Encyclopedia Astronautica
CZ-NGLV-540



cvng540.jpg
CZ-NGLV-540
Credit: © Mark Wade
Chinese orbital launch vehicle. 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 a 200 km orbit at 52.00 degrees.

Stage Data - CZ-NGLV-540

  • Stage 1. 4 x 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: Development 2004. 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 2. 1 x CZ-NGLV-500. Gross Mass: 175,000 kg (385,000 lb). Empty Mass: 17,000 kg (37,000 lb). Thrust (vac): 1,399.990 kN (314,730 lbf). Isp: 432 sec. Burn time: 480 sec. Isp(sl): 333 sec. Diameter: 5.00 m (16.40 ft). Span: 5.00 m (16.40 ft). Length: 31.00 m (101.00 ft). Propellants: Lox/LH2. No Engines: 2. Engine: YF-50t. Status: Development 2004. From top to bottom the 5-m Chinese new generation launch vehicle consists of a 117.3 cubic meter liquid oxygen tank, an intertank section, a 350.7 cubic meter liquid hydrogen tank, and an engine section with two gimballed LOX /LH2 engines of 660 kN vacuum thrust each. The hydrogen tank is pressurised using hydrogen bled from the engine and helium is used to pressurise the oxygen tank.

AKA: Long March Next Generation Launch Vehicle Type F; Chang Zheng Next Generation Launch Vehicle Type F; CZ-NGLV-F; CZ-5-5.0.
Status: In development.
Gross mass: 470,000 kg (1,030,000 lb).
Payload: 10,000 kg (22,000 lb).
Height: 55.00 m (180.00 ft).
Diameter: 5.00 m (16.40 ft).
Span: 11.00 m (36.00 ft).
Thrust: 5,840.00 kN (1,312,880 lbf).
Apogee: 200 km (120 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • YF-120t CAALPT Lox/Kerosene rocket engine. 1340.2 kN. In development. Isp=336s. For CZ-5 Next Generation Launch Vehicle series. Engine can be throttled to 65% of rated thrust. Firing tests began in 2005. More...
  • YF-50t CAALPT lox/lh2 rocket engine. 700 kN. In development. Isp=432s. New Lox/LH2 engine for next generation Chinese launch vehicles. It is an indigenous development based on Chinese experience with the YF-73 and YF-75 upper stage engines. More...

See also
  • CZ-NGLV 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. More...

Associated Manufacturers and Agencies
  • CALT Chinese manufacturer of rockets, spacecraft, and rocket engines. China Academy of Launch Vehicle Technology, Beijing, China. More...

Associated Stages
  • CZ-NGLV-200 Lox/Kerosene propellant rocket stage. Loaded/empty mass 69,000/6,000 kg. Thrust 1,340.17 kN. Vacuum specific impulse 336.3 seconds. 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. More...
  • CZ-NGLV-500 Lox/LH2 propellant rocket stage. Loaded/empty mass 175,000/17,000 kg. Thrust 1,399.99 kN. Vacuum specific impulse 432 seconds. From top to bottom the 5-m Chinese new generation launch vehicle consists of a 117.3 cubic meter liquid oxygen tank, an intertank section, a 350.7 cubic meter liquid hydrogen tank, and an engine section with two gimballed LOX /LH2 engines of 660 kN vacuum thrust each. The hydrogen tank is pressurised using hydrogen bled from the engine and helium is used to pressurise the oxygen tank. More...

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