006 October 23 - . 23:34 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4B.

SJ-6-02A SJ-6C - . Mass: 2,700 kg (5,900 lb). Nation: China. Agency: SISE. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft: SJ-6. USAF Sat Cat: 29505 . COSPAR: 2006-046A. Apogee: 598 km (371 mi). Perigee: 594 km (369 mi). Inclination: 97.70 deg. Period: 96.60 min. Replaced the SJ-6 Group 1 satellites A and B. Official purpose was to measure the space environment, but foreign analysts suspected a SIGINT role..
SJ-6-02B SJ-6D - . Mass: 2,700 kg (5,900 lb). Nation: China. Agency: SISE. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft: CAST2000. USAF Sat Cat: 29506 . COSPAR: 2006-046B. Apogee: 599 km (372 mi). Perigee: 598 km (371 mi). Inclination: 97.70 deg. Period: 96.70 min.

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