Editing NEAR Shoemaker (section)

===Spacecraft===
[[File:NEARCraft.jpg|thumb|''NEAR'' spacecraft inside its [[Delta II]] rocket.]]
The spacecraft has the shape of an octagonal prism, approximately 1.7 m on a side, with four fixed [[gallium arsenide]] [[Photovoltaic module|solar panel]]s in a windmill arrangement, a fixed 1.5 m [[X band|X-band]] high-gain radio antenna with a [[magnetometer]] mounted on the antenna feed, and an X-ray solar monitor on one end (the forward deck), with the other instruments fixed on the opposite end (the aft deck). Most electronics were mounted on the inside of the decks. The propulsion module was contained in the interior. The decision to mount instruments on the body of the spacecraft rather than using booms resulted in the gamma-ray spectrometer needing to be shielded from noise generated by the craft.<ref name=Trombka /> A [[bismuth germanate]] shield was used, although this proved only moderately effective.<ref name=Trombka />

The craft was three-axis stabilized and used a single [[bipropellant rocket|bipropellant]] ([[hydrazine]] / [[nitrogen tetroxide]]) 450 [[newton (unit)|newton]] (N) main thruster,<ref>{{Cite web |url=https://nssdc.gsfc.nasa.gov/planetary/mission/near/near_traj.html |title=NEAR Mission Profile |last=Williams |first=David R. |date=February 8, 2000 |website=NASA Goddard Space Flight Center |access-date=February 5, 2019 }}</ref> and four 21&nbsp;N and seven 3.5&nbsp;N hydrazine thrusters for propulsion, for a total [[delta-V]] potential of 1450&nbsp;m/s. Attitude control was achieved using the hydrazine thrusters and four reaction wheels. The propulsion system carried 209&nbsp;kg of hydrazine and 109&nbsp;kg of NTO oxidizer in two oxidizer and three fuel tanks.<ref name="NSSDC">{{Cite web |url=https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1996-008A |title=NEAR Shoemaker |website=NASA Space Science Data Coordinated Archive |access-date=February 5, 2019}}</ref>

Power was provided by four 1.8 by 1.2&nbsp;meter [[gallium arsenide]] solar panels, which could produce 400&nbsp;[[watt]]s at 2.2&nbsp;[[Astronomical unit|AU]] (329,000,000&nbsp;km), ''NEAR''{{'s}} maximum distance from the Sun and 1800 watts at one AU (150,000,000&nbsp;km). Power was stored in a nine-ampere-hour, 22-cell rechargeable super [[nickel-cadmium]] battery.<ref name="NSSDC"/>

Spacecraft guidance was achieved through the use of a sensor suite of five digital solar attitude detectors, an inertial measurement unit (IMU), and a star tracker camera pointed opposite the instrument pointing direction. The IMU contained hemispherical resonators [[gyroscope]]s and accelerometers. Four [[reaction wheel]]s (arranged so that any three can provide complete three-axis control) were used for normal attitude control. The thrusters were used to dump [[angular momentum]] from the reaction wheels, as well as for rapid slew and propulsive maneuvers. Attitude control was to 0.1 degree, line-of-sight pointing stability is within 50 microradians over one second, and post-processing attitude knowledge is to 50 microradians.<ref name="NSSDC"/>

The command and data handling subsystem was composed of two redundant command and telemetry processors and solid state recorders, a power switching unit, and an interface to two redundant [[MIL-STD-1553|1553 standard data buses]] for communications with other subsystems.
''NEAR'' was the first APL spacecraft to use significant numbers of plastic encapsulated microcircuits (PEMs), and the first to use solid-state data recorders for mass storage—previous APL spacecraft used magnetic tape recorders or magnetic cores.<ref>
Ronald K. Burek.
[http://citeseerx.ist.psu.edu/viewdoc/download?doi=10.1.1.132.2475&rep=rep1&type=pdf "The ''NEAR'' Solid-State Data Recorders"].
Johns Hopkins APL Technical Digest.
1998
</ref>

The solid-state recorders are constructed from 16 Mbit [[International Business Machines|IBM]] Luna-C [[DRAM]]s. One recorder has 1.1 [[gigabit]]s of storage, and the other has 0.67 gigabits.<ref name="NSSDC"/>

The ''NEAR'' mission was the first launch of NASA's [[Discovery Program]], a series of small-scale spacecraft designed to proceed from development to flight in under three years for a cost of less than $150 million. The construction, launch, and 30-day cost for this mission is estimated at $122 million. The final total mission cost was $224 million, which consisted of $124.9 million for spacecraft development, $44.6 million for launch support and tracking, and $54.6 million for mission operations and data analysis.<ref name=FAQ>{{Cite web | title = NEAR: FAQ | publisher = [[Applied Physics Lab]] | url = http://near.jhuapl.edu/intro/faq.html}}</ref>