CZ-NGLV-200 Credit - © Mark Wade

The Long March New Generation Launch Vehicle series small launcher would use the 2.25 m diameter module as the first stage and a single upper stage of the same diameter (probably the existing YF-73 stage of the CZ-3). Payload was given as 1.5 tonnes into low earth orbit. First launch was expected after 2008. Although the configuration was not shown at the Wuzhai Air Show in 2002 it re-emerged at the FAI in 2003. It seemed to be in competition with the all-solid-propellant KT-1, KT-2, and KT-2A series.

China's family of new generation expendable launch vehicles were announced in February 2001, and modified descriptions were provided at the Wuzhai Air Show and IAC in late 2002. Propulsion system details and masses were released at the FAI in Bremen in September 2003. Boosters of various capabilities would be assembled from three modular stages of 2.25 m, 3.35 m and 5.0 m diameter. These would be powered by new variable-thrust 120 tonne thrust Lox/Kerosene engines or 50 tonne thrust Lox/LH2 engines as follows:

• 2.25 m diameter module powered by one 120 tonne thrust Lox/Kerosene engine
• 3.35 m diameter module powered by two 120 tonne thrust Lox/Kerosene engines
• 5.0 m diameter module powered by two 50 tonne thrust Lox/LH2 engines
• 5.0 m diameter upper stage powered by two 8 tonne thrust Lox/LH2 engines (a derivative of the CZ-3B upper stage)
• 3.35 m diameter upper stage powered by four 15 tonne thrust Lox/Kerosene engines, evidently an indigenous Chinese development
• 2.25 m diameter upper stage for the light launch vehicle (probably the CZ-4A third stage)
• Common large payload fairing, 5.2 m in diameter and coming in three standard lengths.

The new launch vehicles were said to be designed for a 98% reliability as compared to 91% for existing Chinese designs. They were also said to be expected to be 20% cheaper than existing designs. Chief Designer for the new series was Long Lehao.

The new family would use a unique 'direct-to-pad' integration concept using highly automated systems with a total cycle time of only 20 days. The launch vehicle was to be assembled vertically on the launch pad as soon as the stages arrived at the site. It would be checked out in a mobile service tower (MST). In parallel to this the payload would be integrated and encapsulated in a separate encapsulation facility. The encapsulated payload was to be transferred and mated to the launch vehicle only three days before launch.

Manufacturer: CALT. LEO Payload: 1,500 kg (3,300 lb). to: 300 km Orbit. at: 42.00 degrees. Liftoff Thrust: 1,200.000 kN (269,700 lbf). Total Mass: 82,000 kg (180,000 lb). Core Diameter: 2.25 m (7.38 ft). Total Length: 33.00 m (108.00 ft). Span: 2.25 m (7.38 ft).

• Stage Number: 1. 1 x Stage: CZ-NGLV-200. Gross Mass: 69,000 kg (152,000 lb). Empty Mass: 6,000 kg (13,200 lb). Thrust (vac): 1,340.170 kN (301,282 lbf). Isp: 336 sec. Burn time: 150 sec. Isp(sl): 301 sec. Diameter: 2.25 m (7.38 ft). Span: 4.60 m (15.00 ft). Length: 25.00 m (82.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: YF-120t. Status: In development. From top to bottom the 2.25-m Chinese new generation launch vehicle consists of a 42.3 cubic meter liquid oxygen tank, an intertank section, a 22.0 cubic meter kerosene tank, and an engine section with one gimballed LOX /Kerosene engines of 1200 kN vacuum thrust. The oxygen tank is pressurised using oxygen bled from the engine and helium is used to pressurise the kerosene tank. The engines can be throttled to 65% of rated thrust. Burn time shown assumes full thrust during engine burn.

• Stage Number: 2. 1 x Stage: CZ-3-3. Gross Mass: 10,500 kg (23,100 lb). Empty Mass: 2,000 kg (4,400 lb). Thrust (vac): 44.100 kN (9,914 lbf). Isp: 425 sec. Burn time: 800 sec. Diameter: 2.25 m (7.38 ft). Span: 2.25 m (7.38 ft). Length: 7.48 m (24.54 ft). Propellants: Lox/LH2. No Engines: 4. Engine: YF-73. Other designations: H-8. Status: In development.

• 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/.

• Yihua Tang, Xiaojun Wang, Tangming Cheng, The Sketch of a New Generation Launch Vehicle of Long-March Family, "International Astronautical Congress, 2002", IAC-02-V.1.04.

• Video presentation, IAF Bremen, September 2003.

• Tangming Cheng, Xiaojun Wang, Dong Li, "The New Generation Launch Vehicles of Long March Family", IAF 2003.