# Regionalized Lunar South Pole Surface Navigation  System Analysis

Authors: Bryan W. Welch
Journal: International Journal of Navigation and Observation
 (2008)

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## Abstract

Apollo missions utilized Earth-based assets for navigation, since the landings took place at lunar locations in constant view from the Earth. The new exploration campaign to the lunar South Pole region will have limited Earth visibility, but the extent to which a navigation system comprised solely of Earth-based tracking stations will provide adequate navigation solutions in this region is unknown. This article presents a dilution-of-precision-(DoP-) based stationary surface navigation analysis of the performance of multiple lunar satellite constellations, Earth-based deep space network assets, and combinations thereof. Results show that kinematic and integrated solutions cannot be provided by the Earth-based deep space network stations. Also, the surface stationary navigation system needs to be operated as a two-way navigation system, or as a one-way navigation system with local terrain information, while integrating the position solution over a short duration of time with navigation signals being provided by a lunar satellite constellation.


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## Body

## 1. Introduction

In support of NASA's vision for space exploration [1], an extension of the position-fixing
capability provided by the GPS constellation [2] to the Moon is being analyzed.
This extension would be provided by a lunar network of spacecraft orbiting the
Moon, Earth-based deep space network assets, and combinations thereof. This
study provides a dilution-of-precision-(DoP-) based stationary surface
navigation analysis via radiometric navigation signals from the aforementioned
systems for users located on the lunar surface. The current study is similar to
prior studies on the subject [3–6] with several differences including
use of the newly developed DoP technique referred to as “generalized DoP,” combination
of radiometric signals from the lunar vicinity and Earth vicinity, and
limitations to the regionalization of interest.Generalized DoP
provides the ability to assess the navigational performance associated with a
receiver that is able to integrate radiometric measurements over time. Such an
analysis method allows one to directly compare the navigational capability
associated with sparse constellations with that provided by constellations
which support full coverage of an appropriate fold. Estimates of a user state
derived from multiple radiometric measurements collected over a period of time
are herein referred to as being “dynamic,” whereas those provided by full
constellations that do not employ integration over time in the receiver are
referred to as being “kinematic.” As
opposed to standard measures of DoP that are restricted to kinematic
position-fixing capabilities, the use of generalized DoP further allows
assessment of the constellation to be performed in terms of the latency
associated with obtaining a specified level of system performance [5, 6].Several different options for the radiometric navigation signal sources are considered in this
study and include equally the Earth-based deep space network (DSN) site
locations, two inclined elliptical lunar constellations [7], and combinations
thereof. Included in this study are assessments of a number of augmentations to
the system, such as two-way mode of operation, good knowledge of the terrain,
and the integration of radiometric measurements over periods of time. Comparisons
of the system performance under the different system assumptions indicate that
system availability performance is significantly improved and latency is
reduced by the prescribed augmentations. Results are derived from temporally
and spatially averaged system availability numbers associated with prespecified
threshold levels of system availability.


## 2. Signal Sources

Three categories of radiometric signal sources are considered two
inclined elliptical lunar-centric constellations, DSN site locations (Canberra, Madrid, and Goldstone),
and the combination of the lunar constellations and DSN assets.
The notation for the lunar-centric constellations subsequently used, such as EllipN/p/f/d
km, is
defined as N the number of satellites, p the number of orbital planes, f the
binary answer as to if phasing exists in the mean anomaly between satellites in
adjacent planes, and d denotes the semi-major axis (SMA) in kilometers. Table 1
lists the parameters of the two lunar-centric constellations [7] that are
considered here. Table 2 lists the latitude and longitude for the three DSN
site locations.Table 1
Lunar network constellations.
ConstellationSatellites no.Planes no.SMA (km)InclinationEccentricityPhasing no.Ellip 1/1/0 a654111654162.9°0.60Ellip 2/1/0 a654121654162.9°0.60Table 2
DSN site locations.
DSN siteLatitude (°N)Longitude (°E)Canberra−35.4148.967Madrid40.383−4.25Goldstone35.33−116.833Each of the sources in this study was considered for specific reasons. The two inclined elliptical
constellations were considered for their providing a focus of coverage over the
lunar South Pole region. The Earth-based
DSN assets were considered because of their usefulness and availability for
space navigation. The combinations of the two sets were examined to determine
additional benefits of combining the services of both assets over their
individual performance. Figure1 shows an illustration of the Ellip 2/1/0 a6541
constellation in orbit around the Moon. Shown in the background of the
illustration are the three Earth-based DSN stations. The image was produced
from orbital plots in Satellite Orbit Analysis Program.Figure 1
Elliptical 2/1/0 a6541 constellation.


## 3. Analysis

### 3.1. Generalized DoP

The analysis performed is a
generalized version of the DoP metric [4–6] of which several forms are
subsequently used for analysis. The generalized DoP is derived from the
observability grammian, which is obtained by using the navigation user
equations of motion and the associated sequence of measurements. The equations of motion and the measurement
sequence are given by [4–6]. It is shown that the DoP metric takes the
following form, derived in [4–6]. Since the DoP metric is calculated for a
stationary user, the state transition matrix is an identity matrix and the
measurement partial derivation matrix is utilized directly in (1)(1)max(eig((∑t0tnHtiTWHti)−1)). The variables listed in (1) are as
follows:(i)
eig(·)
is the Matlab function that calculates the eigenvalues of the input matrix;(ii)
t0 is
time step zero;(iii)
tn is the nth time step since time step zero;(iv)
Hti is the partial derivative measurement matrix at the ith
time step;(v)
W is the measurement weighting matrix.


### 3.2. Variations of Generalized DoP

In order to relax the constraint of
satellite coverage to invert the observability grammian, a number of
augmentations to the lunar navigation system are considered in the analysis, as
in previous analyses [7]. These
augmentations constrain the navigation solution and thereby reduce the number
of required satellites in view. These augmentations include clock
synchronization and good knowledge of the terrain, and create four forms of
DoP. The selected form of DoP used not only affects the required satellites in
view, but also the state transition and H matrices used in the calculation. It
should also be noted that throughout the analysis, both range and range-rate
(Doppler) measurements are used to solve for position and time bias (when
appropriate) estimates only. There are no estimates done for velocity or
frequency bias, as the users are assumed to be stationary.The first form of DoP is the
geometric dilution of precision (GDoP). It is used in the global positioning
system (GPS), where the solution is obtained for position of the user in three
dimensions and the time bias, resulting in the requirement of four navigation
signals. Since two navigation signals are available from each satellite, then
only two satellites are necessary in view to kinematically solve for the user’s
position. Without two satellites in
view, the solution will need to be integrated over time in order to be able to
invert the solution and solve for the user’s position and time bias. The GDoP
metric is used to evaluate a navigation system operating in one-way mode
without terrain information. Equation (2) provides the associated H matrix for
the GDoP metric(2)H=[∂pr1∂x1∂pr1∂y1∂pr1∂z1∂pr1∂(ctbias1)||||∂prm∂xm∂prm∂ym∂prm∂zm∂prm∂(ctbiasm)∂r•1∂x1∂r•1∂y1∂r•1∂z1∂r•1∂(ctbias1)||||∂r•m∂xm∂r•m∂ym∂r•m∂zm∂r•m∂(ctbiasm)]. The variables listed in (2) are as
follows:(i)
H is the partial derivative measurement matrix;(ii)
(xm,ym,zm) is the position of the surface user;(iii)
prm is the mth pseudorange measurement;(iv)
tbiasm is the clock bias of the surface user;(v)
r˙m is the mth range rate measurement;(vi)
c is the speed of light in a vacuum;(vii)
∂ is the partial derivative operator. The second form of DoP is the positional
dilution of precision (PDoP). It provides an estimate of user positioning
accuracy for the case in which there is no time bias between orbiter clocks and
user clocks, such as the case in a two-way mode of operation. PDoP results in
the requirement of three navigation signals. Thus, the PDoP metric also
requires two satellites in view to kinematically solve for the user’s position.
The PDoP metric is used to evaluate a navigation system operating in two-way
mode without terrain information. Equation (3) provides the associated H matrix
for the PDoP metric(3)H=[∂r1∂x1∂r1∂y1∂r1∂z1|||∂rm∂xm∂rm∂ym∂rm∂zm∂r•1∂x1∂r•1∂y1∂r•1∂z1|||∂r•m∂xm∂r•m∂ym∂r•m∂zm]. The new variable listed in (3) is as
follows:(i)
rm is the mth pseudorange measurement.The third form of DoP is the horizontal/time
dilution of precision (HTDoP). This form of DoP is applied when a user has
knowledge of their altitude above the center of the Moon, but still has a time
bias from the source of the navigation signal. This also results in the
requirement of three navigation signals, meaning that two satellites must be in
view to kinematically solve for the user's topocentric North and East
components along with the time bias. The HTDoP metric is used to evaluate a
navigation system operating in one-way mode with terrain information. Equation (4)
provides the associated H matrix for the HTDoP metric(4)H=[∂pr1∂x1∂pr1∂y1∂pr1∂(ctbias1)|||∂prm∂xm∂prm∂ym∂prm∂(ctbiasm)∂r•1∂x1∂r•1∂y1∂r•1∂(ctbias1)|||∂r•m∂xm∂r•m∂ym∂r•m∂(ctbiasm)]. Finally, the fourth form of DoP is
the Horizontal Dilution of Precision (HDoP). It provides an estimate of user
positioning accuracy when both time and user altitude are known, only requiring
two navigation signals, such as the case of a two-way mode of operation with
good knowledge of terrain. This requires that only one satellite be in view to
kinematically solve for the user's topocentric North and East components. The HDoP metric is used to evaluate a
navigation system operating in two-way mode with terrain information. Equation (5)
provides the associated H matrix for the HDoP metric(5)H=[∂r1∂x1∂r1∂y1||∂rm∂xm∂rm∂ym∂r•1∂x1∂r•1∂y1||∂r•m∂xm∂r•m∂ym].


### 3.3. System Availability

The underlying figure of merit (FOM)
used for evaluating the performance associated with a navigation system is
system availability. System availability is defined here as the proportion of
time that the navigation system is predicted to provide performance at or below
a specified level of DoP. In other words, the navigation system is defined as
“available” when the appropriately chosen version of DoP falls below a certain
threshold. For this study, as in previous studies, the threshold is set at 10
[4–6]. Furthermore, a DoP of 10, coupled with a 1 meter user range error,
implies a user state uncertainty of 10 meters. Results provided are in terms of
system availability for a given latency, whether the solution have zero latency
(kinematic) or dynamic solutions of 15 minutes or one hour. Equation (6)
describes how the system availability FOM is calculated, where SA represents
system availability. This results in an estimate of the percentage of time that
the system availability condition has been satisfied(6)SA=100*∑m=1tncos(latm)*∑n=1tf(DoPn,m≤threshold)tf*nlong*∑m=1nlatcos(latm). The variables listed in  (6) are as follows:(i)
nlat is the number of latitude points in the
simulation;(ii)
nlong is the number of longitude points in the
simulation;(iii)
latm is the latitude value of the mth simulation
point of interest;(iv)
tf is the number of time epochs in the
simulation;(v)
tn is the total number of points in the
simulation.


### 3.4. Navigation Signal

The navigation signal requirements used in this study are outlined in Table3.Table 3
Navigation signal assumptions.
Frequency used forGPS L1 (1.57545 GHz)Doppler measurementsURE (user range error)1 mURRE (user range rate error)0.1 mm/sec


### 3.5. Simulation

The lunar South Pole region is taken as a set of 721 points on the surface, spaced evenly in
latitude and longitude. The longitudes for the points go from −175°E to 180°E in 5° increments, and the latitudes of the points
go from −89°N to −80°N in 1° increments. There is an additional point of
interest that is added to the set of data points which is located at the exact South
Pole of −90°N. The analysis is performed over the duration of 1 lunar sidereal
month (27.3 Earth days), where DoPs are calculated at an epoch rate of 15 minutes.
The starting epoch for the simulations is Jan 1, 2020 12 : 00 : 00.000 UTC. Visibility
to the constellations from the surface points is computed based on a 10°
minimum user elevation angle. Figure 2 plots the surface sample points used for
the simulation along an orthographic projection of the lunar surface.Figure 2
Surface sample points.


### 3.6. User Burden

Receivers that support a reduced number of satellites will have an increased level of processing
or other sensing equipment associated with them. This situation leads to increased
user burden in   terms of the mass and power the host platform must provide to
the navigation receiver. To provide knowledge sufficient to infer user altitude
given a horizontal location, a large digital elevation map would have to be available
to the user. To provide an error comparable to the 1-m user range error (URE)
assumed for the system, the user is required to store approximately 1 TB of
terrain data for global coverage. For the user to have knowledge of terrain
within a 30-km radius of a starting point, approximately 100 MB is required for
storage.For a navigation system using two-way radiometric signals as a mode of operation, the two-way
radiometric assumption implies that the user would have to be able to transpond
the ranging signal which is initialized from the lunar-centric constellation or
Earth-based DSN assets. The clock synchronization, which is necessary for
one-way radiometric navigation systems, is not a requirement when using two-way
radiometric navigation signals for the system’s mode of operation.


## 3.1. Generalized DoP

The analysis performed is a
generalized version of the DoP metric [4–6] of which several forms are
subsequently used for analysis. The generalized DoP is derived from the
observability grammian, which is obtained by using the navigation user
equations of motion and the associated sequence of measurements. The equations of motion and the measurement
sequence are given by [4–6]. It is shown that the DoP metric takes the
following form, derived in [4–6]. Since the DoP metric is calculated for a
stationary user, the state transition matrix is an identity matrix and the
measurement partial derivation matrix is utilized directly in (1)(1)max(eig((∑t0tnHtiTWHti)−1)). The variables listed in (1) are as
follows:(i)
eig(·)
is the Matlab function that calculates the eigenvalues of the input matrix;(ii)
t0 is
time step zero;(iii)
tn is the nth time step since time step zero;(iv)
Hti is the partial derivative measurement matrix at the ith
time step;(v)
W is the measurement weighting matrix.


## 3.2. Variations of Generalized DoP

In order to relax the constraint of
satellite coverage to invert the observability grammian, a number of
augmentations to the lunar navigation system are considered in the analysis, as
in previous analyses [7]. These
augmentations constrain the navigation solution and thereby reduce the number
of required satellites in view. These augmentations include clock
synchronization and good knowledge of the terrain, and create four forms of
DoP. The selected form of DoP used not only affects the required satellites in
view, but also the state transition and H matrices used in the calculation. It
should also be noted that throughout the analysis, both range and range-rate
(Doppler) measurements are used to solve for position and time bias (when
appropriate) estimates only. There are no estimates done for velocity or
frequency bias, as the users are assumed to be stationary.The first form of DoP is the
geometric dilution of precision (GDoP). It is used in the global positioning
system (GPS), where the solution is obtained for position of the user in three
dimensions and the time bias, resulting in the requirement of four navigation
signals. Since two navigation signals are available from each satellite, then
only two satellites are necessary in view to kinematically solve for the user’s
position. Without two satellites in
view, the solution will need to be integrated over time in order to be able to
invert the solution and solve for the user’s position and time bias. The GDoP
metric is used to evaluate a navigation system operating in one-way mode
without terrain information. Equation (2) provides the associated H matrix for
the GDoP metric(2)H=[∂pr1∂x1∂pr1∂y1∂pr1∂z1∂pr1∂(ctbias1)||||∂prm∂xm∂prm∂ym∂prm∂zm∂prm∂(ctbiasm)∂r•1∂x1∂r•1∂y1∂r•1∂z1∂r•1∂(ctbias1)||||∂r•m∂xm∂r•m∂ym∂r•m∂zm∂r•m∂(ctbiasm)]. The variables listed in (2) are as
follows:(i)
H is the partial derivative measurement matrix;(ii)
(xm,ym,zm) is the position of the surface user;(iii)
prm is the mth pseudorange measurement;(iv)
tbiasm is the clock bias of the surface user;(v)
r˙m is the mth range rate measurement;(vi)
c is the speed of light in a vacuum;(vii)
∂ is the partial derivative operator. The second form of DoP is the positional
dilution of precision (PDoP). It provides an estimate of user positioning
accuracy for the case in which there is no time bias between orbiter clocks and
user clocks, such as the case in a two-way mode of operation. PDoP results in
the requirement of three navigation signals. Thus, the PDoP metric also
requires two satellites in view to kinematically solve for the user’s position.
The PDoP metric is used to evaluate a navigation system operating in two-way
mode without terrain information. Equation (3) provides the associated H matrix
for the PDoP metric(3)H=[∂r1∂x1∂r1∂y1∂r1∂z1|||∂rm∂xm∂rm∂ym∂rm∂zm∂r•1∂x1∂r•1∂y1∂r•1∂z1|||∂r•m∂xm∂r•m∂ym∂r•m∂zm]. The new variable listed in (3) is as
follows:(i)
rm is the mth pseudorange measurement.The third form of DoP is the horizontal/time
dilution of precision (HTDoP). This form of DoP is applied when a user has
knowledge of their altitude above the center of the Moon, but still has a time
bias from the source of the navigation signal. This also results in the
requirement of three navigation signals, meaning that two satellites must be in
view to kinematically solve for the user's topocentric North and East
components along with the time bias. The HTDoP metric is used to evaluate a
navigation system operating in one-way mode with terrain information. Equation (4)
provides the associated H matrix for the HTDoP metric(4)H=[∂pr1∂x1∂pr1∂y1∂pr1∂(ctbias1)|||∂prm∂xm∂prm∂ym∂prm∂(ctbiasm)∂r•1∂x1∂r•1∂y1∂r•1∂(ctbias1)|||∂r•m∂xm∂r•m∂ym∂r•m∂(ctbiasm)]. Finally, the fourth form of DoP is
the Horizontal Dilution of Precision (HDoP). It provides an estimate of user
positioning accuracy when both time and user altitude are known, only requiring
two navigation signals, such as the case of a two-way mode of operation with
good knowledge of terrain. This requires that only one satellite be in view to
kinematically solve for the user's topocentric North and East components. The HDoP metric is used to evaluate a
navigation system operating in two-way mode with terrain information. Equation (5)
provides the associated H matrix for the HDoP metric(5)H=[∂r1∂x1∂r1∂y1||∂rm∂xm∂rm∂ym∂r•1∂x1∂r•1∂y1||∂r•m∂xm∂r•m∂ym].


## 3.3. System Availability

The underlying figure of merit (FOM)
used for evaluating the performance associated with a navigation system is
system availability. System availability is defined here as the proportion of
time that the navigation system is predicted to provide performance at or below
a specified level of DoP. In other words, the navigation system is defined as
“available” when the appropriately chosen version of DoP falls below a certain
threshold. For this study, as in previous studies, the threshold is set at 10
[4–6]. Furthermore, a DoP of 10, coupled with a 1 meter user range error,
implies a user state uncertainty of 10 meters. Results provided are in terms of
system availability for a given latency, whether the solution have zero latency
(kinematic) or dynamic solutions of 15 minutes or one hour. Equation (6)
describes how the system availability FOM is calculated, where SA represents
system availability. This results in an estimate of the percentage of time that
the system availability condition has been satisfied(6)SA=100*∑m=1tncos(latm)*∑n=1tf(DoPn,m≤threshold)tf*nlong*∑m=1nlatcos(latm). The variables listed in  (6) are as follows:(i)
nlat is the number of latitude points in the
simulation;(ii)
nlong is the number of longitude points in the
simulation;(iii)
latm is the latitude value of the mth simulation
point of interest;(iv)
tf is the number of time epochs in the
simulation;(v)
tn is the total number of points in the
simulation.


## 3.4. Navigation Signal

The navigation signal requirements used in this study are outlined in Table3.Table 3
Navigation signal assumptions.
Frequency used forGPS L1 (1.57545 GHz)Doppler measurementsURE (user range error)1 mURRE (user range rate error)0.1 mm/sec


## 3.5. Simulation

The lunar South Pole region is taken as a set of 721 points on the surface, spaced evenly in
latitude and longitude. The longitudes for the points go from −175°E to 180°E in 5° increments, and the latitudes of the points
go from −89°N to −80°N in 1° increments. There is an additional point of
interest that is added to the set of data points which is located at the exact South
Pole of −90°N. The analysis is performed over the duration of 1 lunar sidereal
month (27.3 Earth days), where DoPs are calculated at an epoch rate of 15 minutes.
The starting epoch for the simulations is Jan 1, 2020 12 : 00 : 00.000 UTC. Visibility
to the constellations from the surface points is computed based on a 10°
minimum user elevation angle. Figure 2 plots the surface sample points used for
the simulation along an orthographic projection of the lunar surface.Figure 2
Surface sample points.


## 3.6. User Burden

Receivers that support a reduced number of satellites will have an increased level of processing
or other sensing equipment associated with them. This situation leads to increased
user burden in   terms of the mass and power the host platform must provide to
the navigation receiver. To provide knowledge sufficient to infer user altitude
given a horizontal location, a large digital elevation map would have to be available
to the user. To provide an error comparable to the 1-m user range error (URE)
assumed for the system, the user is required to store approximately 1 TB of
terrain data for global coverage. For the user to have knowledge of terrain
within a 30-km radius of a starting point, approximately 100 MB is required for
storage.For a navigation system using two-way radiometric signals as a mode of operation, the two-way
radiometric assumption implies that the user would have to be able to transpond
the ranging signal which is initialized from the lunar-centric constellation or
Earth-based DSN assets. The clock synchronization, which is necessary for
one-way radiometric navigation systems, is not a requirement when using two-way
radiometric navigation signals for the system’s mode of operation.


## 4. Results

Results are reported as the system availability FOM and are presented in tabular form for the
lunar South Pole regions. The term “no terrain” indicates that there is no
detailed cartography of the terrain that would allow determining the altitude
of the user. The term “good terrain” indicates that there is such knowledge and
that an accurate estimate of user altitude above the lunar datum is available
to the navigation receiver.  The term “one-way”
indicates that the mode of operation for the navigation system is such that
signals are transmitted via the lunar-centric constellation or Earth-based DSN
assets and received by the lunar stationary surface user. The term “two-way”
indicates that the mode of operation for the navigation system is such that
signals are transmitted via the lunar-centric constellation or Earth-based DSN
assets and transponded by the lunar stationary surface user back to the
original transmitter, which then sends data back to the lunar stationary
surface user for position determination. Tables4 through 7 provide the system
availability results for the four navigation system types previously described.Table 4
System availability—“one-way, no terrain” results.
ConfigurationKinematicDynamic (15 min)Dynamic (1 h)Ellip 1/1/0 a65410.000.008.74Ellip 2/1/0 a65410.0034.1861.50DSN0.000.000.00Ellip 1/1/0 a6541 + DSN2.833.8412.53Ellip 2/1/0 a6541 + DSN4.9137.6763.62Table 5
System availability—“one-way, good terrain” results.
ConfigurationKinematicDynamic (15 min)Dynamic (1 h)Ellip 1/1/0 a65410.0071.4377.12Ellip 2/1/0 a654146.31100.00100.00DSN0.000.000.06Ellip 1/1/0 a6541 + DSN3.7571.6277.35Ellip 2/1/0 a6541 + DSN49.12100.00100.00Table 6
System availability—“two-way, no terrain” results.
ConfigurationKinematicDynamic (15 min)Dynamic (1 h)Ellip 1/1/0 a65410.0071.4277.12Ellip 2/1/0 a654146.31100.00100.00DSN0.450.591.12Ellip 1/1/0 a6541 + DSN3.8671.7877.51Ellip 2/1/0 a6541 + DSN49.41100.00100.00Table 7
System availability—“two-way, good terrain” results.
ConfigurationKinematicDynamic (15 min)Dynamic (1 h)Ellip 1/1/0 a654173.3175.2080.90Ellip 2/1/0 a6541100.00100.00100.00DSN4.804.945.24Ellip 1/1/0 a6541 + DSN74.6576.4981.94Ellip 2/1/0 a6541 + DSN100.00100.00100.00These results are also summarized in a stoplight chart, which shows the performance of each of
the configurations proposed herein in terms of the latency required to achieve
80% system availability over the lunar South Pole region. The correlation between
color and latency is as follows.(i)
A box shaded green indicates that the
configuration meets the 80% system availability kinematically.(ii)
A box shaded yellow indicates that the
configuration meets the 80% system availability dynamically in 15 minutes.(iii)
A box shaded red indicates that the
configuration meets the 80% system availability dynamically in one hour.(iv)
A box shaded gray indicates that the
configuration does not meet the 80% system availability within one hour.
It does not mean that the system does not meet the 80% system availability
at all, but rather it indicates that it could take more than one hour to
do so if it will do so.Table8 illustrates the performance of the five configurations in the stoplight chart
form. This form will be useful in making comparisons between configurations.Table 8
System availability—“two-way, good terrain” results.Inspection of the latency result summary provided in Table8 and the system availability
summaries provided in Tables 4 through 7 reveal four general trends apparent in
the lunar South Pole region overall.  The
first general trend is that system availability improves for a given
constellation as the solution is integrated over time. Also, there are larger
improvements when comparing the transition to the 15-minute dynamic solution
(from the kinematic solution) as compared with the transition to the one-hour
dynamic solution (from the 15-minute dynamic solution). It appears that with
these sparse constellations the system availability curve plotted against
integrated time levels off to a non-100% value. Further analysis would be
needed to validate that observation.The second general trend observed for the lunar South Pole region is that the system availability
improves for either a one-way or two-way navigation system with the inclusion
of the local terrain information. This is due to the need for fewer signal
sources necessary to solve for the reduced number of states being solved for.
In a one-way navigation system, four states are solved for by the DoP
technique, which are the localx, y, and z topocentric coordinates and the time
bias. Providing local terrain information removes the need to solve for the
local topocentric z coordinate. Similar statements can be made regarding a
two-way navigation system.The third general trend observed between the one-way and two-way navigation system modes is that
the two-way mode is better than the one-way mode in providing a navigation
solution for all the configurations examined. The results in Table8 show
improvements in system availability above the 80% threshold in the stoplight
chart for the two-way system over that of the one-way system. This is true for
cases with and without local terrain information. Results show that the
Elliptical 2/1/0 constellation can provide 100% system availability with a
dynamic solution of 15 minutes in the two-way mode, compared with a system
availability of 34% in one-way mode with a dynamic solution of 15 minutes. Only
the Elliptical 2/1/0 constellation (with and without the DSN augmentation) can
provide the 80% system availability kinematically, when operating in two-way
mode with local terrain information.The fourth general trend observed is that the combinations of the elliptical lunar-centric
constellations and the Earth-based DSN ground stations did not significantly
improve system availabilities for all the configurations. Data provided in Tables4 through 7 tabulate the system availabilities for all of the
configurations for the different systems schemes. It is observed that the
system availabilities obtained for the Ellip 1/1/0 a6541 + DSN and Ellip 2/1/0
a6541 + DSN configurations are not much larger than for the Ellip 1/1/0 a6541
or Ellip 2/1/0 a6541 configurations, respectively. Therefore, it can be
determined that the geometry added via the DSN measurements does not improve
the geometry from the lunar-centric measurements by a significant factor.It is important to note that the performance of the DSN configuration should not be expected to
be above a system availability of 50%. The reason for this is that half of the
points in the simulation are on the lunar far side, the side that does not face
toward the Earth. It is noted that due to the wobble of the Moon in orbit, that
some points near the lunar South Pole could face the Earth when the Moon is
tilted away from the Earth in the Moon’s northern hemisphere. However, those
points would still require a minimum user elevation angle of 10° to consider
measurements visible. Therefore, at most, only the lunar nearside points could
have access to the Earth-based DSN ground stations.


## 5. Conclusions

Generalized DoP allows the effects of multiple radiometric measurements to be assessed in the
same manner that standard measures of DoP are used. In the current case, the
effect of integrating multiple radiometric measurements in time is assessed to
allow the performance of sparse constellations around the Moon to be analyzed
and compared with kinematic only solutions. Using this innovation, the basis of
comparison can be changed to a domain that is more closely aligned with user
requirements, namely, the latency associated with achieving a particular level
of precision in the state estimate.A restriction to the use of kinematic solutions, as is done with analysis based on static DoP,
biases the selection of a constellation to those with more satellites. The use
of dynamic solutions allows for integrating radiometric signals over a period
of time to improve the system availability and thus allows for the
consideration of constellations with fewer satellites. The application of
generalized DoP for the evaluation of inherent navigation capability of
constellations of lunar-centric satellites, Earth-based DSN assets, and
combinations thereof has eliminated this bias.Inspection of the results summaries provided in Tables4 through 8 reveal several trends. First,
time integration of the solution will improve the system availability metric
and lower the estimated solution error. Second, use of a local terrain map can
improve system performance for both one-way and two-way navigation systems.
Third, use of a two-way navigation system has improved performance over the use
of a one-way navigation system due to the lack of needing to solve for the
user’s time bias. Finally, augmenting the lunar-centric constellations with the
Earth-based DSN assets provides minimal improvements in system availability
performance. It should also be noted that the Earth-based DSN configuration
exhibits system availabilities of a maximum of 5% during the case of operating
as a two-way navigation system with local terrain information while integrating
the solution for one hour.From this list of possible configurations using the stated assumptions regarding visibility, the
recommended constellation would be the Ellip 2/1/0 a6541. The navigation system
should operate in two-way mode, collecting range and range-rate measurements
while be augmented via a local terrain map. Under this mode of operation for
the Ellip 2/1/0 a6541 satellite constellation, the 80% system availability
metric can be met kinematically with a predicted system availability of 100%.
The Ellip 2/1/0 a6541 + DSN constellation also provides this level of system
availability, but is therefore not necessary to meet a DoP threshold of 10,
corresponding to an error on the order of 10 meters.



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*Source: 435961-2008-04-09.xml*