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CZ-NGLV-522
Part of CZ-NGLV Family
CZ-NGLV-522
CZ-NGLV-522
Credit: © Mark Wade
Chinese orbital launch vehicle. 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 metric tons to low earth orbit. Version dropped together with the 2.25 m booster module.

AKA: Chang Zheng Next Generation Launch Vehicle Type E;CZ-5-5.0;CZ-NGLV-E;Long March Next Generation Launch Vehicle Type E. Status: In development. Payload: 20,000 kg (44,000 lb). Thrust: 8,240.00 kN (1,852,420 lbf). Gross mass: 630,000 kg (1,380,000 lb). Height: 55.00 m (180.00 ft). Diameter: 5.00 m (16.40 ft). Span: 13.00 m (42.00 ft). Apogee: 200 km (120 mi).

LEO Payload: 20,000 kg (44,000 lb) to a 200 km orbit at 52.00 degrees.

Stage Data - CZ-NGLV-522

  • Stage 1. 2 x 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: Development 2004. 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 gimbaled LOX /Kerosene engines of 1200 kN vacuum thrust each. The oxygen tank is pressurized using oxygen bled from the engine and helium is used to pressurize the kerosene tank. The engines can be throttled to 65% of rated thrust. Burn time shown assumes full thrust during engine burn.
  • Stage 1. 2 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 gimbaled LOX /Kerosene engines of 1200 kN vacuum thrust. The oxygen tank is pressurized using oxygen bled from the engine and helium is used to pressurize 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 gimbaled LOX /LH2 engines of 660 kN vacuum thrust each. The hydrogen tank is pressurized using hydrogen bled from the engine and helium is used to pressurize the oxygen tank.



Family: orbital launch vehicle. Country: China. Engines: YF-120t, YF-50t. Stages: CZ-NGLV-300, CZ-NGLV-500, CZ-NGLV-200 stage. Agency: CALT.

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