CZ NGLV Credit - (c) Mark Wade

China's family of new generation expendable launch vehicles began development in 2000. 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.

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. These modular stages were 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.

CZ-NGLV-320.

CZ-NGLV-320/HO Credit - © Mark Wade

Status: In development. Popular Name: CZ-NGLV-Medium. Alternate Designation: CZ-5-3.35.

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.

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).

CZ-NGLV-504.

CZ-NGLV-504 Credit - © Mark Wade

Status: In development. Other Designations: Long March Next Generation Launch Vehicle Type D. Manufacturer's Designation: Chang Zheng Next Generation Launch Vehicle Type D. Popular Name: CZ-NGLV-D. Alternate Designation: CZ-5-5.0.

The 504 configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m diameter core stage with four 3.35 m diameter stages as strap-ons. Payload was given as 25 tonnes to low earth orbit. A standard large 5.2 m diameter fairing tops the vehicle. It would be used to launch the Chinese Space Laboratory in 2010.

CZ-NGLV-504/HO.

CZ-NGLV-504/HO Credit - © Mark Wade

Status: In development. Other Designations: Long March Next Generation Launch Vehicle Type B. Manufacturer's Designation: Chang Zheng Next Generation Launch Vehicle Type B. Popular Name: CZ-NGLV-B. Alternate Designation: CZ-5-5.0.

The 504/HO configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m core stage, topped by the 5.0 m upper stage, together with 4 x 3.35 m strap-on stages. First flight of this version was expected after 2010. Payload was given as 14 tonnes to geosynchronous transfer orbit.

Payload: 14,000 kg (30,000 lb). to a: geosynchronous transfer orbital trajectory. Liftoff Thrust: 10,640.000 kN (2,391,960 lbf). Total Mass: 810,000 kg (1,780,000 lb). Core Diameter: 5.00 m (16.40 ft). Total Length: 62.00 m (203.00 ft). Span: 13.00 m (42.00 ft).

CZ-NGLV-522.

CZ-NGLV-522 Credit - © Mark Wade

Status: In development. Other Designations: Long March Next Generation Launch Vehicle Type E. Manufacturer's Designation: Chang Zheng Next Generation Launch Vehicle Type E. Popular Name: CZ-NGLV-E. Alternate Designation: CZ-5-5.0.

The 522 configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m diameter core stage with 2 x 2.25 m plus 2 x 3.35 m strap-on stages. Payload is estimated as 18-20 tonnes to low earth orbit.

LEO Payload: 20,000 kg (44,000 lb). to: 200 km Orbit. at: 52.00 degrees. Liftoff Thrust: 8,240.000 kN (1,852,420 lbf). Total Mass: 630,000 kg (1,380,000 lb). Core Diameter: 5.00 m (16.40 ft). Total Length: 55.00 m (180.00 ft). Span: 13.00 m (42.00 ft).

CZ-NGLV-522/HO.

CZ-NGLV-522/HO Credit - © Mark Wade

Status: In development. Other Designations: Long March Next Generation Launch Vehicle Type A. Manufacturer's Designation: Chang Zheng Next Generation Launch Vehicle Type A. Popular Name: CZ-NGLV-A. Alternate Designation: CZ-5-5.0.

The 522/HO was the 'all up' baseline configuration for the Long March New Generation Launch Vehicle series. It would use the 5.0 m core stage, topped by the 5.0 m upper stage, together with 2 x 2.25 m plus 2 x 3.35 m strap-on stages. It was announced in 2003 that it would be first to fly, with a launch before the Beijing Olympics in 2008. It would be used for launch of large communications satellites. Payload is estimated as 10-12 tonnes to geosynchronous transfer orbit.

Payload: 11,000 kg (24,000 lb). to a: geosynchronous transfer orbital trajectory. Liftoff Thrust: 8,240.000 kN (1,852,420 lbf). Total Mass: 630,000 kg (1,380,000 lb). Core Diameter: 5.00 m (16.40 ft). Total Length: 58.00 m (190.00 ft). Span: 13.00 m (42.00 ft).

CZ-NGLV-540.

CZ-NGLV-540 Credit - © Mark Wade

Status: In development. Other Designations: Long March Next Generation Launch Vehicle Type F. Manufacturer's Designation: Chang Zheng Next Generation Launch Vehicle Type F. Popular Name: CZ-NGLV-F. Alternate Designation: CZ-5-5.0.

The 540 configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m diameter core stage with four 2.25 m diameter stages as strap-ons. Payload was given as 10 tonnes to low earth orbit. A standard short 5.2 m diameter fairing tops the vehicle.

LEO Payload: 10,000 kg (22,000 lb). to: 200 km Orbit. at: 52.00 degrees. Liftoff Thrust: 5,840.000 kN (1,312,880 lbf). Total Mass: 470,000 kg (1,030,000 lb). Core Diameter: 5.00 m (16.40 ft). Total Length: 55.00 m (180.00 ft). Span: 11.00 m (36.00 ft).

CZ-NGLV-540/HO.

CZ-NGLV-540/HO Credit - © Mark Wade

Status: In development. Other Designations: Long March Next Generation Launch Vehicle Type C. Manufacturer's Designation: Chang Zheng Next Generation Launch Vehicle Type C. Popular Name: CZ-NGLV-C. Alternate Designation: CZ-5-5.0.

The 540/HO configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m core stage, topped by the 5.0 m upper stage, together with 4 x 2.25 m strap-on stages. First flight of this version was expected after 2010. Payload was given as 6 tonnes to geosynchronous transfer orbit.

Payload: 6,000 kg (13,200 lb). to a: geosynchronous transfer orbital trajectory. Liftoff Thrust: 5,840.000 kN (1,312,880 lbf). Total Mass: 490,000 kg (1,080,000 lb). Core Diameter: 5.00 m (16.40 ft). Total Length: 53.00 m (173.00 ft). Span: 11.00 m (36.00 ft).