Editing Clementine (spacecraft) (section)

== Spacecraft design ==
{{Unreferenced section|date=September 2023}}
[[File:Clementine v01.stl|thumb|3D model of Clementine]]
The spacecraft was an octagonal [[Prism (geometry)|prism]] 1.88 m high and 1.14 m across<ref>{{cite web|title= The Clementine Satellite
 |url=https://www.llnl.gov/sites/www/files/2020-05/clementine-etr-jun-94.pdf|publisher=Lawrence Livermore National Lab|access-date=February 23, 2025}}</ref> with two [[Photovoltaics|solar panels]] protruding on opposite sides parallel to the axis of the prism. A {{convert|42|in|mm|adj=mid|-diameter}} high-gain fixed dish antenna was at one end of the prism, and the 489 N thruster at the other end. The sensor openings were all located together on one of the eight panels, 90 degrees from the solar panels, and protected by a single sensor cover.

The [[spacecraft propulsion]] system consisted of a [[monopropellant]] [[hydrazine]] system for [[Spacecraft attitude control|attitude control]] and a [[bipropellant]] [[Dinitrogen tetroxide|nitrogen tetroxide]] and [[Monomethylhydrazine|mono-methyl hydrazine]] system for the maneuvers in space. The bipropellant system had a total [[Delta-v]] capability of about 1,900&nbsp;m/s with about 550&nbsp;m/s required for lunar insertion and 540&nbsp;m/s for lunar departure.

Attitude control was achieved with 12 small attitude control jets, two star trackers, and two inertial measurement units. The spacecraft was three-axis stabilized in lunar orbit via [[reaction wheel]]s with a precision of 0.05 deg in control and 0.03 deg in knowledge. Power was provided by [[gimbal]]ed, single axis, GaAs/Ge solar panels which charged a 15 A·h, 47 W·h/kg Nihau ([[Nickel–hydrogen battery|Ni-H]]) common pressure vessel battery.

Spacecraft data processing was performed using a [[MIL-STD-1750A]] computer (1.7 MIPS) for safe mode, attitude control, and housekeeping operations, a [[Reduced instruction set computer|RISC]] 32-bit processor (18 MIPS) for image processing and autonomous operations, and an image compression system provided by the French Space Agency [[CNES]]. A data handling unit sequenced the cameras, operated the image compression system, and directed the data flow. Data was stored in a 2 Gbit dynamic solid state data recorder.