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CZ-3A Space Launch Vehicle

With its limited payload capacity and the continued growth of GEO spacecraft, the CZ-3 was joined in 1994 by the CZ-3A. The new launch vehicle incorporates a lengthened first stage, a pair of more powerful LH/LOX YF-75 engines in the third stage, and an improved, light-weight flight control system. The LEO payload capacity of the CZ-3A is 6.5-metric tons (compared to 5.5 metric tons for the CZ-3) and the GTO payload capacity is 2.6 metric tons.

Both 1994 flights of the CZ-3A were successful, although the payload of the second mission malfunctioned and could not reach its intended orbit.

LM-3A (China)

Background Information First Launch: February 1994 Flight Rate: 2-3 per year Launch Site: Xichang Space Launch Center, China Capability: 15,800 lb to LEO; 5,500 lb to GTO (31.1 degrees) History Chinese rocket program started in the late 1950s Evolved from Chinese surface-to-surface series IRBMs LM-3A is enhanced version of the LM-3 (improved cryogenic upper stage) Description Three-stage liquid fueled vehicle Stage 1 consists of four YF-20B motors burning UDMH/N2O4 providing a total thrust of 665,450 lb Stage 2 uses one YF-22B engine and four YF-23B verniers burning UDMH/N2O4 for a total thrust of 177,200 lb Stage 3 uses two YF-75 engines burning LOX/LH2 providing a thrust of 35,200 lb Profile Length: 172 ft Launch Weight: 529,000 lb Diameter: 11 ft Liftoff Thrust: 665,450 lb Payload Fairing: 29.2 ft x 11.0 ft

Sources and Resources

• Long March 3A (LM-3A) @ CALT
• Space Launch Vehicles Secretary of the Air Force Acquisition - Space Programs Directorate
• Adapted from: Europe and Asia in Space 1993-1994, Nicholas Johnson and David Rodvold [Kaman Sciences / Air Force Phillips Laboratory]

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