orbit and constellation design
DESCRIPTION
Orbit and Constellation Design. Dr. Andrew Ketsdever MAE 5595 Lesson 6. Outline. Orbit Design Orbit Selection Orbit Design Process Δ V Budget Launch Earth Coverage Constellation Design Basic Formation Stationkeeping Collision Avoidance. Orbit Design. - PowerPoint PPT PresentationTRANSCRIPT
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Orbit and Constellation Design
Dr. Andrew Ketsdever
MAE 5595
Lesson 6
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Outline
• Orbit Design– Orbit Selection– Orbit Design Process– ΔV Budget– Launch
• Earth Coverage• Constellation Design
– Basic Formation– Stationkeeping– Collision Avoidance
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Orbit Design
• What orbit should the satellite be put in?– Mission objectives– Cost– Available launch vehicles– Operational requirements
• Orbit Design Process– 11 Step Process– Wide variety of mission types which will be
unique in the orbit selection process
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Orbit Design Process
• Step 1: Establish Orbit Types– Earth referenced orbits
• GEO, LEO
– Space referenced orbits• Lagrange points, planetary
– Transfer orbit• GTO, Interplanetary
– Parking orbit• Temporary orbit for satellite operational checks,
EOL
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Orbit Design Process
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Orbit Design Process
• Step 2: Establish Orbit-Related Mission Requirements– Altitude
• Resolution Lower altitude is better• Swath width Higher altitude is better
– Inclination • Ground station coverage
– Other orbital elements• J2 effects on RAAN and AoP
– Lifetime– Survivability (ambient environment)
• Must be able to survive the entire orbital profile (e.g. transit through Van Allen Radiation Belts)
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Orbit Design Process
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Orbit Design Process
• Step 3: Assess Specialized Orbits– Typically set some orbital parameters (e.g.
semi-major axis, inclination)• Geosynchronous, Geostationary• Semi-synchronous• Sun synchronous• Molniya• Lagrange points
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GEO
• 24 hr period – co-rotation with Earth• Solar/Lunar pertubations
– N/S drift– Pointing requirements
• J2 perturbations– E/W drift– 10% of ΔV required for N/S– Important due to neighboring slots
• Early 1990’s– 50% of launches to GEO
• Overcrowding is a constant issue
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Sun Synchronous Orbit
• J2 causes orbit to rotate in inertial space– Rate is equal to average rate of Earth’s
rotation around the sun– Position of Sun relative to orbital plane
remains relatively constant– Sun Synchronous orbits can be achieved
around other central bodies• Usually near 90º inclinations
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Molniya Orbit
• Highly elliptical orbit with i=63.4º (zero rate of perigee rotation)
• Can have a large (up to 99%) fraction of the orbit period between
• Any orbital period can be obtained change apogee altitude
• Satellite constellations in these orbits can provide very efficient coverage of high (or low) latitudes
27090
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Orbit Design Process• Step 4: Select Single Satellite or Constellation
Architecture– Single satellite
• Advantages– Reduced overhead (single system)– More capability per copy
• Disadvantages– Limited coverage (potential)– Reliability– High cost
– Constellation• Advantages
– Enhanced coverage– Survivability– System simplicity
• Disadvantages– Higher operational and launch costs (potential)– Limited capability
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Orbit Design Process
• Step 5: Mission Orbit Design Trades– How do orbital parameters affect the mission
requirements?– How are satellites in a constellation phased
throughout the orbital plane(s)?– Constellations
• Typically at the same altitude and inclination• Drift characteristics
– At different altitudes and inclinations, satellites in a constellation will drift apart
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Orbit Design Process
• Step 6: Evaluate Constellation Growth and Replenishment or Single-Satellite Replacement Strategy– Constellation
• Growth– Time consuming (several months to years)
– Operational without full constellation
• Graceful degradation (reduced level of service)• Replenishment
– Single Satellite• Single point failure • Degradation• Replacement
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Orbit Design Process
• Step 7: Assess Retrieval or Disposal Options– Retrieval is typically not an option (Shuttle)
• On-orbit servicing
– Disposal (De-orbit) may be a requirement soon
• Orbital debris• Limited useful operational orbits• Re-enter (LEO)• Disposal orbit (GEO)
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Orbit Design Process
• Step 8: Create a ΔV Budget– Orbital maneuvers
• Launch Vehicle may not get you directly to the desired orbit
• Transfer orbit ΔV– Orbit size– Orbit inclination– RAAN
• Stationkeeping• Rephasing• De-orbit
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The ΔV Budget
• Maneuvers requiring ΔV– Orbital transfer– Plane change– Drag make-up– Attitude control– Stationkeeping– Rephasing– Rendezvous– De-Orbit
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The ΔV Budget• Start with the ideal rocket equation
• Mpropellant for a particular burn is the difference in initial mass and final mass
• High Isp is desirable, but it must be weighed versus the “cost” of the higher value (e.g. higher power, higher dry mass, etc.)
• Investigate concepts that reduce ΔV requirements– Aerobraking– Solar Sails– Tethers
f
iosp M
MgIV ln
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Environment Interactions
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Orbit Design Process• Step 9: Assess Launch and Orbit Transfer
Cost– Availability of LV– Cost– Mass to particular orbit
= $$$
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Orbit Design Process
• Step 10 and 11: Document and Iterate
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Earth Coverage
• Earth coverage refers to the part of the Earth that a spacecraft instrument can “see”
• Field of View: Actual area the instrument can “see” at any moment
• Access Area: Total area on the ground that could potentially be seen at any moment.
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Footprint
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Hellas-Sat 2
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Footprint• ASTRIUM Eurostar 2000+ Platform• Payload
– 30 x 36 MHz transponders, onboard – 8 x 36 MHz redundant
• 12 on fixed beam F1, 6 on fixed beam F2, up to 12 on beam S1 and 6 on beam S2.
• Footprints– Fixed over Europe– Steerable over Southern Africa, Middle
East, Indian subcontinent, South East• Frequencies
– Downlink Ku-Band• 10.95-11.20 GHz (F2)• 11.45-11.70 GHz (S2)• 12.50-12.75 GHz (F1, S1)
– Uplink Ku-Band• 13.75-14.50 GHz
• Services– Audio/Video Broadcasts– Telephone Relay– Internet Access– Business Teleconferencing
F1
S1
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Footprint• Geostationary Operational
Environmental Satellites (GOES)– GOES 8: Decommissioned– GOES 9: Operational (Japan)– GOES 10: Operational, Standby,
Drifting– GOES 11: Operational, West– GOES 12: Operational, East
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Sirius Radio
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Earth Coverage
• Earth Coverage Figures of Merit– Percent Coverage: Number of times that a point is
covered by one or more satellites divided by a time period
– Maximum Coverage Gap: Longest of the coverage gaps (no coverage) encountered for a particular point
– Mean Coverage Gap: Average of the coverage gaps (no coverage) for a particular point
– Mean Response Time: Average time from a random request to observe a particular point
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Earth Coverage
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A Different Kind of Gap?• A U.S. Government Accountability Office report on a new polar-
orbiting environmental satellite program has concluded that cost overruns and procedural difficulties could create a gap in important national weather data derived from the satellites that could last at least three years, beginning in late 2007.
• Polar-orbiting environmental satellites provide data and images used by weather forecasters, climatologists and the U.S. military to map and monitor changes in weather, climate, the oceans and the environment. The satellites are critical to long-term weather prediction, including advance forecasts of hurricane paths and intensity.
• The current U.S. program comprises two satellite systems - one operated by the National Oceanic and Atmospheric Administration, and one by the Department of Defense - as well as supporting ground stations and four central data processing centers. The new program, called the National Polar-orbiting Operational Environmental Satellite System, or NPOESS, is supposed to replace the two systems with a single, state-of-the-art environment-monitoring satellite network.
• NPOESS - to be managed jointly by NOAA, DOD and NASA - will be critical to maintaining the continual data required for weather-forecasting and global climate monitoring though 2020. The problem is the last NOAA polar-orbiting satellite in the existing program is scheduled to be launched in late 2007, while the first NPOESS launch will not be until at least late 2010. If the earlier satellite fails, its data capability would be difficult, if not impossible, to replace during the interim.
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Swath Width
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Earth Coverage
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Earth Coverage
(-) for subscript 1, (+) for subscript 2
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Earth Coverage
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Constellation Design
• Constellation: Set of satellites distributed over space intended to work together to achieve a common objective
• Satellites that are in close proximity are called clusters or formations
• Constellation architectures have been fueled by recent development of small, low cost satellites
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Constellation Design
• Coverage– Principle performance parameter– Minimize gap times for regions of
interest• Entire Earth• North America• Colorado• US Air Force Academy
• Number of Satellites– Principle cost parameter– Achieve desired coverage with the
minimum satellites• Example
– GPS requires continuous coverage of the entire world by a minimum of four non-coplanar satellites
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Constellation Design
• Number of Orbital Planes– Can be a driver for coverage– Satellites spread out (typically
evenly) throughout plane– Plane changes require large
amounts of propellant– Meet requirements with the
minimum number of orbital planes
– Rephasing can be accomplished with less propellant in a single plane
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Constellation Design
• Constellation Build-Up, Replenishment, and End of Life– Typically a constellation is in a
“less-than-complete” form– Build-up can be a several year
process with multiple launches– Re-Configuration of the
constellation is necessary when satellites fail
– Dead satellites need to be removed from the active constellation
• Collision avoidance
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GlobalStar• LEO Cellular Phone
Constellation• 48 satellites in 8 planes• h=1414km• i=52º• Latitude coverage: 70º• 7 Boeing Delta II Launches• 6 Russian Soyuz Launches• Each launch vehicle
carried 4 satellites• On-orbit spares• Two additional Deltas were
purchased to ferry spares to the constellation
General Characteristics:Total weight - 450kg,Number of Spot beams - 16Power - 1100WLifetime - 7.5 years
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Constellation Coverage
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Street of Coverage
Swath 2street where coverage will be continuous
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Street of Coverage
• Adjacent Planes
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Iridium (Atomic No=77)
66 active satellites, 6 planes
Reduced to 6 orbital planes (from a proposed 7) byIncreasing the orbital altitude slightly.
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Iridium Satellite Constellation
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Constellation Design
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The Walker Constellation
• Symmetric• T = total number of satellites• S satellites evenly distributed in each of P orbital
planes• Ascending Nodes of the P orbital planes are
uniformly distributed about the equator• Within each plane, the S satellites are uniformly
distributed in the orbit• Relative phase between satellites in adjacent
planes to avoid collisions
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Stationkeeping
• Approaches to perturbations– Leave perturbation uncompensated– Control the perturbing force the same for all satellites
in the constellation– Negate the perturbing force
• Example: h=700 km, i=30º and 70º– Node rotation rate of 2.62º /day and 6.63º /day– Relative plane movement of 4º /day– Makes construction of long term constellation difficult
• Coverage requirements• Active rephasing may be necessary
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Collision Avoidance
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Microsatellite Constellations