This document provides an overview of GPS (Global Positioning System) including its history, components, signals, measurements, and applications. It discusses how GPS uses precise timing signals from satellites combined with trilateration to determine user locations on Earth. It also covers topics like reference frames, datums, orbit determination, and factors that influence satellite positioning.
These applications fall into five :Location - determining a basic position Navigation - getting from one location to another Tracking - monitoring the movement of people/things Mapping - creating maps of the world Timing - bringing precise timing to the world
These applications fall into five :Location - determining a basic position Navigation - getting from one location to another Tracking - monitoring the movement of people/things Mapping - creating maps of the world Timing - bringing precise timing to the world
Brilliant Lecture delivered to me in Alagappa Engineering college Workshop.
The Global Positioning System (GPS) is a satellite
based radio navigation system provided by the
United States Department of Defence. It gives
unequaled accuracy and flexibility in positioning
for navigation, surveying and GIS data collection.
This presentation gives an overview of the networking and conceptualize the terms of the Satellite networking systems, and also provide a glance of the typical functionality of the satellite system in establishing the worldwide mobile communication system, as well as the broadcasting system.
With the support and encouragement of my faculty and friends developed this presentation...
Thank you
Application of differential systems in global navigation satellite systemsAli N.Khojasteh
Global Navigation Satellite Systems (GNSS) include different parts such as control and monitoring stations for the Earth and space settings. Timing, positioning, and control of navigation methods are the main outputs of GNSS. Based on Approach Procedure with Vertical guidance (APV), local and global Satellite Navigation Systems used for positioning and precision approach in aviation instead of present systems like Instrumental Landing Systems (ILS) and its future predict of ICAO. But these systems have errors in positioning and
velocity measurements. The differential corrections are determined by single or multiple reference stations. The single reference station concept is simple but the position accuracy is decreases. This article compares differential systems methods for correcting the errors.
The Global Positioning System (GPS), originally Navstar GPS,[1][2] is a space-based radionavigation system owned by the United States government and operated by the United States Air Force. It is a global navigation satellite system that provides geolocation and time information to a GPS receiver anywhere on or near the Earth where there is an unobstructed line of sight to four or more GPS satellites
Brilliant Lecture delivered to me in Alagappa Engineering college Workshop.
The Global Positioning System (GPS) is a satellite
based radio navigation system provided by the
United States Department of Defence. It gives
unequaled accuracy and flexibility in positioning
for navigation, surveying and GIS data collection.
This presentation gives an overview of the networking and conceptualize the terms of the Satellite networking systems, and also provide a glance of the typical functionality of the satellite system in establishing the worldwide mobile communication system, as well as the broadcasting system.
With the support and encouragement of my faculty and friends developed this presentation...
Thank you
Application of differential systems in global navigation satellite systemsAli N.Khojasteh
Global Navigation Satellite Systems (GNSS) include different parts such as control and monitoring stations for the Earth and space settings. Timing, positioning, and control of navigation methods are the main outputs of GNSS. Based on Approach Procedure with Vertical guidance (APV), local and global Satellite Navigation Systems used for positioning and precision approach in aviation instead of present systems like Instrumental Landing Systems (ILS) and its future predict of ICAO. But these systems have errors in positioning and
velocity measurements. The differential corrections are determined by single or multiple reference stations. The single reference station concept is simple but the position accuracy is decreases. This article compares differential systems methods for correcting the errors.
The Global Positioning System (GPS), originally Navstar GPS,[1][2] is a space-based radionavigation system owned by the United States government and operated by the United States Air Force. It is a global navigation satellite system that provides geolocation and time information to a GPS receiver anywhere on or near the Earth where there is an unobstructed line of sight to four or more GPS satellites
Levelwise PageRank with Loop-Based Dead End Handling Strategy : SHORT REPORT ...Subhajit Sahu
Abstract — Levelwise PageRank is an alternative method of PageRank computation which decomposes the input graph into a directed acyclic block-graph of strongly connected components, and processes them in topological order, one level at a time. This enables calculation for ranks in a distributed fashion without per-iteration communication, unlike the standard method where all vertices are processed in each iteration. It however comes with a precondition of the absence of dead ends in the input graph. Here, the native non-distributed performance of Levelwise PageRank was compared against Monolithic PageRank on a CPU as well as a GPU. To ensure a fair comparison, Monolithic PageRank was also performed on a graph where vertices were split by components. Results indicate that Levelwise PageRank is about as fast as Monolithic PageRank on the CPU, but quite a bit slower on the GPU. Slowdown on the GPU is likely caused by a large submission of small workloads, and expected to be non-issue when the computation is performed on massive graphs.
Unleashing the Power of Data_ Choosing a Trusted Analytics Platform.pdfEnterprise Wired
In this guide, we'll explore the key considerations and features to look for when choosing a Trusted analytics platform that meets your organization's needs and delivers actionable intelligence you can trust.
06-04-2024 - NYC Tech Week - Discussion on Vector Databases, Unstructured Data and AI
Discussion on Vector Databases, Unstructured Data and AI
https://www.meetup.com/unstructured-data-meetup-new-york/
This meetup is for people working in unstructured data. Speakers will come present about related topics such as vector databases, LLMs, and managing data at scale. The intended audience of this group includes roles like machine learning engineers, data scientists, data engineers, software engineers, and PMs.This meetup was formerly Milvus Meetup, and is sponsored by Zilliz maintainers of Milvus.
ViewShift: Hassle-free Dynamic Policy Enforcement for Every Data LakeWalaa Eldin Moustafa
Dynamic policy enforcement is becoming an increasingly important topic in today’s world where data privacy and compliance is a top priority for companies, individuals, and regulators alike. In these slides, we discuss how LinkedIn implements a powerful dynamic policy enforcement engine, called ViewShift, and integrates it within its data lake. We show the query engine architecture and how catalog implementations can automatically route table resolutions to compliance-enforcing SQL views. Such views have a set of very interesting properties: (1) They are auto-generated from declarative data annotations. (2) They respect user-level consent and preferences (3) They are context-aware, encoding a different set of transformations for different use cases (4) They are portable; while the SQL logic is only implemented in one SQL dialect, it is accessible in all engines.
#SQL #Views #Privacy #Compliance #DataLake
STATATHON: Unleashing the Power of Statistics in a 48-Hour Knowledge Extravag...sameer shah
"Join us for STATATHON, a dynamic 2-day event dedicated to exploring statistical knowledge and its real-world applications. From theory to practice, participants engage in intensive learning sessions, workshops, and challenges, fostering a deeper understanding of statistical methodologies and their significance in various fields."
Enhanced Enterprise Intelligence with your personal AI Data Copilot.pdfGetInData
Recently we have observed the rise of open-source Large Language Models (LLMs) that are community-driven or developed by the AI market leaders, such as Meta (Llama3), Databricks (DBRX) and Snowflake (Arctic). On the other hand, there is a growth in interest in specialized, carefully fine-tuned yet relatively small models that can efficiently assist programmers in day-to-day tasks. Finally, Retrieval-Augmented Generation (RAG) architectures have gained a lot of traction as the preferred approach for LLMs context and prompt augmentation for building conversational SQL data copilots, code copilots and chatbots.
In this presentation, we will show how we built upon these three concepts a robust Data Copilot that can help to democratize access to company data assets and boost performance of everyone working with data platforms.
Why do we need yet another (open-source ) Copilot?
How can we build one?
Architecture and evaluation
Techniques to optimize the pagerank algorithm usually fall in two categories. One is to try reducing the work per iteration, and the other is to try reducing the number of iterations. These goals are often at odds with one another. Skipping computation on vertices which have already converged has the potential to save iteration time. Skipping in-identical vertices, with the same in-links, helps reduce duplicate computations and thus could help reduce iteration time. Road networks often have chains which can be short-circuited before pagerank computation to improve performance. Final ranks of chain nodes can be easily calculated. This could reduce both the iteration time, and the number of iterations. If a graph has no dangling nodes, pagerank of each strongly connected component can be computed in topological order. This could help reduce the iteration time, no. of iterations, and also enable multi-iteration concurrency in pagerank computation. The combination of all of the above methods is the STICD algorithm. [sticd] For dynamic graphs, unchanged components whose ranks are unaffected can be skipped altogether.
Algorithmic optimizations for Dynamic Levelwise PageRank (from STICD) : SHORT...
gps_details.ppt
1. Introduction to GPS
“… it isn’t hard to operate a GPS receiver –
matter of fact, most of them are so user-
friendly you don’t need to know the first thing
about GPS to make them work; that is, until
they don’t. Getting coordinates from a GPS
receiver is usually a matter of pushing
buttons, but knowing what those coordinates
are, and more importantly, what they aren’t,
is more difficult.”
Jan Van Sickle
2. Use of Satellites in Surveying
Started as early as Sputnik (1957)
Continued with other satellites
– Measuring positions of satellites against
background stars on photographs
– Laser ranging
– Used Doppler effect to determine velocity
vector
3. TRANSIT Satellite
Navy Navigation Satellite System (NNSS) started in
1960s
Used the Doppler shift of the signal to determine
velocity vector
Six satellites in low (1100 km) circular, polar orbits
One satellite every 90 minutes, need 2 passes
– Susceptible to atmospheric drag and gravitational
perturbations
– Poor quality orbital parameters
Produces poor positions (by modern standards)
4. Brief History of GPS
Initial work in 1970s
– Counselman, Shapiro, etc. (MIT)
First used for practical purposes in 1980s
– Civilian use ahead of military use
Initial operational capability (IOC) July ‘93
Full operational capability (FOC) 17 July 1995
5. GPS Overview
Consists of ~24 satellites
4 satellites in 6 orbital planes
– Planes inclined 55°
20,000 km orbits
– Periods of 11h 58m
Each satellite carries multiple atomic clocks
6. GPS Segments
User Segment
– Military and civilian users
Space Segment
– 24 satellite constellation
Control Segment
– Worldwide network of stations
7. Space Segment
Block I
Block II
Block IIA (A – advanced)
Block IIR (R – replenishment)
Block IIF (F – Follow on)
Block III
– See http://www.spaceandtech.com/spacedata/constellations/navstar-
gps-block1_conspecs.shtml
9. Control Segment
Worldwide network of stations
– Master Control Station – Colorado Springs, CO
– Monitoring Stations – Ascension Island, Colorado
Springs, Diego Garcia, Hawaii, Kwajalein
Other stations run by National Imagery and Mapping
Agency (NIMA)
– Ground Control Stations – Ascension, Diego
Garcia, Kwajalein
11. Data Flow
Master Control Station
USNO
Monitor Station
USNO
AMC
Satellite Signal
Timing
Links
Time
Timing data
Control
Data
Satellite
Signal
12. Basic Idea
Broadcast signal has time embedded in it
Need to determine distance from satellite to
receiver
One way uses distance = velocity * time
– If time between when the signal is sent and when
it is received is known, then distance from satellite
is known
Using multiple distances, location can be
determined (similar to trilateration)
18. Codes
Stream of binary digits known as bits or
chips
– Sometimes called pseudorandom noise
(PRN) codes
Code state +1 and –1
C/A code on L1
P code on L1 and L2
Phase modulated
19. C/A Code
1023 binary digits
Repeats every millisecond
Each satellite assigned a unique C/A-code
– Enables identification of satellite
Available to all users
Sometimes referred to as Standard Positioning
Service (SPS)
Used to be degraded by Selective Availability
(SA)
20. P Code
10 times faster than C/A code
Split into 38 segments
– 32 are assigned to GPS satellites
– Satellites often identified by which part of the
message they are broadcasting
PRN number
Sometimes referred to as Precise Positioning
Service (PPS)
When encrypted, called Y code
– Known as antispoofing (AS)
21. Future Signal
C/A code on L2
2 additional military codes on L1 and L2
3rd civil signal on L5 (1176.45 MHz)
– Better accuracy under noisy and multipath
conditions
– Should improve real-time kinematic (RTK)
surveys
22. Time Systems
Each satellite has multiple atomic clocks
– Used for time and frequency on satellite
GPS uses GPS Time
– Atomic time started 6 January 1980
– Not adjusted for leap seconds
– Used for time tagging GPS signals
Coordinated Universal Time (UTC)
– Atomic time adjusted for leap seconds to be within
±0.9 s of UT1 (Earth rotation time)
23. Pseudorange Measurements
Can use either C/A- or P-code
Determine time from transmission of
signal to when the signal is received
Distance = time*speed of light
Since the position of the satellite is
assumed to be known, a new position
on the ground can be determined from
multiple measurements
24. Carrier-phase Measurements
The range is the sum of the number of full
cycles (measured in wavelengths) plus a
fractional cycle
– ρ = N*λ + n* λ
The fraction of a cycle can be measured very
accurately
Determining the total number of full cycles
(N) is not trivial
– Initial cycle ambiguity
– Once determined, can be tracked unless …
25. Cycle Slips
Discontinuity or jump in phase
measurements
– Changes by an integer number
– Caused by signal loss
Obstructions
Radio interference
Ionospheric disturbance
Receiver dynamics
Receiver malfunction
26. How to Fix Cycle Slips?
Slips need to be detected and fixed
Triple differences can aid in cycle slips
– Will only affect one of the series
Should stand out
Once detected, it can be fixed
27. GPS Errors and Biases
Satellite Errors
– Potentially different for each satellite
Transmission Errors
– Depends on path of signal
Receiver Errors
– Potentially different for each receiver
28. Linear Combination
Errors and biases, which cannot be
modeled, degrade the data
Receivers that are ‘close enough’ have
very similar errors and biases
Data can be combined in ways to
mitigate the effects of errors and biases
29. Linear Combination
Combine data from two receivers to one
satellite
– Should have same satellite and
atmospheric errors
– Differences should cancel these effects out
30. Linear Combination
Combine data from one receiver to two
satellites
– Should have same receiver and
atmospheric errors
– Differences should cancel these effects out
31. Linear Combination
Combine data from two receivers to two
satellites
– Should have same receiver, satellite and
atmospheric errors
– Differences should cancel out
32. Linear Combination
Can also combine the L1 and L2 data to
eliminate the effects of the ionosphere
– Ionosphere-free combination
L1 and L2 phases can also be combined
to form the wide-lane observable
– Long wavelength
– Useful in resolving integer ambiguity
34. Two Reference Frames
Satellites operate in an inertial
reference frame
– Best way to handle the laws of physics
Receivers operate in a terrestrial
reference frame
– Sometimes called an Earth-centered,
Earth-fixed (ECEF) frame
– Best way to determine positions
35. Inertial Frame (Historically)
X axis through the vernal equinox
Y axis is 90° to the ‘east’
Z axis through the Earth’s angular
momentum axis
X-Y plane is the celestial equator
Z axis is through the celestial North Pole
37. Inertial Frame
Defined by the positions of distant radio
sources called quasars
Realization from observations provided by
Very Long Baseline Interferometry (VLBI)
– e.g. International Celestial Reference Frame
Right-handed, Cartesian coordinate system
38. Terrestrial Frame (Historically)
X axis through the Greenwich meridian
Y axis is 90° to the east
Z axis through the Earth’s angular
momentum axis
X-Y plane is the equator
Z axis is through the North Pole
40. Terrestrial Frame
Defined by the positions of reference points
Realization from observations provided by
VLBI, SLR, and GPS
– e.g. International Terrestrial Reference Frame
– e.g. World Geodetic System (WGS)-84
Right-handed, Cartesian coordinate system
41. Terrestrial Frame
Can transform from non-Cartesian (geodetic)
coordinates to Cartesian coordinates
– X = (N+h) cosφ cosλ
– Y = (N+h) cosφ sinλ
– Z = [ N(1-e2)+h] sin φ
Where N = a/sqrt(1-e2sin2 φ)
h = ellipsoid height
φ = latitude
λ = longitude
42. Transformation between
Frames
Transformation is accomplished through
rotation by Earth orientation parameters
(EOPs)
– Polar Motion (W)
– Earth rotation (T)
– Precession/nutation (P)(N)
xcts = (W)(T)(N)(P)xcis
43. Datums
Based on a reference ellipsoid
– Semimajor axis (a) and semiminor axis (b)
or semimajor axis (a) and flattening (f)
Needs to have a well defined center
(origin)
Needs to have a well defined direction
or axes (orientation)
44. Datums
Can be done with 8 parameters
– 2 define the ellipsoid
– 3 define the origin of the ellipsoid
– 3 define the orientation of the ellipsoid
45. Datums
North American Datum 1927 (NAD27)
– Clarke ellipsoid of 1866
North American Vertical Datum 1929
(NAVD29)
North American Datum 1983 (NAD83)
– GRS 1980 ellipsoid
North American Vertical Datum 1988
(NAVD88)
Even the last two have minimal input from
GPS
46. Vertical Measurements
Vertical measurements from GPS are
relative to the ellipsoid (ellipsoid height)
– Not from the geoid or topography
To translate to other surfaces (either
reference or real) requires additional
information
– Orthometric or geoid heights
48. HARN
High Accuracy Reference Network
(HARN)
Created by states, with federal assistance
(NGS)
Predominantly based on GPS
observations
– Very accurate
49. Plane Coordinate Systems
Used over ‘local’ areas
State Plane Coordinate (SPC) systems
– Results of projection onto surface
Lambert conic projection
Mercator (cylindrical) projection
50. Time Systems
Earth rotation time
– Solar/sidereal
Dynamical
– Barycenter/terrestrial
Atomic (off by integer seconds)
– Coordinated Universal Time (UTC)
– International Atomic Time (TAI)
– GPS Time
51. Calendar
Julian Date (JD) are days from noon (UT)
January 4713 BC
– JD = INT[365.25y] + INT[30.6001(m+1)] + D +
UT/24 + 1720981.5
y = Y-1 and m = M+12 if M ≤ 2
y = Y and m = M if M > 2
Modified Julian Date
– MJD = JD – 2400000.5
– http://tycho.usno.navy.mil/mjd.html
Calculator -
http://aa.usno.navy.mil/data/docs/JulianDate.html
53. Kepler Orbital Parameters
(Kepler Elements)
Ω – right ascension of ascending node
i – inclination of orbital plane
ω – argument of perigee
a – semimajor axis of orbital ellipse
e – numerical eccentricity of ellipse
T0 – epoch of perigee passage
55. Perturbation of Orbits
Mathematically, treat the problem as
small corrections to the idealized motion
Can use mathematical tricks to simplify
the problem
– Assume the corrections are sufficiently
‘small’
– Use Taylor’s Theorem
56. Disturbing Accelerations
Gravitational
– Nonsphericity of the Earth
– Tidal attraction (direct and indirect)
Nongravitational
– Solar radiation pressure
– Relativistic effects
– Solar wind
– Magnetic field
– Out-gassing
57. Nonsphericity of the Earth
The Earth’s potential can be
approximated using spherical harmonics
Disturbing Potential can be given as
R = V – V0
58. Tidal Effect (direct)
Celestial body will attract the satellite
The effect will be a function of the angle
between the celestial body, the Earth, and the
satellite
Only a few bodies need to be considered
– Sun
– Moon
– Venus
Acceleration is ~10-6 m/s2
59. Tidal Effect (indirect)
Celestial body will deform the Earth
– Both ocean tides and solid earth tides
Deformation of the Earth will perturb
the orbit of the satellite
Acceleration is ~10-9 m/s2
60. Solar Radiation Pressure
Sunlight impinging on a surface imparts
momentum
Two components
– Principal component away from the Sun
Modeled
– Component along satellite y-axis (y-bias)
Solved for
Eclipse ‘season’ causes additional problems
Acceleration is ~10-7 m/s2
61. Relativistic Effect
Caused by the Earth’s gravity field
Creates a perturbing acceleration
Acceleration is ~10-10 m/s2
62. Other
Solar Wind
– Sun emits a wind which interacts with
objects in the solar system
Magnetic Field
– Interaction of the Earth’s magnetic field
with a (metallic) satellite
Out-gassing
– Gasses from satellite evaporate
– Act similar to a jet
63. Orbit Dissemination
Best orbital determinations come from a
global network with a ‘good’ geometric
distribution
– Want ~30 stations if possible
Military network
– Monitoring Stations
Civilian
– International GPS Service (IGS)
64. Types of Orbits
Almanac
– Poor quality (~100m)
– Used well into the future
Broadcast
– Good quality (1-2m with SA off)
– Used in real-time work
Precise
– Excellent quality (5-10cm)
– Used in the most precise work
68. Summary of Carriers and
Codes
2 carrier waves
2 codes (+1 and –1)
Combined, they look like
– L1(t) = a1P(t)D(t)cos(f1t) +
a1C/A(t)D(t)sin(f1t)
Note the phase shift between the P-code and C/A-
code
– L2(t) = a2P(t)D(t)cos(f2t)
69. C/A Code
Produced by 2 10-bit feedback shift
registers
Frequency is 1.023 MHz
Repetition rate of 1ms
The code length is 1023 chips
Time interval between 2 chips is 1μs
– 300 m chip length
70. P Code
Produced by 2 shift registers
The code length is 2.3547*1014 bits
Corresponding time span is 266.4 days
Chip length is 30 m
To protect against deliberate misinformation,
combined with the encrypting W-code to
produce Y-code
– Only accessible if you know how to decode (i.e.
military applications)
71. Navigation Message
Contains information about each satellite
– Clocks, orbits, health, corrections
Subframes contain
– Telemetry word (TLM)
– Hand-over word (HOW)
– Clock Corrections
– Broadcast ephemeris
– Almanac data
72. Signal Processing
Different inputs (codes, NAV message,
carriers) get combined
Combined signal is broadcast by satellite
Receiver picks up broadcast and must
decompose the signal to recover
– Code
– Navigation message
– Carrier
73. Receivers
Must contain
– Signal reception (antenna)
Omnidirectional
Signals measured from phase center
– Signal processing
Microprocessor controls system
Control device provides communications
Storage device
74. Radio Frequency Signal
Need to discriminate between satellites
– Use unique codes
– Use unique Doppler shifts
Modern receivers use a separate channel for
each satellite (continuous tracking)
Receivers also need to be able to generate
frequency to create their own signals
– Usually uses internal oscillator
75. How to Determine Time?
PRN code generated on satellite
Identical code created in receiver
If the time on the satellite were
synchronized to the receiver, problem
solved
– Unfortunately, not the case
Trick is to match up the code to find time
Use autocorrelation
1
0
)
(
)
(
1
)
(
N
t
x
t
x
N
r
79. Code Squaring
Used to eliminate code information
– Results consist only of carrier wave
Multiply the modulated carrier by itself
(square the signal)
Code signal (which consists of +1 and –
1) becomes 1 throughout
– (+1)2 = 1
– (-1)2 = 1
83. Code Pseudorange
Based on travel time between when
signal is sent and when it is received
Time data also includes errors in both
satellite and receiver clocks
– Δt = tr – ts = [tr(GPS)-δr] – [ts(GPS) – δs]
Pseudorange given by R = c Δt = ρ +
cΔδ
– Pseudo because of cΔδ (where Δδ = δs – δr)
factor
84. Carrier Phase
Based on the number of cycles
(wavlengths) between satellite and
receiver
Phase data will include errors in both
the satellite and receiver as well as an
initial integer number, N
N
c
N
c
R
85. Doppler
Doppler shift depends on radial velocity
– More useful for determining velocities than
for determining positions
To get positions, need to integrate
Doppler shifts (phase differences)
c
dt
d
dt
d
D
86. Data Combinations
Theoretically, data can be obtained
from
– Code ranges – RL1, RL2
– Carrier phases – ΦL1, ΦL2
– Doppler shifts – DL1, DL2
Combinations of these data could be
used as well
87. Data Combinations
In general, linear combinations of phase
will look like
– φ = n1φ1 + n2φ2
– Where n1 and n2 can be any integer
Noise level increases for combined data
– Assuming noise levels are equal for both,
the increase is by a factor of √2
88. Data Combinations
If n1 = n2 = 1, then
– ΦL1+L2 = ΦL1 + ΦL2
Denoted narrow-lane
λL1+L2 = 10.7cm
If n1 = 1 and n2 = -1, then
– ΦL1-L2 = ΦL1 – ΦL2
Denoted wide-lane
λL1-L2 = 86.2cm
Used for integer ambiguity resolution
89. Data Combinations
If n1 = 1 and n2 = –fL2/fL1, then
– ΦL3 = ΦL1 – fL2/fL1 ΦL2
– Called L3 (sometimes denoted ionosphere-
free)
Used to reduce ionospheric effects
90. Combinations of Phase and
Code
Historically smoothed the code
pseudorange using carrier phase
Several different algorithms
Don’t see as many applications today
91. What to do with Errors?
There are essentially 4 options:
– Ignore them
Works if the errors are small (negligible)
– Model them
Need good models
Not all effects can be modeled
– Solve for them
Increases complexity of solution
– Make them go away
92. GPS Ephemeris Errors
3 types of ephemerides
– Almanac – very crude (~100m), used only
for planning purposes
– Broadcast – reasonably accurate (~1m),
used for real-time work
– Precise – very accurate (~10cm), used for
high precision work
Available after the fact
93. Selective Availability (SA)
Way to degrade the navigation accuracy
of the code pseudorange
Comprised of two parts:
– Dithering the satellite clock (δ-process)
– Manipulating the ephemerides (ε-process)
94. Selective Availability
Dithering the satellite clock
– Changing the fundamental frequency
– Changes over the course of minutes
– Can be eliminated by differencing between
receivers
Manipulating the ephemerides
– Truncating the navigational information
– Changes over the course of hours
95. Clock Errors
Both satellites and receivers will have clock
errors
– There’s no such thing as a perfect clock
Any error in a clock will propagate directly into
a positioning error
– Remember distance = velocity*time
Satellite clock errors can be reduced by
applying the corrections contained in the
broadcast
96. Ionospheric Delay
Caused by the electrically charged upper
atmosphere, which is a dispersive medium
– Ionosphere extends from 40 to 1100 km
– Effects carrier phase and code ranges differently
– Effect on the phase and group velocity
nph = 1 + c2/f2 …
ngr = 1 – c2/f2
– Note that this will effect frequencies differently
Higher frequency is affected less
97. Ionospheric Delay
Measured range given by s = ∫n ds
– n is the refractive index
– ds is the path that the signal takes
The path delay is given by
– Δph
iono = –(40.3/f2) ∫Ne ds0 = –40.3/f2 TEC
– Δgr
iono = (40.3/f2) ∫Ne ds0 = 40.3/f2 TEC
Where TEC = ∫Ne ds0 is the total electron
content
98. Ionospheric Delay
Still need to know TEC
Can either
– Measure using observations
– Estimate using models
Note that with data on 2 frequencies,
estimates of the unknowns can be
made
99. Tropospheric Delay
Caused by the neutral atmosphere, which is a
nondispersive medium (as far as GPS is
concerned)
– Troposphere extends up to 40 km
– Effects carrier phase and code ranges the same
Typically separate the effect into
– Dry component
– Wet component
ΔTrop = 10-6∫Nd
Trop ds + 10-6∫Nw
Trop ds
– Where N is the refractivity
– ds is the path length
100. Tropospheric Delay
Dry component contributes 90% of the
error
– Easily modeled
Wet component contributes 10% of the
error
– Difficult to model because you need to
know the amount of water vapor along the
entire path
101. Tropospheric Delay
There are many models which estimate the
wet component of the tropospheric delay
– Hopfield Model
– Modified Hopfield Model
– Saastamoinen Model
– Lanyi Model
– NMF (Niell)
– Many, many more
102. Special Relativistic
Considerations
Time dilation
– Moving clock runs slow
Lorentz contraction
– Moving object seems contracted
Second order Doppler effect
– Frequency is modified like time
Mass relation
103. General Relativistic
Considerations
Perturbations in the satellite orbit
Curvature of the path of the signal
– Longer than expected in Euclidian space
Effects on the satellite clock
– Clocks run fast further out of the potential
well
Effects on the receiver clock (Sagnac
effect)
104. Phase Center Errors
Phase center is the ‘point’ from which the
GPS location is measured
Difficult to measure precisely
Changes with different factors:
– Elevation
– Azimuth
– Frequency
Either model the error or reduce the effect of
the error by always orienting antenna the
same direction
105. Receiver Noise
All electronic devices will have a certain
amount of noise
Because of the characteristics of the
noise modeling is not an option
The best that can be done is average
the data to reduce the effects of the
noise
106. Multipath Errors
GPS assumes that the signal travels
directly from the satellite to the receiver
Multipath results from signal reflecting
off of surface before entering the
receiver
– Adds additional (erroneous) path length to
the signal
Difficult to remove; best to avoid
108. Geometric Factors
The strength of figure of the satellites is
taken into consideration by the dilution
of precision (DOP) factor
– Depends on number of satellites
– Depends on location of satellites
110. Geometric Factors
Different kinds of DOPs
– HDOP (horizontal)
– VDOP (vertical)
– PDOP (position) (3-D component)
– TDOP (time)
– GDOP (geometric) (PDOP and TDOP)
111. User Equivalent Range Error
(UERE)
Crude estimate of the expected error
Consists of contributions from
– Measurement noise
– Satellite biases
– Wave propagation errors
Transmitted through the Navigation
message
Combined with DOP information
113. General Thoughts on Survey
Accuracy
Project size
Density of control
Physical restrictions
Number of receivers
Adjustment capability
Station and reference azimuth mark visibility
Cost
Observation time
114. More Specific Thoughts
Code range vs. carrier phase
Real-time processing vs. postprocessing
Point positioning vs. relative positioning
Static vs. kinematic
116. Point Positioning
Determines the coordinates of the receiver
If using a single receiver, this is the only reasonable
option
Standard Positioning Service (SPS) uses C/A code
– ~10 m accuracy
Precise Positioning Service (PPS) uses both codes
– ~1 m accuracy
117. Differential GPS
Uses (at least) two receivers
– One located at a known point
– One used to determine position of unknown point
Typically uses pseudorange data
Known position used to compute corrections
At least four common satellites must be observed
118. Differential GPS
Correction transmitted to other receiver
– Need to have a (radio) data link
Data usually transmitted using the Radio
Technical Commission for Maritime Service,
Special Committee 104 (RTCM) format
Initial position combined with correction to
create a refined position
119. Relative Positioning
Uses (at least) two receivers
– One located at a known point
– One used to determine position of
unknown point
Typically uses carrier phase
Determine the vector between known
point and unknown point
120. Relative Positioning
Static
– Receivers remain stationary
Rapid Static
– Receivers remain stationary for short times
– Need good receivers (dual frequency)
121. Relative Positioning
Kinematic
– Receiver is continually moving
– Must maintain lock on 4 satellites at all times
Semi-kinematic (stop-and-go)
– Receiver makes brief stops
Pseudokinematic
– Receiver makes stops but must reoccupy after
significant (~1 hour) time
122. Field Equipment
Typical equipment includes (but not limited
to)
– Receiver
– Battery
– Meteorological sensor
– Tripod
– Tribrach
– Communication device
123. Survey Planning
Decide the extent of the planning
Study a map of the area
Point selection
Satellite coverage
– DOP estimates
Session length
Field reconnaissance
125. Organizational Design
Number of sessions
– n = (s-o)/(r-o)
s – number of sites
r – number of receivers
o – overlapping sites
– n = ms/r
m – number of times site to be occupied
126. Organizational Design
Radial survey
– One receiver placed at fixed site
– Other receivers placed at locations
– Measure lines from fixed site to other
locations
Network survey
– Closed geometric figures
128. Preobservation
Antenna setup
– Avoid multipath
– Center antenna over point
– Know antenna phase center
– Know your H.I.
Receiver calibration
– One antenna, two receivers
130. Observation
Communication can be crucial if
observations need to be coordinated
Receivers are automated
Need good DOPs
Potentially need to track same satellites
Can observe through rain but not
lightening
131. Survey Procedure
Postobservations
– Document!
Prepare site occupation sheet
Ties to the control monuments
– Usually need to connect the survey to
control
132. Data Processing
Transfer the data to computer
Process the data
– Use ‘canned’ software
– Two strategies for static surveys
Vector-by-vector (single baseline)
– Easier to detect bad baselines
Mulitpoint solutions
– Not as common
133. Vector Processing
(directly from the book)
1. Generation of orbit files.
2. Computation of the best fit value for point
positions from code pseudorange.
3. Creation of undifferenced phase data from
receiver carrier phase readings and satellite
orbit data. Time tags may also be corrected.
4. Creation of differenced phase data and of
computation of their correlations.
134. Vector Processing
(directly from the book)
5. Computation of an estimate of the vector
using triple-difference processing. This
method is insensitive to cycle slips but
provides least accurate results.
6. Computation of the double-difference
solution solving for vector and (floating point
or real) values of phase ambiguities.
7. Estimation of integer values for the phase
ambiguities computed in the previous step,
and decision whether to continue with fixed
ambiguities.
135. Vector Processing
(directly from the book)
8. Computation of the fixed bias solution
based upon best ambiguity estimates
computed in the previous step
9. Computation of several other fixed bias
solutions using integer values differing
slightly (e.g. by 1) from selected values
10. Computation of the ratio of statistical fit
between chosen fixed solution and the next
best solution. This ratio should be at least
two to three indicating that the chosen
solution is at least two to three times better
than the next most likely solution.
136. Troubleshooting
Easiest to see with single baseline
vectors
Check standard error estimates
Check ratio
Check rms
Check ambiguities
137. Network Adjustment
Check loop closures
Perform minimally constrained least-squares
solution
– Bad lines must be removed first
– Check computed coordinates with previous
Points with large shifts could be problematic
Check residuals (both normalized and
unnormalized)
Scale errors by appropriate factor
138. And Finally …
Transform coordinates into appropriate
coordinate system
Produce final report
– Formats will differ depending on employer
– See book for an example of things to
consider
140. Formats
Each receiver stores data in its own
(proprietary) binary format
– Saves space
Combining data from different receivers
could potentially be problematic
Need standard formats that are
supported by different equipment
142. RINEX
Receiver Independent Exchange (RINEX)
ASCII file
– Easily readable (even by people)
– Less compact than binary
Has been different versions
– Current version is 2.10
– Version 2.20 proposed to deal with low earth orbit
(LEO) satellites
143. RINEX
Six different RINEX files
1. Observation data file
2. Navigation message file
3. Meteorological file
4. GLONASS navigation message file
5. Geostationary satellites data file
6. Satellite and receiver clock file
144. RINEX
Naming convention is ssssdddf.yyt where
– ssss is the site designation
– ddd is the day of year of the first record
– f is the file sequence number
– yy is the two digit year
– t is the file type
O – observation
N – navigation
M – meteorological
G – GLONASS
H – geostationary
146. RINEX
Navigation file
– Header
– Data
Clock parameters
Broadcast orbit
Meteorological file
– Header
– Data
Temperature
Barometric Pressure
Relative Humidity
147. NGS-SP3
National Geodetic Survey – Standard
Product #3
ASCII file
Facilitates exchanging precise satellite
ephemerides
148. NGS-SP3
Header
– Information on observing session (date,
number of satellites,
Data
– Divided into epochs
– Each satellite on a separate line
Satellite orbits, clock corrections
149. RTCM SC–104
Radio Technical Commission for
Maritime Services, Special Committee
104
Original format used for transmitting
information for real-time DGPS
– Differential corrections
Current version 2.2
151. NMEA 0183
National Marine Electronics Association
ASCII file
Current version 3.0
Used to transmit GPS information from
the receiver to hardware that uses the
positioning as input
– Real-time marine navigation
153. Data Handling
Downloading
– Need to move data from receiver to computer
Data Management
– Need structure to handle large amounts of data
– Separating by projects is often used
Data Exchange
– Original data usually binary
– May want data in other formats
Most receivers now convert to Receiver Independent
Exchange (RINEX) format
154. Cycle Slips
When a receiver is turned on, there is an
initial integer number of wavelengths (Nj) for
every satellite j when measuring carrier phase
When a receiver loses lock on a particular
satellite, there is a new initial integer number
of wavelengths (Nj*) for every satellite j
– This event is called a cycle slip
– Note that Nj ≠ Nj*
Unfortunately, the receiver/software assumes
that Nj is a constant unless told otherwise
– Produces a sudden apparent jump in position
155. Cycle Slips
Generally caused by one of four things
– Obstructions
Caused by trees, buildings, bridges, mountains, etc.
Most frequent problem
– Low signal-to-noise (SNR) ratio
Caused by ionospheric conditions, multipath, high
receiver dynamics, low satellite elevations
– Failure in receiver software
Infrequent
– Malfunctioning satellite oscillators
Rare
157. Cycle Slips
Need to determine the instant at which
the slip occurs
– Accomplished by comparing observations
at successive epochs
– Often done using triple differences
‘Repairs’ consist of correcting all
subsequent observations for the jump
– Note that the jump must be an integer
158. Ambiguity Resolution
Assuming that tracking is continuous,
there is no time dependence to
equations
– Φ = λ-1ρ + fΔδ + N – λ-1ΔIono
– Need to determine integer ambiguity N
Once accomplished, ambiguity is said to be
resolved or fixed
Note that ambiguity resolution is not
always a possibility
159. Ambiguity Resolution
For instance, look at double differences
– λΦ = ρAB
jk(t) + λN + noise
– Effect of ionosphere, troposphere are
neglected
Any errors from these terms will
contaminate the parameter estimation
– The ‘best’ estimates (think least-squares) for
N may not be an integer even though they
should be
160. Ambiguity Resolution
Satellite geometry is an important
consideration
– More satellites with better geometry will
provide better DOPs
– Better DOPs will improve ambiguity resolution
Length of observation critical to ambiguity
resolution
– Want to track the satellite across the sky
161. Ambiguity Resolution
Multipath can make ambiguity
resolution more difficult
– It contaminates observations which makes
parameter estimation more difficult
162. Ambiguity Resolution
Three steps need to followed
– Determine the ‘search space’
– Identify the correct integers
– Validation of integer set
163. Ambiguity Resolution
Determine the ‘search space’
– Which integers could possibly be correct?
Remember that the problem is multi-dimensional
Every satellite will have an integer ambiguity
– Since the solution will be pulled from the search
space, you need to be conservative to ensure that
the correct integers will be selected
– However, the bigger the search space, the longer
it will take to find the integers
– In static positioning, can be determined
approximately from float solution
164. Ambiguity Resolution
Identify the correct integers
– Done statistically
– Minimizing sum of squared residuals
– Assume that the integers that best fit the
observations are most likely to be correct
– Also assumes that the integers are normally
distributed
Not always true
Most frequent cause of resolution failure in long
baselines
165. Ambiguity Resolution
Validation of integer set
– How correct are the integers selected?
– Success rate depends on
Observation equations
Precision of observables
Method of estimation
– Are the integers chosen significantly better
than the other possibilities
Look at ratio of the sum of squared residuals
Want the ratio to be three or greater
166. Ambiguity Resolution
Approaches
Single frequency phase data
Dual frequency phase data
Combining dual frequency carrier phase
and code data
Combining triple frequency carrier
phase and code data
– Only after modernization
167. Search Techniques
If processing double-differences by
least-squares, the initial estimates of
ambiguities are real (floating point)
numbers
– Called a float solution
Produces ‘best estimate’ of ambiguities
168. Search Techniques
However, the results won’t be correct because
the numbers won’t be integers
They will be close if
– Stations are close together
– Observation span is long
If the two results are close, the resulting
differences in position should be close
Otherwise, ambiguity resolution is more
important
169. Search Techniques
For the static case, the search space can be
created from the float ambiguity solution and
statistics
– Take the float solution estimate and use the
standard deviations to indicate how big a window to
use
– Typically use 3σ windows
The number of possibilities increases quickly
with the uncertainty and number of satellites
170. Search Techniques
Every ambiguity combination is checked
– Ambiguities are fixed to a set of integers inside
the search space
– Measurement residuals are computed for
observations
– Residual sum of squares is computed
The smallest residual sum of squares ‘wins’
Note that this number will be bigger than the
residual computed by least-squares
171. Search Techniques
The candidate solution needs to be validated
Often use the ratio of the residual sum of
squares between the best two integer
solutions
Ratio should be greater than 3
If not, the candidate may not be the best
solution
– May be safer to stick with the float solution
172. Search Techniques
If the observations are made in
kinematic mode, a float solution won’t
work to provide an initial estimate of
the ambiguities
– At every epoch, there is a new position
Typically use ‘on-the-fly’ ambiguity
resolution
173. Search Technique
Can use code solution to estimate position
– Need a good receiver
– The search space will be larger than for static case
because of the increased uncertainties
Use wide-lane to get a better estimate of the
position
– Smaller search space
Use improved position for final ambiguity
resolution
174. Search Technique
On-the-fly methods include
– Ambiguity function method
– Least-squares ambiguity search technique
– Fast ambiguity resolution approach
– Fast ambiguity search filter
– Least-squares ambiguity decorrelation adjustment
method
– Ambiguity determination with special constraints
175. Least-Squares Adjustment
Ax = ℓ where
– A – design matrix (m x 4)
– x – vector of unknowns (4 x 1)
– ℓ – vector of observations (m x 1)
– m – number of observations
In addition, let
– σ0
2 – a priori variance
– Σ – covariance matrix
176. Least-Squares Adjustment
Qℓ is called the cofactor matrix
– It is a covariance-like quantity
– Qℓ = σ0
-2Σ
The weight matrix is given by
– P = Qℓ
-1
177. Least-Squares Adjustment
To get a consistent solution, noise is added
– ℓ + n = Ax
A unique solution can be found with
– nTPn = minimum
– ATPAx = ATPℓ
– x = (ATPA)-1ATPℓ
– Qx = (ATPA)-1 (from covariance propagation)
178. Kalman Filtering
A way of combining different
observations which are related to each
other
Takes into account the uncertainties of
the observations
Optimal linear filter
– Must assume a linear process
– Optimal in many statistical senses
179. Linearization
Linearize equation using Taylor’s
theorem
Like many applications, only the first
order terms need to be included
– Higher order terms are small enough to be
neglected
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182. Linearization
We now have a linear equation that
relates the range to the unknown
positions
– In this case, the unknowns are actually the
(usually small) corrections
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183. Point Positioning
For this example, simplify the equation
to not account for ionosphere,
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184. Point Positioning
This assumes that the satellite clock
error is known
– Not a bad assumption because of the clock
corrections in the navigation signal
For every epoch, t, there are 4
unknowns
Observations from 4 satellites are
needed in order to solve the equations
188. Other Observations
Analogously, can set up equations for
carrier phase
– (or Doppler, or combinations, etc.)
Can also set up equations for relative
positioning
189. Network Adjustment
There are two methods of determining
positions of a network
– Single baseline solution
– Multipoint solution
190. Single Baseline Solution
Baseline by baseline computation
Need to compute for all possibilities
The number of baselines is
– ni(ni-1)/2
Where ni is the number of stations
Only ni-1are independent (Why?)
Redundant baselines are used
– For additional adjustment
– Misclosure checks
191. Single Baseline Solution
In the end, the vectors are subjected to
a simultaneous adjustment
Note that because of the way the
problem was set up, the correlations of
the simultaneously observed baselines
are ignored
– Not the correct way to handle the problem
theoretically
193. Single Baseline vs. Multipoint
(from text)
Correlations not modeled correctly with the
single baseline solution
Computer program simpler for single baseline
Computation time not an issue
Cycle slips easier to detect and repair in
multipoint solution
Easier to isolate (and eliminate) bad
measurements in single baseline
Correlations with multipoint while better than
single baseline still might not be perfect
194. Dilution of Precision
The dilution of precision (DOP) is a
measure of the geometry of the
satellites
It changes with time
– Number of satellites changes
– Position of satellites changes
196. Dilution of Precision
The first three elements in each row are
components of the unit vector pointing
from the four satellites to the observing
site i
Solution exists as long as the design
matrix (A) is non-singular
– The determinant is not zero
197. Dilution of Precision
The determinant is proportional to the
scalar triple product
The scalar triple product is one way to
compute the volume of a body defined
by the three vectors
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198. Dilution of Precision
The larger the volume, the better the
geometry
The better the geometry, the lower the
value of DOP
Therefore, want DOP to be inversely
proportional to the volume
199. Dilution of Precision
DOP can be calculated from the inverse
of the normal equation matrix
– QX = (ATA)-1 (if weight matrix is the
identity)
QX is called the cofactor matrix
– It is a covariance-like quantity
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201. Dilution of Precision
Similar quantities can be calculated for
the topocentric local coordinate system
– Axes along local north, east, and up
The global cofactor matrix QX needs to
be transformed into the local cofactor
matrix Qx
– Use the law of covariance propagation
203. Dilution of Precision
The three dimensional error, whether
computed in the equatorial coordinate
system or the local coordinate system
must be the same
However
– qXX ≠ qxx
– qYY ≠ qyy hh
yy
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204. Dilution of Precision
Assuming σ is the measurement accuracy,
positioning accuracy is given by
– GDOP σ – geometric accuracy in position and
time
– PDOP σ – accuracy in position
– TDOP σ – accuracy in time
– HDOP σ – accuracy in the horizontal position
– VDOP σ –accuracy in the vertical position
206. Integration
GPS determines positions
– Can provide a lot of input in a short
amount of time
Many other systems can use positions
as inputs
– Either real-time or post-processed
GPS and other technology make a good
match
207. GPS/GIS
Geographic information system (GIS)
– Acquires, stores, manipulates, analyzes,
and displaying spatially oriented data
– Data stored in layers
GIS is a tool to study the geographic
information
– Coordinates can be provided by GPS
208. GPS/GIS
Industries that use this combination
include
– Utility
– Forestry
– Agriculture
– Public safety
– Vehicle fleet management
209. GPS/LRF
Laser range finder (LRF)
– Uses laser to determine distance between
finder and target
– Needs to be tied to coordinate system
– Works as long as there is a line of sight
between finder and target
210. GPS/LRF
Set up GPS in an area with clear view of sky
Use LRF to determine distances and azimuth
from GPS to other objects
– Think about using this in a wooded area
– Capable of determining positions even in an area
where the sky is not clear enough for GPS
Needs some post-processing to combine the
data
211. GPS/Dead Reckoning
Utilizes odometer sensor and
gyroscopes
– Computes relative distance and direction
Determines distance with odometer
Determines changes in direction with gyroscope
Needs GPS to pin down positions in an
absolute frame
Used in automatic vehicle location
212. GPS/Dead Reckoning
Dead reckoning needs to continuous
information
GPS is subject to data outages
– Overpasses, urban canyons, trees, etc.
Odometer and gyroscopes subject to drift
Combining GPS positions and dead reckoning
information can provide better estimates of
positioning and direction always
– Uses Kalman filter to combine
Not good for accurate applications
213. GPS/INS
Inertial Navigation System (INS)
– Also inertial measurement unit (IMU)
Similar to dead reckoning equipment
Uses accelerometers and gyroscopes
– Determines accelerations
– Determines angular velocity
214. GPS/INS
GPS and INS (IMU) data combined
– Combination done with a Kalman filter
– Utilizes the best of both information
GPS good for long-term stability of positions
– Subject to data outages
INS good for determining moment-by-moment
changes
– Tends to drift but should always provide data
– Provides data at a very high rate
215. GPS/INS
Combined data provide excellent
position and attitude information
Equipment is more expensive than dead
reckoning equipment
Used for high-accuracy applications
216. GPS/Pseudolite
Pseudo-satellite
– Ground-based device
– Transmits a satellite-like signal
Used to provide signal (information) to
areas that can’t receive satellite signal
– Urban canyons
– mines
217. GPS/Pseudolite
Used to increase the number of signals
and the geometry of the signal senders
VDOP in particular can be improved
Signal needs to be ‘just right’ to avoid
the near-far problem
Also suffers because of inaccurate
clocks and potential multipath
Used in mining, precise aircraft landing
218. GPS/Cellular
Instances where it would be beneficial to
determine where a cell call originates
– 911 emergencies (1/3 come from cell phones)
FCC has made it mandatory to be able to
locate 911 calls within 125m
Can be done with time-difference of arrival
(TDOA) and/or angle of arrival
– Need GPS receivers at base stations
219. GPS/Cellular
Can also be done with GPS chipsets in
handset
– Need to insert chips into new phones
– Signal will be weak inside of buildings
Used in vehicle navigation
221. Applications
Fast growing especially since SA was
turned off
– That was the idea
Stand-alone GPS users can obtain 10-
20m accuracy
– Good enough for some kinds of navigation
Can also use carrier phase or DGPS for
higher accuracy
223. Global Navigation
Primary planned use when the system was
conceived
Both military and civilian applications
In the future, all planes, boats, etc. will have
GPS installed
Used for
– Route navigation
– Safety (collision avoidance)
– Automated vehicle navigation
224. Global Geodetic
Measurements
GPS can provide coordinates in a global
terrestrial reference frame
– Perfect for making large-scale observations
GPS has already made significant
contributions to the study of
– Plate tectonics/crustal deformation
– Earth orientation parameters
– Postglacial rebound/volcanic uplift
– Sea-level monitoring
225. Global Timing/Communcation
Because time is an implicit part of the signal,
GPS can provide a cheap and easy way to
determine accurate time
Most communication needs accurate
timing/frequency information
As communication needs increase, accurate
time/frequency will provide the ability to pack
more information into the same amount of
bandwidth
226. Regional Navigation
U.S. Coast Guard has set up network to
help approaching vessels reach the
harbor safely
– This will work in poor/no visibility scenarios
Used in conjunction with GIS to provide
regional information
Can be used for vehicle fleet
management
227. Regional Surveying
Monitoring fault lines can provide
information on stresses and strains
– Could lead to improved understanding of
earthquakes
Could possibly help in predicting earthquakes
Most complete networks in California
and Japan
Can also monitor subsidence
228. Local Navigation
Will aid in aircraft landings
Emergency vehicle management
– Make sure that vehicles are going where
they’re needed in the quickest possible way
Can help in finding alternate routes
Also can be used in farming, forestry,
and mining
229. Local Surveying
Probably the most common application
for people in this class
GPS can provide coordinates to varying
accuracies (depending on method of
observing)
Coordinates can be used in a variety of
surveying related activities (cadastral,
stakeout, etc.)
230. Attitude Determination
Theoretically possible to determine
attitude of aircraft using GPS
Could potentially be used for photo-
control
Not as accurate as using GPS/INS
231. Satellite Positions
GPS is now being used on-board
satellites to determine satellite positions
– TOPEX/Poseidon
– SPOT
– Even GPS itself
232. Installation of Control
Networks
GPS provides three dimensional coordinates
Excellent for setting high-accuracy networks
– GPS has made significant contributions to the
International Terrestrial Reference Frame (ITRF)
– HARN based on GPS observations
– Continuously Operating Reference Station (CORS)
occupied by GPS receivers
233. Other Applications
Utility industry
– Power poles, lines, mains, etc.
– Often used in conjunction with GIS
Forestry and Natural Resources
– Need to know topography and tree locations
Farming
– Want to know exactly where crops, chemicals are
in the field
234. Other Applications
Civil Engineering
– Road construction, Earth moving, structural
placement
– Monitoring structural deformation
Mining
– Drilling blast holes precisely
– Open pit mining equipment can be
controlled using inputs provided by GPS
235. Other Applications
Seismic Surveying (both land and
marine)
– Used for oil and gas exploration studies
Need to know position of transmitted acoustic
waves and receivers
Airborne mapping
– Need to determine position and attitude of
plane
Use GPS/INS combination
236. Other Applications
Seafloor Mapping
– Hydrographic mapping requires that the position
of the vessel is accurately known
Vehicle Navigation
– Automated techniques need the position of the
vehicle to by known
– Transit systems can use it to determine the
positions of vehicles
– Retail industry use it to determine truck fleet
locations
238. New Applications
Intelligent Vehicle/Highway Systems
(IVHS)
Intelligent Transportation Systems
Automated Construction Equipment
Time Determination/Time Transfer
Atmospheric Sensing
Aircraft Navigation and Landing
239. GPS Modernization
New Block IIF scheduled to be launched in
next few years (2007?)
– Ability to transmit data between satellites
– Autonomous navigation
Navigation accuracy maintained for six months (????)
Uplink jamming less of a concern
One upload per spacecraft per month (??)
Minimize ground tracking
Improved navigation
240. Augmented Signal Structure
SA is now off and likely to stay off
Additional L5 carrier frequency
– Ability to correct for ionospheric effects when using
carrier phase
– Modulated by a new civil code (similar to P-code)
– L2-L5 produces extra wide lane
– L1-L5 can be used as ionosphere free
Military Y-code replaced by split M-code
241. GPS Augmentation
Want to use GPS for aviation
– Reliability needs to be extremely good
– Want to augment GPS to provide additional
reliability and improve results
Local Area Augmentation Systems
(LAAS) will use pseudolites
– Should allow precision approach and
landing
Category II/III
242. GPS Augmentation
Can also use geostationary satellites
– Will have broadcast capability
– Transmit DGPS corrections and integrity
messages
Wide Area Augmentation System
(WAAS) will use Inmarsats to augment
GPS
– Operational sometime
243. GNSS
Global Navigation Satellite System (GNSS)
Integration of different satellite navigation
systems
– Already have capability of combining information
from GPS and GLONASS
– Also includes augmentation from other kinds of
satellites (like Inmarsat)
– Also include Galileo when launched
244. GNSS/LORAN-C
Long Range Radio Navigation (LORAN)
– Used mostly for maritime navigation
– Broadcast stations organized into ‘chains’
– Very similar to GPS
cannot provide vertical component
– Can be used to augment GPS
245. Hardware
In short, hardware will continue to get
better, cheaper, smaller
– Cost will drop if quantities increase in a
way that everyone has (at least) one GPS
receiver working in his/her life
– Resolution of wave will improve (<0.1%)
– More channels (for increased number of
observables)
More frequencies and more satellites
246. Software
In short, software will continue to get
more sophisticated and run faster
– Improved modeling or solution for
unknown parameters
– Better algorithms for solution
– Faster computers will allow more to be
done in the same amount of time
247. GPS Products
Data will continue to improve
– Centimeter level orbits will be available
– Centimeter level positioning will be possible
in real time
– Sub-centimeter positioning will be possible
by post-processing
250. GLONASS
Global Navigation System developed by
Russia
Nominally consists of 21 satellites plus 3
spares
8 satellites arranged in 3 orbital planes with
an inclination of 64.8º
Orbits are approximately circular with a
period of 11h 15m
251. GLONASS
Also transmits L1&L2 carriers, C/A & P
codes
– L1 is in 1602-1615.5 MHz band
To be shifted to (1598.0625-1604.25 MHz)
– L2 is in 1246-1256.5 MHz band
To be shifted to (1242.9365-1247.75 MHz)
– C/A code is 0.5Mps
– P Code is 5.11 Mbps
252. GLONASS
Carrier frequency depends on the satellite
– Each one is currently unique
After shift, each pair of satellites will be
assigned the same frequency
– Pairs on opposite sides of the Earth (antipodal)
Uses frequency channel rather than code to
identify satellite
253. GLONASS
The system is not as robust as
predicted
Economic crisis has severely hurt the
Russian space program
– Fewer satellites in orbit than expected
As little as 7 in May 2001
New class of satellites (GLONASS-M)
should be launched soon
254. GLONASS
Can be used in conjunction with GPS to
improve navigation/positioning
Need to account for 2 differences in reference
– Need to transform Earth Parameter System 1990
(PZ-90) to WGS 84
Can differ by up to 20 m
– Need to relate Russian time scale to GPS time
Can differ by 10s of μs
255. Beidou
Chinese regional satellite navigation
system
Consists of 2 satellites in geostationary
orbits
– Altitude of 36000 km
Used in land and marine transportation
Plans for next generation system
256. Galileo
Proposed and being planned by Europe
It will be controlled by civilians
Plans call for 30 medium Earth orbit
satellites
Distributed in 3 orbital planes
– Altitude of 23000 km
257. Galileo
Will provide 2 levels of service
– Basic (free-of-charge)
– Chargeable service
3 phases of development
– Definition phase (already completed)
– Development and validation phase
– Deployment phase
Scheduled to begin in 2006/7 timeframe
Service by 2008 (?)
258. Galileo
Because it is civilian operated, it will
have advantages in the marketplace
Already promising to provide a service
that will meet legal standards
– GPS can’t do this
If the lawyers are happy, the business
money is more likely into Galileo
products
259. WAAS
Wide Area Augmentation System (WAAS)
– Covers North America
– South America could be covered later
Utilizes GPS but augments it with additional
satellite information
– Use geostationary satellites
International Maritime Satellite (Inmarsat)
– Provides additional reliability and accuracy
Used for aircraft navigation
– Not necessarily for takeoff and landing
260. LAAS
Local Area Augmentation System (LAAS)
Utilizes GPS but augments it with pseudolite
information at critical locations
– Typically around airports but could be used in
other locations theoretically
Used for aircraft takeoff and landing
– Including category II/III
261. EGNOS
European Geostationary Navigation
Overlay System (EGNOS)
European version of WAAS
– Covers all of Europe and North Africa
– Could be extended to cover all of Africa
and Middle East
Will eventually be superceded by Galileo
262. MSAS
MTSAT Satellite-Based Augmentation
System (MSAS)
– Multi-functional Transport Satellite (MTSAT)
Japanese version of WAAS
– Covers parts of Asia and the Pacific