Week3 Satellites

Satellite Positioning TechniquesSatellite Positioning Techniques

Prof. Dr. Muhammed ŞAHİN

http://olcme.ins.itu.edu.trhttp://atlas.cc.itu.edu.tr/~sahin


STARLETTE (French)Launch date: 06-Feb-75 Satellite Number: 7501001 Area: .045 Weight: 47.25 kg Shape: sphere Diameter: 36 cm Perigee Rate: 3.296 Perigee Height: 812.19 km Apogee Height: 1114.8 km Eccentricity: 0.0206 Inclination: 49.83 degree Semi-major axis: 7331 km Comment: contains 60 laser corner reflectors


LAGEOS-1, Laser GEOdynamic Satellite (USA)Launch date: 04-May-76 Satellite Number: 7603901 Area: .2827 Weight: 411 kg Shape: sphere Diameter: 60 cm Perigee Rate: -.214 Perigee Height: 5834.25 km Apogee Height: 5944.82 km Eccentricity: 0.0045 Inclination: 109.84 degree Semi-major axis: 12273 km Comment: contains 426 retroreflectors each 3.8 cm in

diameter


ETALON-1 (Russian)Launch date: 10-Jan-89 Satellite Number: 8900103 Area: Weight: 1415 kg Shape: sphere Diameter: 129.4 cm Perigee Rate: Perigee Height: 19400 km Apogee Height: 19400 km Eccentricity: Inclination: 64.8 degree Semi-major axis: 25478 km Comment: Russian satellite with 2000 corner cube

reflectors


ETALON-2 (Russian)Launch date: 31-May-89 Satellite Number: 8903903 Area: Weight: 1415 kg Shape: sphere Diameter: 129.4 cm Perigee Rate: Perigee Height: Apogee Height: Eccentricity: Inclination: Semi-major axis: Comment: Russian satellite with 2000 corner cube

reflectors


TOPEX/POSEIDONLaunch date: 10-Aug-92 Satellite Number: 9205201 Area: Weight: Shape: see figure above Diameter: Perigee Rate: Perigee Height: ca. 1300 km Apogee Height: ca. 1300 km Eccentricity: Inclination: 66 degree Semi-major axis: Comment:


LAGEOS-2, Laser GEOdynamic Satellite (USA-Italy)Launch date: -92 Satellite Number: 9207002 Area: Weight: 405 kg Shape: sphere Diameter: 60 cm Perigee Rate: Perigee Height: ca. 5900 km Apogee Height: Eccentricity: Inclination: 52 degree Semi-major axis: 12273 km Comment: contains 426 retroreflectors each 3.8 cm in

diameter


GPS-35Launch date: 1993 Satellite Number: 9305401 Area: Weight: Shape: Diameter: Perigee Rate: Orbit Height: 20200 km Perigee Height: Apogee Height: Eccentricity: Inclination: 55 degrees Semi-major axis: Comment: GPS-35 and GPS-36 contain also

retroreflectors for SLR measurements


GPS-36Launch date: 1994 Satellite Number: 9401601 Area: Weight: Shape: Diameter: Perigee Rate: Orbit Height: 20200 km Perigee Height: Apogee Height: Eccentricity: Inclination: 55 degrees Semi-major axis: Comment: GPS-35 and GPS-36 contain also

retroreflectors for SLR measurements


GLONASS-49Launch date: set into orbit since 1982 Satellite Number: Area: Weight: Shape: Diameter: Perigee Rate: Perigee Height: 19 100 km Apogee Height: 19 100 km Eccentricity: roughly circular Inclination: 64.8 degrees Semi-major axis: 25 440 km Comment: The space segment of GLONASS is formed by 24

satellites located on three orbital planes. Each satellite is identified by its slot number, which defines the orbital plane (1-8, 9-16, 17-24) and the location within the plane. The three orbital planes are separated 120 degrees, and the satellites within the the same orbital plane by 45 degrees.


ERS-1 (ESA Remote Sensing Satellite)Launch date: 17-Jul-91 Satellite Number: 9105001 Area: Weight: 2300 kg Shape: see image above Diameter: Payload - 2m x 2m x 3m, solar array - 12m 2.4m Perigee Rate: Perigee Height: ca. 800 km Apogee Height: ca. 800 km Eccentricity: Inclination: 98.5 degree Semi-major axis: 7153.138, 7159.496, 7147.191 km for

3, 35 and 168 days repeat cycles Comment:


ERS-1


GFZ-1 (German)

Shape: spherical Mass: 20 kg Diameter: 200 mm Life time: 3 years Planned altitude: 350 km Launch: from Russian space station MIR Orbit: low spherical orbitwith high inclination


TiPS/ Tether Physics and Survivability MissionLaunch date: late June 1996 Satellite Number: 9602901 TiPS, 9602902 TiPS-Norton, 9602903 TiPS-Ralph Area: Weight: Shape: Diameter: Perigee Rate: Altitude: 1022 km Eccentricity: 0.000 Inclination: 63,4 ° Semi-major axis:

Comment: The Tethered Satellite called TiPS is a tether physics experiment consisting of two end masses connected by a 4 km non-conducting tether. TiPS contains single retroreflectors per end mass face, 18 retroreflectors per end mass, and coated retroreflectors to reject 1064 nm on one end mass


ADEOS/ MIDORI (GREEN) /Advanced Environmental Observation Satellite

Launch date: August 17, 1996 Satellite Number: 9604601 Area: Weight: Shape: Diameter: Perigee Rate: Perigee Height: Apogee Height: Eccentricity: Inclination: 98.6 degree Semi-major axis: 7167 km (altitude 797 km)


BEACON-C/ BE-B /BEACON EXPLORER-C

Launch date: April 29, 1965 (by a four-stage Scout Rocket) Satellite Number: 6503201 Area: Weight: 32 kg Shape: Octogonal prism with truncated octogonal pyramids at ends. Four panels, 46 cm in diameter and 25 cm high, carrying solar cells extended radially from prism 122 cm x 25 cm, each with 46 cm x 25 cm appendage. Diameter: Perigee Rate: Perigee Height: 940 km Apogee Height: 1300 km Eccentricity: Inclination: 41.2 ° Semi-major axis: Comment: It is magnetically stabilized and equipped with 160 corner cube reflectors distributed in pyramidal shape on the front part of the satellite body.

Satellite Positioning TechniquesSatellite Positioning TechniquesDIADEME-1 / D-1C / -

Satellite name/other name/full name:Launch date: February 08, 1967 (by a DIAMANT Rocket from

CNES Space Center in Hammaguir/Algeria) Satellite Number: 6701101 Area: Weight: 23 kg Shape: Cylindrical body covered by 2 flattened truncated cones, roughly 50 cm in diameter, 20 cm high. Four solar panels, 50 cm x 20 cm, about 40 ° inclined from the cylinder axis Diameter: Perigee Rate: Perigee Height: 550 km (at launch 570 km) Apogee Height: 1080 km (at launch 1350 km) Eccentricity: Inclination: 40 ° Semi-major axis: Comment: The satellite is magnetically stabilized in its quite eccentric orbit. It carries 144 corner cube reflectors located both on the satellite body at nadir and at the base of each of the four solar arrays.

Satellite Positioning TechniquesSatellite Positioning TechniquesDIADEME-2 / D-1D / -

Launch date: February 15, 1967 (by a DIAMANT Rocket from the CNES Space Center in Hammaguir/Algeria) Satellite Number: 6701401 Area: Weight: 23 kg Shape: Cylindrical body covered by 2 flattened truncated cones, roughly 50 cm in diameter, 20 cm high. Four solar panels, 50 cm x 20 cm, about 40 ° inclined from the cylinder axis. Diameter: Perigee Rate: Perigee Height: 590 km (at launch 590 km) Apogee Height: 1730 km (at launch 1880 km) Eccentricity: Inclination: 39.5 ° Semi-major axis: Comment: The satellite is magnetically stabilized in its quite eccentric orbit. It carries 144 corner cube reflectors located both on the satellite body at nadir and at the base of each of the four solar arrays.

Satellite Positioning TechniquesSatellite Positioning TechniquesGFO-1/ - / GEOSAT Follow-On-1

Launch date: October 30, 1996 (Taurus Launch Vehicle) Satellite Number: Area: Weight: approximately 300 kg Shape: Diameter: Perigee Rate: Altitude: 800 km Eccentricity: 0.001 Inclination: 108 ° Semi-major axis: Comment: Sensors on board include

Radar Altimeter - single frequency (13,5 GHz) with 3.5 cm heightprecision

Water Vapor Radiometer - Dual frequency (22 and 37 GHz) nadir-

looking with a path correction accuracy of 1.9 cm rms GPS Receivers - redundant receivers allow POD with rms

accuracy in the radial component of 10 cm on wavelength less

than 40000 km Doppler Beacon - GEOSAT performance-stable oscillators and Doppler beacons with 1,8 cm rms radial orbit error SLR Retroreflector Array - Hemispherical array of 9 cube corner

retroreflectors with array accuracy of 1 cm


WPLS/ - / Western Pacific Laser Tracking Network Satellite

Launch date: First quarter 1997 (Launch Vehicle: RESURS-01 #4) Satellite Number: Area: Weight: 23,5 kg Shape: Diameter: Perigee Rate: Altitude: 835 km Eccentricity: circular Inclination: 98 °, Sun-synchronus Semi-major axis: Comment: Features

Single cube response - only 0,7 corner cubes will reflect on any shot, on average Eyesafe - Response optimized for 1,54 micron wavelength, to provide

for fully eyesafe ranging at any power cm correction - New process developed to obtain the center-of-mass correction with 0,5 mm accuracy Fizeau - Corner cube design and material assume the Fizeau Effect

which, if real, will decrease return signal levels dramatically at 532

nm wavelength


AJISAI (Japanese Experimental Geodetic Satellite)

Launch date: August 12, 1986Satellite Number: Area: Weight: 685 kg Shape: Spherical Diameter: Perigee Rate: Altitude: 1500 km Eccentricity: 0.0006Inclination: 50 ° Semi-major axis: Comment: covers 1416 laser reflectors and 318 solar

reflectors


CHAMP (A CHAllenging Mini-Satellite Payload)

Dual-frequency GPS receiverThree-axes accelerometerMagnetometer instrument packageDigital ion drift meterRetroreflector array


CHAMP (A CHAllenging Mini-Satellite Payload)

Sponsor: GFZ (Germany)

Expected Life: 5 years

Primary Applications: geodesy

Primary SLR Application:

precision orbit determination and geodesy

COSPAR ID: 0003902

SIC Code: 8002

NORAD SSC Code: 26405

Launch Date: July 15, 2000

NP Bin Size 5 seconds

RRA Diameter: 5 cm

RRA Shape: rectangular

Reflectors: 4 corner cubes

Orbit: circular, near polar

Inclination: 87.27 degrees

Eccentricity: 0.00396

Perigee: 474 km

Period: 94 minutes

Weight: 400 kg

Week3 Satellites

Documents

Transcript of Week3 Satellites