Editing Shenzhou (spacecraft) (section)

=== Orbital module ===
[[File:Shenzhou5-2.JPG|thumb|Shenzhou 5's reentry module]]The [[orbital module]] ({{lang-zh|c=轨道舱)|p=Guǐdào cāng
}}) contains space for experiments, crew-serviced or crew-operated equipment, and in-orbit habitation. Without [[Space rendezvous|docking]] systems, Shenzhou 1–6 carried different kinds of payload on the top of their orbital modules for scientific experiments.

The [[Chinese Docking Mechanism|Chinese spacecraft docking mechanism]] (beginning with Shenzhou 8) is based on the [[Androgynous Peripheral Attach System]] (APAS).<ref name="her">{{cite web|url=https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20110010964.pdf |website=NTRS |title=ISS Interface Mechanisms and their Heritage|author1=John Cook|author2=Valery Aksamentov|author3=Thomas Hoffman|author4=Wes Bruner|date=1 January 2011|publisher=Boeing|access-date=31 March 2015|location=Houston, Texas |url-status=live |archive-url=https://web.archive.org/web/20150429130021/https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20110010964.pdf |archive-date= Apr 29, 2015 }}</ref>

Up until Shenzhou 8, the orbital module of the Shenzhou was equipped with its own [[Spacecraft propulsion|propulsion]], [[Solar panels on spacecraft|solar power]], and [[Spacecraft attitude control|control]] [[Robotic spacecraft|systems]], allowing autonomous flight. It is possible for Shenzhou to leave an orbital module in orbit for redocking with a later spacecraft, a capability which Soyuz does not possess, since the only hatch between the orbital and reentry modules is a part of the reentry module, and orbital module is depressurized after separation. For future missions, the orbital module(s) could also be left behind on the planned Chinese [[project 921/2]] [[space station]] as additional station modules.

In the uncrewed test flights launched, the orbital module of each Shenzhou was left functioning on orbit for several days after the reentry modules return, and the [[Shenzhou 5]] orbital module continued to operate for six months after launch.
{| class="wikitable"
|+Orbital Module
!Design life
|200 days
|-
!Length
|{{cvt|2.8|m|ftin}}
|-
!Diameter
|{{cvt|2.25|m|ftin}}
|-
!Span
|{{cvt|10.4|m|ftin}}
|-
!Habitable volume
|{{cvt|8|m3}}
|-
!Mass
|{{cvt|1500|kg}}
|-
!RCS (coarse)
|16 × {{cvt|5|N}}
|-
!RCS propellant
|[[Hydrazine]]
|-
!Electrical system
|Solar panels, {{cvt|12.24|m2}}
|-
!Power
|0.50 kW (avg.)
|}