Tiangong 2 (TG-2)

Spacecraft nº:

Chinese spacecraft nº: 307

Launch & orbit data: Designation  41765 / 16057A Launch date - time  15 Sep 2016 - 14:04:12 UTC Launch site  Jiuquan, SLS-1 Launch vehicle  CZ-2F (T2) Application  Space station, laboratory LEO Earth orbit    - Perigee / Apogee  380 x 400 km    - Eccentricity      - Inclination  42.77°    - Period   min De-orbite date - time  21 July 2019 - UT Reenter location  South Pacific Ocean Flight Duration (d:hr:min)   Nbr orbits

Tiangong-2 in assembly hall.

Spacecraft data: Prime manufactor  CAST/CASC Programme  Project 921-II Operator  China Manned Space Agency (CMSA) Beijing Aerospace Flight Control Center Mass at launch  8506 kg Dry Mass   kg Basic shape  Cylinder Dimension (m)  10.4 metre long, 3.35 wide Pressurised volume  14 m³ Equipment   Solar array  2 deployable solar arrays - span: 18.4 m Stabilization   Propulsion  N2O4/MMH DC power   Decay date:  19 July 2019 (.55)

Tiangong 2 Experiment Compartment and transition section.

Description:

• Five years after the launch of the first Space Laboratory module Tiangong 1, the China Manned Space Programme (CMSP, Project 921) was ready to launch a second module. Two identical modules were originally built for the Tiangong 1 mission. After the successful launch of Tiangong 1, its backup was modified into an improved module added with upgraded systems and new capabilities, most notably the ability to be resupplied and refuelled by a Tianzhou cargo vehicle.
• To ensure the ‘new’ space module was still qualified for orbital flight after spending five years inside the spacecraft hangar at CAST, engineers had to carefully assess the conditions of nearly 300 components and parts on the module, either putting them through a life-extension process or replacing those that no longer met the requirements.
• Unlike its predecessor Tiangong 1, which was mainly intended as a target vehicle for perfecting orbital rendezvous docking, Tiangong 2’s main objective was to “verify key technologies including cargo transportation, on-orbit propellant resupply, and medium-term stay of astronauts”, as well as “conducting space science and application experiments on a relatively large scale”, according to the programme′s official statement.
  
  Spacecraft Design:
  
• The Tiangong 2 module is almost identical to its predecessor in size and appearance, consisting of two cylinder-shaped sections: a habitable Experiment Compartment serving as the main living quarters and laboratory for the crew; and an inhabitable Service Compartment that houses propulsion, power, life support, and communications systems. A pair of solar wings each with 4 solar panels are attached to the Service Compartment. The space module is 10.4 m in length and 3.35 m in diameter, with an orbital mass of 8.6 t.
  • The front Experiment Compartment is 5 m in length and 3.35 m in diameter, with a habitable internal volume of 14.4 cubic metres (2.0 x 1.8 x 4.0 m). The front end of the compartment, which provides a small free space for the crew to live and conduct experiment, is surrounded by heat pipes designed to conduct heat from internal systems to an external radiator. Inside the compartment is an instrument panel for flight controls and communications, a foldable table for eating and conducting experiments, and two sleep stations. There is a window on either side of the compartment allowing observation of outside. The remaining part of the compartment is packed with equipment and experiments.
  • The module is connected to the visiting Shenzhou and Tianzhou spacecraft via an androgynous docking mechanism developed by Shanghai Academy of Spaceflight Technology (SAST). The system is believed to have derived from the Russian APAS-75, consisting of a docking port, radio beacons, transponders, communication antenna, UHF radar, laser rangefinder, and electro-optical tracking system. Visiting astronauts enter the Experimental Compartment via the hatch on the 0.8 m-diameter docking port. The docking port on Tiangong 2 has been modified in order to support in-orbit refuelling/resupply operations.
  • Behind the experiment compartment is a 1.1 m-long transition section, tapered from 3.35 m diameter of the experiment compartment to the 2.25 m diameter of the aft service compartment. The section houses the nitrogen and oxygen tanks used for environmental control, and the water tank. The gases are stored in steel alloy spheres at a pressure of 21 Mpa.
  • The aft Service Compartmen is about 3.3 m in length and 2.5 m in diameter, and has been derived from the Shenzhou service module. The Space Laboratory is fitted with a different propulsion system to that of Shenzhou, with a 490-N dual-chamber high-expansion-ration main engine, four sets of two small aft-firing engines at the base to provide vernier thrust for fine manoeuvres, four sets of two small engines mounted around the external base of the module for pitch/yaw control, and four roll control thrusters. The unified propulsion system feeds both attitude control and main engines from four 230-litre propellant tanks loaded with up to 1,000 kg of N2O4/MMH propellants. The engines are pressure-fed using six 20-litre titanium cold gas tanks pressurised to 23 Mpa. This gas is used to force propellant at 2 Mpa using diaphragms within the propellant tanks.
  • Two four-panel solar wings, with a total span of about 23 m, deploy from the sides of the Service Compartment. These can be rotated to obtain maximum solar insolation regardless of spacecraft attitude. Each wing, about 3.1 m x 10 m, provides about double the electrical power of the Shenzhou system (total about 7 kW peak, 2.5 kW average). The back surface filled silicon solar cells of the arrays have an efficiency of 14.8% on Shenzhou. Sun sensors between the panels measure the sunlight incidence angle which allows the panels to be automatically commanded to an optimum angle. Silver-zinc batteries in the service module provide emergency power in case of failure of the solar arrays. The spacecraft′s power bus operates at 28 V.
  • The module is fitted with a robotic arm, developed by China Aacademy of Space Technology. The 10-m long robotic arm is designed to help the assembly and maintenance of the space station, move equipment and supplies around the station, and support astronauts in EVA.
• The Banxing 2 micro satellite, designed by Shanghai Academy of Spaceflight Technology (SAST), will be launched on the piggyback of Tiangong 2 and then released in orbit to demonstrate relevant technologies. Just like its predecessor Banxing 1 launched by the Shenzhou 7 mission in 2008, Banxing 2 will probably also carry an onboard camera to capture images of the mothership in orbit.
• Tiangong 2 carries a total of 14 mission and experiment packages, including:
  • The world′s first-ever in-space cold atomic fountain clock;
  • Space-Earth quantum key distribution and laser communications experiment;
  • A Gamma ray detector;
  • Liquid bridge thermocapillary convection experiment;
  • Space material experiment;
  • Space plant growth experiment;
  • Multi-angle wide-spectral imager;
  • Multi-spectral limb imaging spectrometer;
  • Stereoscopic microwave altimeter;
• If all goes smoothly, Tiangong-2 will be visited by China’s first refuelling and cargo vessel, Tianzhou-1 in the first half of 2017, launched on a Long March 7 rocket from the new Wenchang spaceport.

Tiangong-2 in June 2016 (CCTV/Framegrab).

Tiangong-2 main engine.

Mission details:

• The launch campaign began with the arrival of the Tiangong 2 module at the launch centre on 9 July 2016, after a two-day train journey from its fabrication facility at the Beijing Space City. Upon its approval, the Tiangong 2 module was examined and assembled inside the Spacecraft Non-Hazard Operation Building, before being moved to the Spacecraft Hazard Operation Building for the irreversible process of fuelling with liquid propellants and loading of pressurised gases. The completed spacecraft inside its payload fairing was rolled to the Launch Vehicle Vertical Processing Building, where the CZ-2F launch vehicle was assembled. The spacecraft inside the payload fairing was then hoisted onto the top of the launch vehicle for payload integration.
• On 9 September 2016, the CZ-2F/Tiangong 2 launch vehicle stack sitting vertically atop the Mobile Launcher Platform (MLP) was rolled out to Pad 921 situated 1.5 km away from the processing building. Once the launch vehicle stack arrived at the pad, the rotating platforms of the umbilical tower were swung to ‘embrace’ the vehicle to allow the final checkout procedure to be conducted. After the mission managers gave a Go to the launch, fuelling of the CZ-2F launch vehicle with liquid propellants began in the morning of 14 September.
• The CZ-2F (T2) launch vehicle, which lifted off from Jiuquan at 22:04 CST (14:04:12.428 UTC) on 15 September 2016, inserted the Tiangong 2 module into an initial 350 x 200 km parking orbit with an inclination of 42°. The next day, the space module used its own propulsions to make two orbit elevation manoeuvres, moving onto a 380 km near-circular orbit. Over the next few weeks, the ground mission control carried out various checks remotely to ensure that the space module is readied for the docking operation.
• Tiangong-2 spacelab was used for a single human expedition in 2016 (Shenzhou 11); China has announced that no further visits were planned. Since Shenzhou 11 left in Nov 2016, TG-2 has made small reboost manuevers on 2017 Mar 5, Apr 5-6, May 13, Jun 17-20, Sep 17, and Nov 4. The Tianzhou-1 freighter docked with it several times between Apr and Sep 2017 and transferred an unknown amount of propellant. The freighter carried about 2000 kg of propellant in eight 250 kg tanks, half of which were for its own maneuevers. Each of the three propellant transfer exercises were carried out involved one tank′s worth.
• On 2018 Jun 13 at around 0645 and 0735 UTC the lab made a two-impulse manuever to lower its orbit from 388 x 391 km to 293 x 299 km. It seemed as if this might be a precursor to a deorbit burn, but on Jun 22 at about 0117 and 0202 UTC a second two-impulse manuever restored the orbit to 390 x 399 km. The full sequence used about 330 kg of propellant.
  If we assumed Tianzhou left the 1000-kg-capacity tanks full, that leaves about 670 kg. Total mass of Tiangong-2 including propellant is probably now around 8500 kg. At least 250 kg of propellant is required to safely deorbit the vehicle at end of mission.
• As of Jul 26, 2018 Tiangong-2 remained in a 386 x 395 km orbit.
• Tiangong 2 carried out major orbit-lowering manoeuvre on July 18(.59) and a de-orbit burn on July 19(.52), 2019.

An orbital view of the Tiangong 2 (right) and Shenzhou 11 (left) complex, captured by the BX-2 CubeSat.

Tiangong-2 description with modules.

Tianzhou 1 (left) docked to Tiangong 2.

Tiangong-2 Station after its completion in November, 2022.

External links:

• Wikipedia: Space station description

Astrophilately covers:

"Flight cover" with MPO and "27" in cancel, and film strip.

Same cover with MPO and "27" in cancel, without film strip.

Launch cancel without MPO and "27". Credit: #411a