CZ-NGLV-320/HO Credit - © Mark Wade

The Long March New Generation Launch Vehicle series medium launcher would use the 3.35 m diameter module and a new 3.35 m diameter second stage as the core vehicle. Either two or four 2.25 m diameter modules would be used as strap-ons. Payload to low earth orbit would be three tonnes with two strap-ons and 10 tonnes with four strap-ons. For geosynchronous or planetary missions the 5.0-m diameter HO fourth stage would be used. Payload to geosynchronous transfer orbit would be 1.5 tonnes with two strap-ons and six tonnes with four strap-ons. By late 2002 this version was no longer mentioned, then it re-emerged at the FAI in Bremen in 2003. However it was indicated that it had a lower priority since the payload range was covered by the existing CZ series of vehicles. Specifically it was said there was no plan to replace the CZ-2F as the launch vehicle for the Shenzhou manned spacecraft with the new 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: 10,000 kg (22,000 lb). to: 200 km Orbit. at: 42.00 degrees. Payload: 6,000 kg (13,200 lb). to a: geosynchronous transfer orbital trajectory. Liftoff Thrust: 7,200.000 kN (1,618,600 lbf). Total Mass: 420,000 kg (920,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 55.00 m (180.00 ft). Span: 8.00 m (26.20 ft).

• Stage Number: 1. 2 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-NGLV-300. Gross Mass: 147,000 kg (324,000 lb). Empty Mass: 12,000 kg (26,000 lb). Thrust (vac): 2,680.350 kN (602,567 lbf). Isp: 336 sec. Burn time: 160 sec. Isp(sl): 301 sec. Diameter: 3.35 m (10.99 ft). Span: 4.60 m (15.00 ft). Length: 26.30 m (86.20 ft). Propellants: Lox/Kerosene. No Engines: 2. Engine: YF-120t. Status: In development. From top to bottom the 3.35-m Chinese new generation launch vehicle consists of a 90.7 cubic meter liquid oxygen tank, an intertank section, a 47.7 cubic meter kerosene tank, and an engine section with two gimballed LOX /Kerosene engines of 1200 kN vacuum thrust each. 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: 3. 1 x Stage: CZ-NGLV-KO. Gross Mass: 60,000 kg (132,000 lb). Empty Mass: 7,000 kg (15,400 lb). Thrust (vac): 588.000 kN (132,187 lbf). Isp: 340 sec. Burn time: 300 sec. Diameter: 3.35 m (10.99 ft). Span: 3.35 m (10.99 ft). Length: 13.00 m (42.00 ft). Propellants: Lox/Kerosene. No Engines: 4. Status: In development. Upper stage for the 3.35 m diameter core vehicle. Only information available are the types of propellants, total thrust, and number of engines. Therefore all values shown here except thrust are estimated. This launcher has a low priority since its payload capability overlaps existing Chinese launch vehicles, and it would not be developed until after 2010.

• Stage Number: 4. 1 x Stage: CZ-NGLV-HO. Gross Mass: 26,000 kg (57,000 lb). Empty Mass: 3,100 kg (6,800 lb). Thrust (vac): 156.000 kN (35,070 lbf). Isp: 448 sec. Burn time: 600 sec. Diameter: 3.35 m (10.99 ft). Span: 5.00 m (16.40 ft). Length: 12.00 m (39.00 ft). Propellants: Lox/LH2. No Engines: 2. Engine: YF-75. Status: In development. The upper stage for the Chinese Next Generation Launch Vehicle is a modification of the CZ-3B upper stage. The stage uses a version of the Lox/LH2 YF-75 engine, simplified for improved reliability. The stage is of hammerhead form, with the upper LH2 tank with a diameter of 5 m, and the lower liquid oxygen tank with a diameter of 3.35 m. The total propellant is 22,900 kg with a burn time of over 600 seconds. Empty mass has not yet been released and is estimated.

2000 September 21 - Launch Vehicle: CZ-NGLV-320.

• Chinese Rocket Plans Nation: China. Chief Designer of Chinese rockets Long Lehao described China's three-phase future space launcher plan. Phase 1, 2001-2003: Modify existing launchers to increase their reliability and payload capacity. Phase 2, by 2005: Develop non-toxic, non-polluting launchers, and increase low-Earth-orbit launch capacity to over 20 tonnes and geosynchronous transfer orbit capacity from the current 5.5 tonnes to about 14 tonnes. Phase 3: Develop a recoverable launch vehicle with lower launch costs.References: 424.

• 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.