中国的新运载火箭CZ-504.负伤英文介绍：Orbital launch vehicle. Year: 2013. Family: Long March. Country: China. Status: 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. Manufacturer: CALT.
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. LEO Payload: 25,000 kg. to: 200 km Orbit. at: 52.0 degrees. Liftoff Thrust: 1,085,000 kgf. Liftoff Thrust: 10,640.00 kN. Total Mass: 800,000 kg. Core Diameter: 5.00 m. Total Length: 55.00 m. Span: 13.00 m.
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.
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Stage Data - CZ-NGLV-504
Stage Number: 1. 4 x CZ-NGLV-300 Gross Mass: 147,000 kg. Empty Mass: 12,000 kg. Thrust (vac): 273,320 kgf. Isp: 336 sec. Burn time: 160 sec. Isp(sl): 301 sec. Diameter: 3.35 m. Span: 4.60 m. Length: 26.30 m. Propellants: Lox/Kerosene No Engines: 2. YF-120t Status: 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: 2. 1 x CZ-NGLV-500 Gross Mass: 175,000 kg. Empty Mass: 17,000 kg. Thrust (vac): 142,760 kgf. Isp: 432 sec. Burn time: 480 sec. Isp(sl): 333 sec. Diameter: 5.00 m. Span: 5.00 m. Length: 31.00 m. Propellants: Lox/LH2 No Engines: 2. YF-50t Status: Development.
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. |
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