Proposed launch vehicle derived from the CZ-1, but with a new N2O4/UDMH second stage. Used for a suborbital re-entry vehicle test but never flown on an orbital mission.

Launches: 1. Failures: 0. Success Rate: 100.00% pct. First Launch Date: 01 June 1995. Last Launch Date: 01 June 1995. LEO Payload: 740 kg. to: 300 km Orbit. Payload: 440 kg. to a: Geosynchronous transfer trajectory. Liftoff Thrust: 112,290 kgf. Total Mass: 79,400 kg. Core Diameter: 2.3 m. Total Length: 28.2 m. Launch Price $: 12.00 million. in 1994 price dollars.

• Stage Number: 1. 1 x CZ-1-1 Gross Mass: 64,100 kg. Empty Mass: 4,100 kg. Thrust (vac): 124,872 kgf. Isp: 268 sec. Burn time: 130 sec. Isp(sl): 241 sec. Diameter: 2.3 m. Span: 4.0 m. Length: 17.8 m. Propellants: Nitric acid/UDMH No Engines: 4. YF-2A

• Stage Number: 2. 1 x CZ-1D-2 Gross Mass: 14,850 kg. Empty Mass: 2,650 kg. Thrust (vac): 29,980 kgf. Isp: 287 sec. Burn time: 120 sec. Isp(sl): 260 sec. Diameter: 2.3 m. Span: 2.3 m. Length: 5.4 m. Propellants: N2O4/UDMH No Engines: 1. YF-3

• Stage Number: 3. 1 x CZ-1D-3 Gross Mass: 875 kg. Empty Mass: 150 kg. Thrust (vac): 2,000 kgf. Isp: 291 sec. Burn time: 100 sec. Isp(sl): 200 sec. Diameter: 2.0 m. Span: 2.0 m. Length: 2.2 m. Propellants: Solid No Engines: 1. CZ-1D-3

• Reentry Test Spacecraft: Reentry Test.

  Suborbital.

• 42 - Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991.
• 61 - Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al.