Äîêóìåíò âçÿò èç êýøà ïîèñêîâîé ìàøèíû. Àäðåñ îðèãèíàëüíîãî äîêóìåíòà : http://www.ipa.nw.ru/conference/wpltn2012/docs/27/1020%20WPLTN2012_Lim.pdf Äàòà èçìåíåíèÿ: Mon Oct 1 12:29:48 2012 Äàòà èíäåêñèðîâàíèÿ: Sun Feb 3 20:34:22 2013 Êîäèðîâêà: Ïîèñêîâûå ñëîâà: âíåøíèå ïëàíåòû

WPLTN-2012 Technical Workshop

Current Status and Plan of Korean SLR System for Space Geodesy and Space Debris

2012. 9. 27 Hyung-Chul Lim
Korea Astronomy and Space Science Institute


Outline

1 2 3 4 5 6

Overview of ARGO Project Introduction of ARGO-M and ARGO-F Current Status of ARGO-M Development Future Plan of Fundamental Station Future Plan of Laser Tracking System of Space Debris Summary

The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Overview of Korean SLR Project
A R GO
· Name of Korean SLR project · Accurate Ranging system for Geodetic Observation

Development Period
· 2008 - 2015 (8 years)

Final Goal
· One mobile system(40cm/10cm) : ARGO-M · One fixed system(1m) : ARGO-F

Objectives
· Space geodesy research and GEOSS/GGOS contribution by laser ranging for satellites with LRA · Precise obit determination(POD) through laser ranging measurement with mm level accuracy · Contribution to international SLR societies and ILRS network participation
The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Milestone of ARGO Project
ARGO
1st Stage
2008
SRR (0 8 . 0 9 )

2nd Stage
2011
CDR (1 1 . 0 3 ) SI (1 1 . 1 2 )

2009
SDR (0 9 . 0 5 )

2010
PDR (0 9 . 1 2 )

2012

2013

2014

2015

ARGO-M (Mobile)

Req. decision & analysis

SDR/PDR/CDR (Optics, Mount, Optoelectronics Operation system) Outsourcing (Laser)

Manu -facture

SI

T es t Operation

Normal operation
(Test Site)

Move to Sejong site (13.4) Normal Operation (13.05)

Test site construction

LHRS installation

Sejong site construction
SRR (1 2 . 1 2 ) SDR (1 3 . 0 9 ) PDR (1 4 . 0 3 ) CDR (1 4 . 0 9 ) SI (1 5 . 0 6 )

ARGO-F (Fixed)

Requirement decision & analysis

SDR/PDR/CDR Manu (Optics, Mount, Laser, -facture Optoelectronics, Operation system)

SI

T es t Operation

Site candidate surveying
ARGO-M Completed

Site decision & Station design Join ILRS Network

Site construction

LHRS Installation

Remark

ARGO-F Completed

The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Major Characteristics of ARGO-M
Tracking Capability
­ Capable of tracking satellites between 300km and 25,000km altitude
· STSAT-2(300x1,500km), KOMPSAT-5, GPS, Galileo

­ KHz laser ranging ­ Daylight and night tracking

Ranging Accuracy
­ Lageos : 10mm(SS), 5mm(NP) ­ Ground Target : 5mm(SS)

Operational Functions
­ ­ ­ ­ Controlled from the remote site Automated scheduling, planning and orbit prediction capability Automatic ranging based on schedule and aircraft detection(using radar) Automated diagnostic warning to monitoring system

Etc
­ Container and central locking dome (move by using a trailer)
The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Major Characteristics of ARGO-F
Tracking Capability
­ Capable of tracking satellites between 300km and 36,000km altitude
· STSAT-2(300x1,500km), KOMPSAT-5, GPS, GEO satellites

­ Daylight and night tracking ­ Satellite imaging using adaptive optics

Ranging Accuracy
­ Lageos : 4~6mm(SS), 1~2mm(NP) ­ Ground Target : 2~4mm(SS)

Operational Functions
­ Fully automatic remote operation

The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Comparisons between ARGO-M and ARGO-F
Item Parameter
Optical path Rx and Tx telescope Primary mirror F-ratio Telescope Transmit beam divergence Max slew rate Tracking & Pointing accuracy Type Detector Quantum efficiency Wavelength Pulse energy Laser Pulse width Repetition rate of Operation Beam diameter @ Tx telescope Etc Timing system Aircraft detection type

ARGO-M
Bistatic 40/10 cm 1.5 5 ~ 200 arcsec 20 deg/sec (Az) 10 deg/sec (El) < 5 arcsec C-SPAD 20% 532 nm 2.5mJ @2 kHz 50 ps 2 kHz 7.5 cm Event timer Radar

ARGO-F
Common Coude > 120 cm 3 ~ 25 arcsec 10 deg/sec (Az) 10 deg/sec (El) < 1 arcsec MCP-PMT or C-SPAD 532 nm > 2mJ @2 kHz 10 ~ 30 ps > 80 cm Event Timer -

The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Configuration of ARGO-M

Operation System

Telescope/Mount

Radar

Ground Target Las er
The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

Electronics

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External Image of ARGO-M

Test site at KASI HQ
The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Internal Structure of ARGO-M
Laser room Operation room Accessory room

-

Tracking mount Las er Optical table Ground target pillar

-

Electronics : Event timer, GPS and etc Tracking mount servo system Operation system Radar controller(LCU) Firewall and network system

- UPS - Power distribution unit - Surge protection device

The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Status of ARGO-M System Integration (OPS)
Design of Receiving Optics
Detecting Optics

Receving Optics

· Separate path(Tx/Rx telescope) to reduce back scattering - Aperture : 40cm Rx telescope & 10cm Tx telescope - FoV of Rx telescope : 5 arcmin - Reflectivity of primary and secondary mirror : >90% @532nm · Ir is - 3 h o le s a n d o n e b lo c k e d h o le - the spatial filters(day, night and twilight) and the sun shutter - controlled by the operation system for hole choice · Collimating Lens - controlled by the operation system for focusing of C-SPAD and camera
The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Status of ARGO-M System Integration (OPS)
Design of Detecting Optics

· Bandpass filter(F1) : 0.3nm for daytime tracking · Switching mirror(M3) : - change the beam path for daytime camera and C-SPAD - On : the daytime camera is activated - Off : C-SPAD and the nighttime camera are activated · C-SPAD : Peso Consulting(Austria) · Daytime camera : PCO1600 - Resolution pixel : 1600 x 1200 - Data interface : IEEE1394a, camera link, GigE Vision · Nighttime camera : Watec WAT-120N - CCD size : 0.5 inch

The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Status of ARGO-M System Integration (LAS)
RGL-532 Model (Photonics Industry, USA)
­ Nd:YAG(laser material) and 532nm wavelength ­ Pulse energy : 2.5mJ@2KHz ­ Pulse width : 30ps ­ Beam diameter : 1.9mm at the exit of laser head, · It is expanded to 25mm on the optical table using two beam expanders ­ Head size : 600 â 192 â 127mm ­ M2 : < 1.2 Laser head

Laser controller

Rising Block Pier Optical table

Laser chiller

The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Status of ARGO-M System Integration (LHRS)
LHRS (Laser Hazard Reduction System)
­ Provides a means of detecting aircraft before they intersect a transmitted laser beam ­ Laser beam is disable when aircraft is detected ­ Made by Honeywell(USA)

Specification
­ ­ ­ ­ Max. detection range : 40 km Beamwidth : 2.8 deg Position resolution : 0.09 deg for Az/El Max. slew rate : 15 deg/sec for Az/El

Current Status
­ System installation and test : 2012.01 ­ Helicopter and fighter detection test : 2012.06

The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Optical Coude Path & Ground Target of ARGO-M
3x : transmitting telescope

M4 M5

M2

M3

M1

M0 15x : two beam expanders

The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Current Status of ARGO-M Development
· Satellite optical tracking experiment for tracking performance verification · Laser ranging experiment of ground target · Waiting for an approval from Korean government to fire laser into the sky Sirius Beacon-C Optical tracking Experiment
Tracking & pointing accuracy : < 5 arcsec

S ta r

Accuracy < 5mm RMS GT laser ranging Experiment

The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Future Plan ­ Fundamental Station
Composition
­ VLBI, GNSS : NGII (National Geographic Information Institute) ­ SLR, DORISS : KASI (Korea Astronomy & Space Science Institute)

Location
­ S e j o n g c i ty ­ ARGO-M will be moved to Sejong site in March 2013

Normal operation : April 2013

Sejong

The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Future Plan ­ Laser Tracking System of Space Debris (1)

Earth Orbiting Space Debris
­ Object > 10 cm : 15,000 ­ Object > 1 cm : 350,000

Damage from Space Debris Collision
­ 5 ~ 15 mm : will damage or impair a spacecraft ­ > 15 mm : will destroy a spacecraft

Korean Satellites
­ Several satellites in LEO (Low Earth Orbit) ­ In the face of collision risk against space debris

Laser tracking system for space debris monitoring
The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Future Plan ­ Laser Tracking System of Space Debris (2)

Development Strategies
­ Development period : 2016 ~ 2018 (3 years) ­ ARGO-F(Fixed SLR system) upgrade
· New high power laser system installation · Operation system modification

Laser Tracking System of Space Debris
­ Performance
· Capable of tracking space debris > 10 cm · Tracking coverage : < 1,000 km ­ Tracking accuracy : < 0.2 arcsec ­ Las er S pec . · > 20 Hz repetition rate, > 5 J/pulse energy · < 5 ns pulse width, M2 < 1.5

The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Summary
Three SLR Systems
­ ARGO-M for space geodesy ­ ARGO-F and laser tracking system of space debris for space surveillance

ARGO-M
­ Develop period : 2008 ~ 2012 ­ System integration & optical alignment was finished ­ It will be moved to Sejong site in March 2013 for the fundamental station

ARGO-F
­ Development period : 2012 ~ 2015 ­ Capable of tracking satellites up to geostationary orbits ­ S a te l l i te i m a g i n g u s i n g a d a p ti v e o p ti c s

Laser tracking system of space debris
­ Development period : 2016 ~ 2018 ­ Capable of tracking space debris > 10 cm within 1,000 km altitude ­ ARGO-F upgrade
The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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Thanks for your attention !!!

The data contained in this document, without the permission of KASI, shall not be used, duplicated or disclosed, in whole or in part, for any purpose other than ARGO development.

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