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Chang Zheng 7
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CZ-NGLV-320/HO Credit: © Mark Wade

AKA: CZ-5-3.35;CZ-NGLV-320;CZ-NGLV-Medium. Status: Active. First Launch: 2016-06-25. Last Launch: 2017-04-20. Number: 3 . Payload: 13,500 kg (29,700 lb). Thrust: 7,200.00 kN (1,618,600 lbf). Gross mass: 594,000 kg (1,309,000 lb). Height: 53.10 m (174.20 ft). Diameter: 3.35 m (10.99 ft). Span: 10.05 m (32.97 ft).

In initial flights a modified version of the YZ-1 storable propellant upper stage was used. For geosynchronous or planetary missions a 5.0-m diameter Lox/LH2 fourth stage would be used. By late 2002 the CZ-7 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. This decision was later reversed and the CZ-2F was said to be the basis for the vehicle structure, modified for the different engines and new propellants.

Number stage 0: 2-4. LEO Payload: 13,500 kg (29,800 lb) to a 200 km x 400 km orbit at 42.00 degrees; 5,500 kg (12,100 lb) to a 700 km sun synchronous orbit. Payload: 6,000 kg (13,200 lb) to a GTO.

Stage Data - CZ-NGLV-320

• 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-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 3. 1 x 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: Development 2004. 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 4. 1 x 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: Development 2004. 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.

• DFFC - . Nation: China. Class: Technology. Type: Reentry test. Spacecraft: DFFC. COSPAR: 2016-042. Apogee: 382 km (237 mi). Perigee: 288 km (178 mi). Inclination: 40.80 deg.

  China inaugurated the Wenchang spaceport on Hainan Island on Jun 25 with the launch of the first Chang Zheng 7 rocket. The CZ-7 entered orbit with a YZ-1A upper stage, which made several burns to deploy small satellites and then was deorbited along with a subscale spacecraft reentry cabin to qualify systems for the next generation of Chinese human spaceflight missions. Four small satellites were ejected from the YZ-1A. Attached to the YZ-1A as a non-separable payload was the 'zai guijia zhu shiyan zhuangzhi', the In-Orbit Refeulling Experimental Device. The YZ-1A was deorbited over the Pacific after the experiment was completed; the stage had a design operation life of 48 hours. US tracking indicates the stage was deorbited on Jun 27 as expected. The primary payload was the DFFC (Duoyongtu Feichuan Fanhui Cang, multipurpose subscale spacecraft return capsule) flight test mission, which was to be recovered in China. There was also a ballast frame (pei zhong zhijia) which may be a dummy service module for the capsule. The capsule was deorbited on Jun 26 and landed in China at 0741 UTC. It was possible that the YZ-1A stage performed the deorbit and then separated to fire again immediately, regain orbit and continue operations for another day, but the details of what actually happened are not clear.

• Aoxiang zhixing - . Nation: China. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2016-09-29 . USAF Sat Cat: 41625 . COSPAR: 2016-042B. Apogee: 376 km (233 mi). Perigee: 289 km (179 mi). Inclination: 40.80 deg. Aoxiang Zhixing was the first 12U cubesat, with a mass of 18 kg (33 kg including payload adapter)..

• Aolong 1 - . Nation: China. Class: Technology. Type: Technology satellite. Decay Date: 2016-08-27 . USAF Sat Cat: 41629 . COSPAR: 2016-042F. Apogee: 367 km (228 mi). Perigee: 198 km (123 mi). Inclination: 40.80 deg. Ao Long 1 was an active space debris removal experiment.

• Tiange feixingqi 1 - . Nation: China. Class: Technology. Type: Technology satellite. Decay Date: 2016-08-27 . USAF Sat Cat: 41636 . COSPAR: 2016-042L. Apogee: 289 km (179 mi). Perigee: 277 km (172 mi). Inclination: 40.80 deg. Part of a pair of satellites testing data relay to each other.

• Tiange feixingqi 2 - . Nation: China. Class: Technology. Type: Technology satellite. Decay Date: 2016-08-24 . USAF Sat Cat: 41637 . COSPAR: 2016-042M. Apogee: 287 km (178 mi). Perigee: 277 km (172 mi). Inclination: 40.80 deg.

• ZGZ shiyan zhuangzhi - . Nation: China. Class: Technology. Type: Technology satellite. Decay Date: 2016-06-27 . USAF Sat Cat: 41624 . COSPAR: 2016-042A. Apogee: 381 km (236 mi). Perigee: 287 km (178 mi). Inclination: 40.80 deg.

• Silu-1 - . Nation: China. USAF Sat Cat: 42903 . COSPAR: 2017-021F. Apogee: 311 km (193 mi). Perigee: 289 km (179 mi). Inclination: 42.77 deg. Period: 90.52 min. See SilkRoad-1 01 (Silu 1). ..

• Tianzhou-1 - . Nation: China. Class: Manned. Type: Manned logistics spacecraft. Spacecraft Bus: Shenzhou. Spacecraft: Tianzhou. Decay Date: 2017-09-22 . USAF Sat Cat: 42684 . COSPAR: 2017-021A. Apogee: 369 km (229 mi). Perigee: 311 km (193 mi). Inclination: 42.80 deg. Period: 92.36 min.

  See Tianzhou 1 (TZ 1). China's first space station cargo resupply ship. Tianzhou-1 had a mass of 12910 kg. It flew on the second Chang Zheng 7 rocket, launched from Wenchang space centre on Hainan island. Tianzhou-1 docked with the Tiangong-2 space lab, then unoccupied. This mission was mainly for technology development; the Tianzhou frieghters were to be used operationally to resupply China's future large space station. Tianzhou 1 was inserted into a 198 x 372 km x 42.8 deg initial orbit, which was then raised to 311 x 369 km. The second stage ejected the usual four motor separation covers into 200 x 550 km orbits.