on orbit calibration of laser beam intensity · serc will build and launch two test satellites by...
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Ben Greene 33rd AIAA International Communications Satellite Systems Conference (ICSSC).
Gold Coast
7-10 September 2015
Preserving Space for our Future
ON ORBIT CALIBRATION OF LASER BEAM INTENSITY
Ben Greene
20th International Workshop on Laser Ranging
Potsdam 13 October 2016
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SERC:
Automated, high-precision laser tracking of space debris has been operationally deployed in Australia for many years
Leverage accurate debris catalogue to improve safety of navigation in space, and ultimately to safely move space debris using ground-based lasers
Integrate best-available global technologies in an international collaboration
Initial R&D budget US$50M plus infrastructure budget US$60M
2018 expansion will double R&D and infrastructure programs
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SERC Founding Participants
SERC members represent government, industry and universities across several countries [Japan, USA, Australia]. Expansion to more countries will occur in 2017.
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Collisions in Space
Algorithms propagate all catalogue objects in an all-on-all conjunction analysis
Runs every hour for the entire catalogue to produce 7 days look-ahead for collisions
Catalogue updated continuously with new tracking data
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Conjunction Statistics
5km is typical for NORAD position uncertainties
500m was the predicted miss distance for Iridium/Cosmos crash
Accurate orbits [<100m error] resolve almost all potential collisions, and manoeuvre can then protect all satellites
However, debris manoeuvre and debris removal remain key objectives
Closest Approach Number of Occurrences
<5km 42,000 per week
<1km 3,000 per week
<500m 700 per week
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Typical EO Sensors
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7 EOS Space Research Centre at Mount Stromlo, Canberra, Australia
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EOS Space Debris Site in WA
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Manoeuver by CW Laser Radiation
This is an inherently gentle and slow process
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Avoidance vs Removal
• SERC is fully funded to demonstrate the feasibility of reducing the rate at which collisions occur by temporarily relocating debris using non-threatening CW lasers
• CW lasers of 20-100 kW produce radiation on orbit similar to solar radiation, and apply radiation pressure
• Laser engagement may need to be repeated a number of times for each object
• It’s a temporary solution, but it buys time while more permanent solutions are developed and implemented.
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How much manoeuvre is enough?
If we assume we act in the final 48 hours before a predicted collision
• SERC special catalogue has the positions of each object for 48 hours to 80 m uncertainty.
• We need to move one object >160 m to be sure of avoiding a collision
• This means we need an average velocity change of 1 mm/sec over 48 hours
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Debris velocity change: worked example
Parameter Value
Orbit Altitude 500 km
Debris Dimension 20 cm
Debris Mass 0.2 kg
Beam Director Diameter 1.8 m
Laser Power 20 kW
Laser Beam Quality (M2) 1.2
Delivered Strehl 0.3
A/M=0.2
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Velocity Change
Allowing for photon flux, range, along track vector and dwell time vs ZD
Integrate under the curve and divide by mass gives Δv =0.16 mm/s or 6 passes for 1mm/s change
SERC baseline configuration provides marginal performance but affordable phenomenology verification is needed
0 20 40 60 800
0.1
0.2
0.3
0.4
Force vs ZD
Zenith distance (deg)
For
ce (
uN)
“Artificial” debris is required to achieve proper characterization of the phenomenology and fully assess the operational utility [affordability]
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SERC will build and launch TWO test satellites by 2020 to calibrate laser beam properties in space. Satellites will have corner cubes, laser power measurement, precision navigation, and radiation sails. Use by collaborating agencies will be permitted. SERC will release AO in 2017 for use of these satellites by collaborators
Test Satellites
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Project Timeline
1. 2016: Precision debris tracking and orbit propagation
2. 2017: AO system and 20 kW laser operational
3. 2018: Launch test satellite #1 for beam monitoring on orbit
4. 2019: Launch test satellite #2 for thrust measurement
5. 2020: Debris manoeuvre experiments
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Summary
1. Demonstrate by 2020 that photon pressure can be used
to modify the orbit of smaller debris objects
2. Requires:
Precision tracking
Accurate orbit propagation
Energy Concentration (beam director & AO).
3. Ca. 50% of small [<10kg] objects can be moved
4. Reduces collision risk and buys time for debris removal
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