CZ-2

On April 28, 1993, the Chinese Great Wall Industrial Corporation and Motorola signed a launch services contract for multiple launch of Iridium communications satellites using CZ-2C/SD launch vehicles. The main differences between the CZ-2C and the CZ-2C/SD were: a modified fairing with a diameter of 3.35m; a newly developed Smart Dispenser; improved second stage fuel and oxidizer tanks; and second stage engines with higher expansion ratio nozzles.

The Smart Dispenser included a solid rocket kick motor for insertion of the Iridium satellites into a 780 km circular orbit. Each CZ-2C/SD had the capacity of delivering two Iridium system satellites. A successful CZ-2C/SD demonstration launch was conducted from Taiyuan on September 1, 1997. The first three deployment launches for the Iridium program were successfully conducted on December 8, 1997, March 26, 1998 and May 2, 1998. Another variant of the vehicle was announced in May 2001 when it was announced that the DoubleStar and KOMPSAT-2 satellites would be launched by a CZ-2C with a CTS upper stage. This was apparently a further development of the SD and was a three-axis stabilised upper stage consisting of a Spacecraft Adapter and an Orbital Maneuver System. It was capable of putting 1400 kg of payload into a 900 km sun-synchronous orbit.

Manufacturer: Shanghai Academy of Spaceflight Technology. Launches: 7. Success Rate: 100.00%. First Launch Date: 1997-09-01. Last Launch Date: 1999-06-11. Launch data is: continuing. LEO Payload: 2,800 kg (6,100 lb). Payload: 1,400 kg (3,000 lb). to a: 780 km, 86 deg inclination orbital trajectory. Apogee: 1,000 km (600 mi). Associated Spacecraft: LM 700. Liftoff Thrust: 2,960.000 kN (665,430 lbf). Total Mass: 213,000 kg (469,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 40.40 m (132.50 ft). Launch Price $: 25.000 million. in: 1999 price dollars.

• Stage Number: 1. 1 x Stage: CZ-2C-1. Gross Mass: 153,000 kg (337,000 lb). Empty Mass: 10,000 kg (22,000 lb). Thrust (vac): 3,295.000 kN (740,745 lbf). Isp: 291 sec. Burn time: 122 sec. Isp(sl): 261 sec. Diameter: 3.35 m (10.99 ft). Span: 6.00 m (19.60 ft). Length: 20.52 m (67.32 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: YF-20A. Other designations: L-140. Status: Out of production.

• Stage Number: 2. 1 x Stage: CZ-2C/SD-2. Gross Mass: 55,000 kg (121,000 lb). Empty Mass: 5,000 kg (11,000 lb). Thrust (vac): 761.900 kN (171,282 lbf). Isp: 298 sec. Burn time: 190 sec. Isp(sl): 270 sec. Diameter: 3.35 m (10.99 ft). Span: 3.35 m (10.99 ft). Length: 10.00 m (32.00 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: YF-22A/23A. Other designations: L-35. Status: Out of production. Stretched version of CZ-2C second stage. Empty mass estimated.

1997 September 1 - 14:00 GMT - Launch Site: Taiyuan. Launch Complex: LC1. Launch Pad: LC1. Launch Vehicle: CZ-2C/SD. Model: Chang Zheng 2C-III/SD. LV Configuration: Chang Zheng 2C-III/SD CZ2C-15 (47).

• Iridium Nation: USA. Program: Iridium. Payload: Iridium s/n MFS 1. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Agency: CASC. Perigee: 620 km (380 mi). Apogee: 633 km (393 mi). Inclination: 86.34 deg. Period: 97.25 min. COSPAR: 1997-048A. USAF Sat Cat: 24925. Plane 5. Ascending node 271.9 degrees. Dummy satellite. References: 4.

• Iridium Nation: USA. Program: Iridium. Payload: Iridium s/n MFS 2. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Agency: CASC. Perigee: 620 km (380 mi). Apogee: 634 km (393 mi). Inclination: 86.34 deg. Period: 97.26 min. COSPAR: 1997-048B. USAF Sat Cat: 24926. Plane 5. Ascending node 272 degrees. Dummy satellite. References: 4.

• Iridium 42 Nation: USA. Program: Iridium. Payload: Iridium s/n SV042. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Agency: Iridium. Perigee: 776 km (482 mi). Apogee: 780 km (480 mi). Inclination: 86.40 deg. Period: 100.40 min. COSPAR: 1997-077A. USAF Sat Cat: 25077. Plane 6. Ascending node 325.8 degrees. References: 4.

• Iridium 44 Nation: USA. Program: Iridium. Payload: Iridium s/n SV044. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Agency: Iridium. Perigee: 774 km (480 mi). Apogee: 780 km (480 mi). Inclination: 86.39 deg. Period: 100.40 min. COSPAR: 1997-077B. USAF Sat Cat: 25078. Plane 6. Ascending node 325.8 degrees. Not in service. References: 4.

• Iridium 51 Nation: USA. Program: Iridium. Payload: Iridium s/n SV051. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Agency: Iridium. Manufacturer: LM-S/Motorola. Perigee: 751 km (466 mi). Apogee: 756 km (469 mi). Inclination: 86.45 deg. Period: 99.90 min. COSPAR: 1998-018A. USAF Sat Cat: 25262. Plane 4. Ascending node 262.5 degrees. Not in service.

• Iridium 61 Nation: USA. Program: Iridium. Payload: Iridium s/n SV061. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Agency: Iridium. Manufacturer: LM-S/Motorola. Perigee: 776 km (482 mi). Apogee: 780 km (480 mi). Inclination: 86.40 deg. Period: 100.40 min. COSPAR: 1998-018B. USAF Sat Cat: 25263. Plane 4. Ascending node 262.5 degrees.

• Iridium 69 Nation: USA. Program: Iridium. Payload: Iridium s/n SV069. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Agency: Iridium. Manufacturer: LM-S/Motorola. Perigee: 777 km (482 mi). Apogee: 783 km (486 mi). Inclination: 86.40 deg. Period: 100.46 min. COSPAR: 1998-026A. USAF Sat Cat: 25319. Plane 2. Ascending node 199.4 degrees. Not in service.

• Iridium 71 Nation: USA. Program: Iridium. Payload: Iridium s/n SV071. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Agency: Iridium. Manufacturer: LM-S/Motorola. Perigee: 775 km (481 mi). Apogee: 778 km (483 mi). Inclination: 86.40 deg. Period: 100.40 min. COSPAR: 1998-026B. USAF Sat Cat: 25320. Plane 2. Ascending node 199.3 degrees. Not in service.

• Iridium 3 Nation: USA. Program: Iridium. Payload: Iridium s/n SV078. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Agency: Iridium. Manufacturer: LM-S/Motorola. Perigee: 776 km (482 mi). Apogee: 779 km (484 mi). Inclination: 86.40 deg. Period: 100.40 min. COSPAR: 1998-048A. USAF Sat Cat: 25431. Plane 2. Ascending node 199.4 degrees.

• Iridium 76 Nation: USA. Program: Iridium. Payload: Iridium s/n SV076. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Agency: Iridium. Manufacturer: LM-S/Motorola. Perigee: 776 km (482 mi). Apogee: 780 km (480 mi). Inclination: 86.40 deg. Period: 100.40 min. COSPAR: 1998-048B. USAF Sat Cat: 25432. Plane 2. Ascending node 199.4 degrees.

• Iridium 11 Nation: USA. Program: Iridium. Payload: Iridium s/n SV088?. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Agency: Iridium. Manufacturer: LM-S/Motorola. Perigee: 776 km (482 mi). Apogee: 780 km (480 mi). Inclination: 86.40 deg. Period: 100.40 min. COSPAR: 1998-074A. USAF Sat Cat: 25577. Plane 2. Ascending node 197 degrees. Parking orbit.

• Iridium 20 Nation: USA. Program: Iridium. Payload: Iridium s/n SV089?. Mass: 689 kg (1,518 lb). Class: Communications. Spacecraft: LM 700. Agency: Iridium. Manufacturer: LM-S/Motorola. Perigee: 709 km (440 mi). Apogee: 710 km (440 mi). Inclination: 86.50 deg. Period: 99.00 min. COSPAR: 1998-074B. USAF Sat Cat: 25578. Plane 2. Ascending node 197.2 degrees. Parking orbit.

• Iridium 14A Nation: USA. Program: Iridium. Class: Communications. Spacecraft: LM 700. Agency: Iridium. Manufacturer: LM-S/Motorola. Perigee: 708 km (439 mi). Apogee: 711 km (441 mi). Inclination: 86.50 deg. Period: 99.00 min. COSPAR: 1999-032A. USAF Sat Cat: 25777.

• Iridium 21A Nation: USA. Program: Iridium. Class: Communications. Spacecraft: LM 700. Agency: Iridium. Manufacturer: LM-S/Motorola. Perigee: 708 km (439 mi). Apogee: 711 km (441 mi). Inclination: 86.50 deg. Period: 99.00 min. COSPAR: 1999-032B. USAF Sat Cat: 25778.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Chen Lan, Dragon in Space, . The best source anywhere for information on current news regarding the Chinese space program. Accessed at: http://www.geocities.com/CapeCanaveral/Launchpad/1921/.

• Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004. ISBN: 156347591X. The best reference on launch vehicles ever produced. More at amazon.com...