The majority of the text in this file was extracted and/or modified
from:

1. Lunar Reconnaissance Orbiter Project Mission Concept of Operations,
R. Saylor, 431-OPS-000042, 2006. [SAYLOR2006A]

2. Lunar Reconnaissance Orbiter Project Mission Design Handbook, R.
Saylor, 431-HDBK-000486, 2006. [SAYLOR2006B]

3. Exploration and Science, presentation from LOLA Delta-PDR held on
October 6, 2005

4. Theory of LEND Science and Observations, presentation from LEND PDR
held on September 21-23, 2005

5. Investigation Overview, presentation from LROC PDR held on September
8, 2005.

6. The Lunar Reconnaissance Orbiter: Plans for the Extended Science Phase,
R. Vondrak et al, poster session, 43rd Lunar and Planetary Conference,
March 22, 2012.

7. Bistatic Radar Observations of the Moon Using The Arecibo Observatory &
Mini-RF Instrument on LRO, D.B.J. Bussey et al, presentation, 43rd Lunar
and Planetary Conference, March 20, 2012.

LRO was launched on June 18, 2009 on an Evolved Expendable Launch Vehicle
(EELV). The EELV inserted the orbiter into a direct trajectory to the
Moon. The orbiter used the on-board propulsion system to enter
into lunar orbit. After orbiter commissioning, the orbiter entered
the nominal mission orbit of 50 km. LRO will perform routine measurement
operations for one year. After one year, LRO may continue operations as
part of an extended mission operations phase. The duration of extended
mission is dependent on the orbit. After LRO uses all of the onboard
fuel, LRO's orbit will degrade and eventually impact the surface of the
Moon.

The orbiter carried a secondary payload, the Lunar Crater Observation
and Sensing Satellite (LCROSS), which operated as a separate mission to
observe the impact of a spent Centaur rocket released over the Moon's
south pole. (Data from the LCROSS mission are archived separately in
PDS.)

Once LRO was in the final mission orbit, the six instruments began
to collect measurement data for the mission. A technology
demonstration instrument, the Miniature-Radio Frequency (Mini-RF)
instrument, also collected data during the nominal mission. At the start
of the science mission, the status of Mini-RF was changed from
technology demonstration instrument to science instrument. Mini-RF ceased
acquiring monostatic radar data in December 2010 due to transmitter
failure and in 2011 began acquiring bistatic radar measurements.

Radio Science on LRO, while not a formal investigation, includes the
S-band communication and tracking system, the spacecraft timing system,
as well as Laser Ranging, a technology demonstration component. Data
are collected using various elements of the Mission Operations Center
and the LOLA SOC. While the primary function of the radio subsystem is
to support commanding, telemetry and tracking, the data are also
scientifically useful. Range and Doppler data from S-band tracking at
a worldwide station network aids in refining lunar gravity models as
well as positioning the spacecraft. Laser ranging data, which improve
the precision of orbit determination, in turn improve the accuracy of
topographic measurement.

A description of the LRO instruments follows:

1. Cosmic Ray Telescope for Effects of Radiation (CRaTER): Harlan Spence
leads the CRaTER measurement investigation from Boston University (BU).
The CRaTER instrument measures cosmic ray sources from two different
directions (looking nadir and zenith). The instrument telescope contains
a series of five detectors spaced apart that measure the different
cosmic rays. CRaTER measurement goals are to:

a. Measure and characterize the deep space radiation environment and
spectra of galactic and solar cosmic rays.
b. Characterize the biological impacts from the radiation environment.

CRaTER measures the Linear Energy Transfer (LET) spectra behind tissue
equivalent material. LET spectra are the missing link connecting both
Galactic Cosmic Rays (GCRs) and Solar Energetic Particles (SEP) to
potential damage to tissue. CRaTER measures low LET from 200 keV to 100
MeV and high LET from 2 MeV to 1 GeV.

The CRaTER instrument has both a nadir and zenith field of view. The
zenith field of view measures the primary sources of GCRs and SEPs. The
nadir field of view measures sources of radiation from the lunar
surface.

The instrument operates continuously during the entire orbit and
operates autonomously. CRaTER nominally generates ~0.5 kbps of data
but when solar flares are detected, the data rate can increase to ~90
kbps.

2. Diviner Lunar Radiometer Experiment (DLRE): David Paige leads the
Diviner measurement investigation from the University of California,
Los Angeles (UCLA). Diviner includes a 9-channel radiometer with a
wavelength range from 0.3 to 200 microns. DLRE makes precise
radiometric temperature measurements of the lunar surface with the
following measurement goals:

a. Map global day/night surface temperatures.
b. Characterize thermal environments for habitability.
c. Determine rock abundances at landing sites.
d. Identify potential polar ice reservoirs.
e. Search for near-surface and exposed ice deposits.

DLRE is a 9-channel radiometer that measures wavelengths from 0.3 to
200 micron. Measurements have a spatial resolution of less than 500
m at the 50 km altitude.

DLRE operates continuously during the entire orbit. During most of the
orbit, the instrument looks at nadir, but the instrument has two gimbals
which allows it to rotate about both axes. Periodically throughout the
orbit, the instrument rotates to perform two types of calibration
activities. The first is a deep space/internal black body calibration.
The instrument rotates to either deep space or the internal black body
target for approximately 32 seconds. The deep space/black body
calibration is performed approximately 12 times per orbit. The second
calibration activity is the solar calibration activity. The instrument
has a solar calibration target located just below the main instrument
drum. During each orbit, the instrument rotates so that the solar
target is illuminated by the Sun. The solar and the deep space/internal
black body calibrations are both triggered by onboard event tables. The
event tables are uplinked periodically throughout each month.

DLRE collects approximately 3.5 Gbits of data each day. Besides the
periodic uplink of new event tables, the instrument operates
autonomously throughout the orbit. There may be a possibility of
interference with LROC imaging if a DLRE calibration sequence occurs
during LROC NAC imaging. DLRE can execute a freeze command that will
prevent a calibration sequence from occurring. The freeze command is
inserted just prior to the LROC image commands as part of the spacecraft
daily command load.

3. Lyman-Alpha Mapping Project (LAMP): Alan Stern leads the LAMP
measurement investigation from Southwest Research Institute (SwRI). The
LAMP instrument includes high and low power supplies and a double delay
line detector. The LAMP instrument measurement goals are to:

a. Provide landform mapping from Lyman-alpha albedos at sub-km resolution
in and around the permanently shadowed regions of the lunar surface.
b. Identify and localize exposed water frost.
c. Demonstrate the feasibility of using starlight and sky-glow for future
surface mission applications.

LAMP measurements provide additional characteristics on landing sites as
well as aid in the search for localized exposed water ice. The LAMP
instrument's sensitivity to ultraviolet (UV) absorption near 1600
angstrom allows detection of water frost. LAMP also provides images of
permanently shadowed regions at ~500 m resolution.

The LAMP instrument is powered during the entire lunar orbit, but only
collects measurement data over the night portion of the orbit. The LAMP
instrument incorporates a Lunar Terminator Sensor (LTS) that detect the
terminator line. The LTS contains two sensor channels with each channel
offset from the LAMP boresight by +/- 1.5 degrees in a plane that
contains the spacecraft 'in-track' motion (i.e. parallel to the LAMP
entrance slit width). When the instrument is approaching the terminator
line, the instrument high voltages are reduced when passing from dark
to light to prevent the detector from saturating during the dayside
portion of the orbit. The LTS also signals the instrument when the
terminator (light to dark) is passed and the high voltages are then
increased for measurement data collection. In case of an LTS failure,
the ground generates a terminator prediction product that will be used
to trigger the high voltage operations from the daily command load.

The LAMP main door has a small hole which allows it to operate over the
sunlit portion of the orbit. In this mode, the LTS provides the
software with the signal to open and close the door. When LAMP operates
over the entire orbit, the data volume per day is doubled to
approximately 2.14 Gbits.

LAMP routinely collects approximately 1 Gbit of data per day and
operates autonomously throughout the orbit without any daily operations
input.

4. Lunar Exploration Neutron Detector (LEND): The LEND measurement
investigation is led by Igor Mitrofanov from the Russian Institute for
Space Research. The LEND instrument includes a collimated sensor and
sensors to detect thermal, epithermal, and high-energy neutrons.

LEND objectives include:

a. Creation of high-resolution hydrogen distribution maps with
sensitivity of about 100 ppm of hydrogen weight and horizontal
spatial resolution of 5 km.
b. Characterization of surface distribution and column density of
possible near-surface water ice deposits at the Moon's polar cold
traps.
c. Creation of a global model of neutron component of space radiation at
an altitude of 30-50 km above the surface with spatial resolution of
20-50 km at the spectral range from thermal energies up to 15 MeV.

LEND sensors STN1, STN2, STN3, and SETN detect thermal neutrons and
epithermal neutrons to characterize the lunar radiation environment.
Sensors STN1 and STN3 operate as a Doppler filter for thermal neutrons
from the front side and back side of the instrument. Sensors SETN and
STN2 have open fields of view. Sensor SHEN detects high energy neutrons
at 16 energy channels from 300 keV to more than 15 MeV to characterize
the lunar radiation environment. The SHEN sensor has a narrow field of
view of about 20-30 degrees. LEND collimated sensors CSETN1-4 detect
epithermal neutrons with high angular resolution to characterize
spatial variations of lunar neutron albedo, which depend on content of
hydrogen in 1-2 m of the regolith. LEND collimated sensors CSETN1-4 and
SHEN detect epithermal neutrons and high energy neutrons with high
angular resolution to test water ice deposits on the lunar surface.

LEND measurements include:

a. Measurement of thermal neutrons with flux variation greater than 1%
and altitude-dependent spatial resolution about 50km.
b. Measurement of epithermal neutrons greater than 0.4 electron Volts
(eV) with flux variation about 2% (pole) and 10% (equator).
c. Measurement of high-energy neutrons 0.3 - 15.0 Mega-electron Volts
(MeV) with flux variations 4% (pole) and 10% (equator).

LEND operates autonomously, collecting data throughout the lunar orbit.
LEND generates approximately 0.26 Gbits of measurement data per day. In
order to perform early calibration measurements, LEND became active
shortly after the first mid course correction (MCC) burn. Operationally,
LEND is simple and has only three instrument modes: MEASUREMENTS,
STAND-BY, and OFF. While in MEASUREMENTS mode, instrument electronics
and detector high voltage are both 'on' and the instrument generates
measurement and housekeeping data. In STAND-BY mode, instrument
electronics are 'on', detector high voltage is 'off', and only
housekeeping data are generated. While in OFF mode, the instrument is
'off', the instrument external heater is 'on', and only external
temperature data are generated.

5. Lunar Orbiter Laser Altimeter (LOLA): David Smith leads the LOLA
measurement investigation from GSFC. LOLA uses a 1064 nanometer (nm)
laser that expands to provide a five spot pattern on the Moon's
surface. A telescope receives the reflected light where the Electronics
processes the return.

The primary LOLA objectives are:

a. Produce a high-resolution global topographic model and global geodetic
framework that enables precise targeting, safe landing, and safe
mobility on the Moon's surface. LOLA determines the topography of the
Moon to geodetic quality from global to landing-site relevant scales.
b. Characterize the polar illumination environment at relevant temporal
scales, and image permanently shadowed regions of the Moon on landform
scales to identify possible locations of surface ice crystals in
shadowed polar craters.
c. Identify the locations of appreciable surface water ice in the
permanently shadowed regions of the Moon's polar cold traps.
d. Assess meter and smaller-scale features to facilitate safety analysis
of potential future lunar landing sites.

LOLA has two secondary objectives:

a. Establish a global geodetic reference system for the Moon.
b. Improve the model of the lunar gravity field to facilitate precision
navigation and landing.

LOLA has the following capabilities. It measures the distance between
the spacecraft and the surface which, along with the spacecraft
position, will allow precise measurements of the lunar shape. The
instrument lays down a laser spot pattern that provides altimetry
measurements along- and across-track to enable the surface slope to be
derived for safe landing. It measures the distribution of elevation
within the laser footprint for estimation of surface roughness (rock
size). LOLA also identifies regions of enhanced surface reflectance that
might indicate the presence of water ice on the surface.

LOLA achieves its measurement objectives as follows:

a. LOLA provides 5 profiles in a 70-meter swath.
b. The instrument provides full spatial sampling after one year:
i. ~ 1.2 km average spacing at equator
ii. ~ 25 m average spacing above 86 degrees north and south
c. The LOLA ground software performs cross-over analysis of LOLA data-
topography, slopes, and roughness are the same on both tracks.
d. LOLA data provide precision information about the orbiter's location-
S-band tracking data are augmented by Earth-based laser ranges.
e. LOLA data improve the lunar gravity field model via cross-over
analysis.

LOLA Mapping Data Products include the following:

a. Topography with average horizontal resolutions (after one year) of
1.2 km at equator and of 25 m at latitudes greater than 86 degrees,
with accuracies of +/-50 m in horizontal and less than 1 m in
vertical.
b. Surface slopes with average horizontal resolutions (after one year) of
50 m with accuracy of less than +/- 0.5 degrees.
c. Surface roughness with average horizontal resolutions (after one year)
of 5 m with accuracy of ~30 cm.
d. Elevations of permanently shadowed regions with average horizontal
resolutions (after one year) of 25 m with accuracy of ~10 cm.
e. Reflectance of permanently shadowed regions with average horizontal
resolutions (after one year) of 50 m with accuracy of +/- 5%.
f. Polar illumination with average horizontal resolutions (after one
year) of 50 m with accuracy of less than 1 m.
g. Landing site surveys (approximately 50).
h. Global lunar coordinate system with point-to-point distances with
accuracy of +/- 70 m.
i. Precision LRO orbits with accuracy of +/- 50 m in horizontal and +/-
1 m in vertical.
j. Improved gravity model with a goal of producing a global gravity model
that is as good as today's nearside gravity model.

6. Lunar Reconnaissance Orbiter Camera (LROC): Mark Robinson leads LROC
measurement investigation from Arizona State University (ASU). LROC
consists of two narrow angle cameras (NAC), a wide-angle camera (WAC),
and a Sequence and Compression System (SCS).

LROC measurement objectives include:

a. Landing site identification and certification, with unambiguous
identification of meter-scale hazards.
b. Unambiguous mapping of permanent shadows and sunlit regions.
c. Meter-scale mapping of polar regions with continuous illumination.
d. Overlapping observations to enable derivation of meter-scale
topography.
e. Global multispectral imaging to map ilmenite and other minerals.
f. Global morphology base map.
g. Characterize regolith properties.
h. Determine current impact hazards by re-imaging 1-2m/pixel Apollo
images.

The NAC operational concept is as follows:

a. 25 km downtrack (no summing)
b. 50 cm / pixel - 5 km cross track at 50 km
c. 10 degree (300 km) 'read-out gap' (less with smaller images)
d. Image targets at nadir with favorable lighting conditions
e. Build up complete 1 m/pixel maps from 85.5 degrees to pole (N and S)
f. Photometric and geometric stereo through repeat coverage.

The WAC operational concept is as follows:

a. Continuous pole-to-pole 50 km swath mapping in all 7 bands possible
b. Repeat BW coverage at poles every orbit 100 km swath width
c. Global 100 m/pixel (vis) / 400m/pixel (UV) at 50km and 50-75 degree
incidence angle.

LROC provides the following capabilities:

a. Landing site identification and certification
i. Unambiguous identification of 1 m hazards with 0.5 m/pixel and
MTF greater than 0.2 at Nyquist, for blocks and small craters
ii. 5 km swath with two NACs
iii. Topography.
b. Polar illumination
i. WAC repeat synoptic coverage at high time resolution (every
orbit) over full year: 80 degrees to 90 degrees to 88 degrees;
full overlap 88 degrees to 90 degrees every orbit; excellent
repeat coverage 85 degrees to 90 degrees
ii. NAC meter scale mapping of poles: summer mosaics of each pole for
morphology and permanent shadow from 85.5 degrees to the pole;
winter repeat coverage observations of highly illuminated
peaks/ridges, capable of finding smallest usable unit of
'perma-light'
c. High resolution topography
i. Stereo coverage: point cross track, limited by project
constraints and orbit progression, is easy at poles and more
difficult at equator; two NACs offset ~50 lines downtrack for
correlation and remove spacecraft pointing variation;
5 meter (or better) correlation patch
ii. Photometric stereo: three images at different lighting; 1 to
2 m/pixel (bin for SNR); directly supports landing site
certification and science analysis
d. Multispectral mapping
i. WAC uv/visible: 315, 360, 415, 560, 600, 640, 680 nm;
global visible map at 100 m/pixel; global UV map at 400 m/pixel;
map TiO2 soils (hold H, He); pyroclastic glasses (volatiles);
olivine (magmatic processes)
ii. Meshes with Clementine 100-200 m/pixel (415, 750, 900, 950, 1000)
e. Global morphology: 100 m/pixel global map with 55-75 degree incidence
angle - critical for mapping, basemap, crater counts (current best LO
50-600 m/pixel, poorest on farside); key for establishing relative age
dates (ultimately absolute); resource assessment; context imaging
f. Current impact rates
i. Re-image Apollo pan coverage at same lighting (high and low
Sun) at 1 m/pixel
ii. Rates of impacts from 0.1 m to 10 m bolides poorly known (x100
difference in current models)
iii. Should have been 950 craters >10 m/diameter formed since 1972
(crater ~10x impactor)
iv. Re-image 1 percent of Moon at 1 m/pixel should find at least 9
craters
v. Critical measurement for understanding most dangerous impact
hazards on Moon.

7. Miniature-Radio Frequency (Mini-RF): Ben Bussey of the Johns Hopkins
University Applied Physics Laboratory (JHU/APL) leads the Mini-RF
measurement investigation. JHU/APL is responsible for instrument
operations. Mini-RF is a Synthetic Aperture Radar (SAR) that consists of
a fixed planar antenna mounted on an external spacecraft surface, and a
cable harness between the electronics and the antenna. It operated on a
non-interference basis during the nominal mission. After Mini-RF ceased
acquiring monostatic radar data in December 2010, it began acquiring
bistatic radar measurements in 2011.

Mini-RF measurements include:

a. Imaging from 50km altitude surface areas that have been imaged by
Forerunner with the same dual polarization, resolution, and S-band
frequency as was used by Forerunner. The Forerunner instrument is
on the ISRO Chandrayaan-1 mission to the Moon.
b. Imaging polar areas with both S- and X-band, and at both baseline and
zoom resolutions
c. Acquiring data in a continuous transmit mode that is applicable for
topography generation using post processing techniques
d. Conducting a set of experiments to test the usability of Mini-RF
hardware as a communications asset.
e. Acquiring bistatic radar measurements from a high-power signal
transmitted from the Arecibo Observatory Planetary Radar and reflected
off the lunar surface.

Mini-RF Conops has six primary components:

a. The communications experiment consists of two 10-minute data takes,
approximately 24 hours apart, that occurred during the instrument
commissioning phase, before the nominal mission.
b. SAR Data Acquisition during nominal mission: Mini-RF acquired one
4-minute SAR data strip every month. Within this strip it is possible
to alternate between different SAR modes, e.g. S or X band, baseline
or zoom resolution. In addition, twice a year, Mini-RF acquired four
2-minute strips from four consecutive orbits.
c. Continuous Mode Data Acquisition during nominal mission: Mini-RF
acquired one 4-minute SAR data strip every month. Additionally, twice
a year, Mini-RF acquired four 2-minute strips on four consecutive
orbits.
d. Mini-RF Exploration Utilization Plan (MEUP): additional polar campaign
data acquisitions were allowed during late nominal mission and early
science mission during periods where the Beta angle is greater than
60 degrees (to mitigate impact on spacecraft solar array).
e. During the science mission, a primary goal was to acquire significant
global-scale s-band zoom data.
f. Starting in 2011, Mini-RF was used to collect the first ever planetary
bistatic radar images at non Beta=0 angles, to determine if the Moon's
polar craters contain ice. These measurements can be used for studies
of the composition and structure of pyroclastic deposits, impact
ejecta and melts, and the lunar regolith.

8. Radio Science (RS): Gregory Neumann of the Goddard Space Flight Center
(GSFC) leads the Radio Science data collection effort. Data and
Documentation are generated by the Universal Space Network, White Sands
Complex, Deep Space Network, the LRO Project, and the LOLA Science
Team. The Goddard Geophysical Astronomical Observatory provides satellite
laser ranging data and coordinates data from International Laser Ranging
Service partners in other countries.

Radio Science Data consist of primary and ancillary data; where the latter
are needed for the processing or interpretation of the former. The
specific files that are being archived by the RS team are:

a. Tracking Data
The Station Raw Tracking Data support tracking of the orbiter and
generation of orbit and mission products. Each ground station (WS1 and
the USN stations) creates data in a format identified as the Universal
Tracking Data Format (UTDF) as described in publication 453-HDBK-GN
(May 2007).
b. Weather Data
These ascii files are generated by various ground stations and record
information such as time, temperature, pressure, relative humidity and
wind speed.
c. Small Forces Files
These files include the updated parameters for thruster calibration
based on all information from past maneuvers. An assessment is made of
the maneuver execution based on pre- and post-maneuver orbit solutions
and telemetry, which is then used to determine a thrust scale factor
for future maneuvers using the same thruster set.
d. Laser Ranging Data (normal point and full rate)
These data consist of one way range measurements via laser pulse
time-of-flight from Earth to LRO, using one of LOLA's laser detectors.
This is essential to meeting the spacecraft's precision orbit
determination requirement, but also has secondary scientific value.


Mission Phases
==============

LAUNCH 2009-06-18 (2009-169)

The launch phase began with launch vehicle lift-off and lasted about 90
minutes until payload separation. The payload had achieved the
trans-lunar trajectory.

------
CRUISE 2009-06-18 to 2009-06-23 (2009-169 to 2009-174)

The early cruise phase began with payload separation and lasted about 90
minutes until observing mode began. The orbiter performed Sun
acquisition, ground acquisition, and deployments. Initial planning for
a mid-course correction (MCC) occurred during this phase.

The mid-cruise phase began with observing mode and lasted about a day
until completion of the mid-course correction (MCC). During this phase
propulsion checks were performed, final MCC planning was done, and the
MCC was executed.

The late cruise phase began with completion of the mid-course
correction (MCC) and lasted until the lunar orbit
insertion (LOI) sequence began. During this phase the CRaTER and LEND
instruments performed early activation tasks, the orbiter underwent
functional checks, and LOI planning was done.

------
LUNAR ORBIT ACQUISITION 2009-06-23 (2009-174)

The lunar orbit acquisition phase began with the start of the
lunar orbit insertion (LOI) sequence and lasted until
the commissioning orbit was attained.

------
COMMISSIONING 2009-06-23 to 2009-09-14 (2009-174 to 2009-257)

The commissioning phase began with attainment of the 30x216 km
commissioning orbit and lasted until the mission orbit was
achieved. During this phase orbiter and instrument checks and
calibrations were performed and the orbit was adjusted to the mission
orbit.

------
NOMINAL MISSION 2009-09-15 to 2010-09-15 (2009-258 to 2010-258)

The nominal mission phase began with the attainment of the
mission orbit and continued for 1 year. During this phase
routine operations, non-routine operations, and measurement data
processing were performed.

------
SCIENCE MISSION 2010-09-16 to 2012-09-15 (2010-259 to 2012-259)

The science mission began at the completion of one year of nominal
operations (officially at 15:40 UTC on September 16, 2010). It lasted 2
years. During this phase, objectives that had not been determined were
to be realized, and impact planning and prediction would be performed.
The beginning of this phase marked the transition of LRO
programmatic control from the NASA Exploration Systems Mission
Directorate (ESMD) to the NASA Science Mission Directorate (SMD).

------
EXTENDED SCIENCE MISSION 2012-09-15 to 2014-09-14 (2012-259 to 2014-257)

The extended science mission began at the completion of the two-year
Science mission (officially at 01:50 UTC on September 15, 2012). It lasted
2 years. During this phase, objectives included: understanding the
bombardment history of the Moon; interpreting lunar geologic processes;
mapping the global lunar regolith; identifying volatiles on the Moon;
and measuring the lunar atmosphere and radiation environment.

------
SECOND EXTENDED SCIENCE MISSION 2014-09-15 to 2016-09-14 (2014-258 to
2016-259)

The second extended science mission (ESM2) began at the completion of
the two-year Extended Science Mission (ESM1). The Second Extended
Science Mission began officially at 01:14:43 UTC on September 15, 2014.
It will last at least 2 years or until the orbiter impacts the lunar
surface.