AmateuRadioMalaysia

Saturday, December 10, 2005

Do you know Series - 10

Do you know your Malaysian Satellites?

TIUNGSAT-1 (MO-46)

Uplinks
145.850,145.925 MHz 9600 baud FSK
Downlink
437.325 MHz 38.4K Baud FSK

Broadcast Callsign
MYSAT3-11
BBS
MYSAT3-12
NUP
MYSAT3-10

Launched
26 September 2000Status: Operational
TiungSat-1 is Malaysia's first micro-satellite and in addition to commercial land and weather imaging payloads offers FM and FSK amateur radio communication.





















Info from http://www.amsat.org web page


Objectives

The TiungSAT-1 microsatellite mission carries the following payloads:
Multi-Spectral Earth Imaging System (MSEIS)
The MSEIS provides high quality approximately 80-metre ground sampling resolution multi-spectral images in 3 bands (Near Infra-Red, Green and Red) using 1024x1024 pixel 2-dimensional CCD array detector digitised to 8 bits radiometric resolution (256 levels). The image swath width is 80 km and each imager can collect 4 images contiguously along the flight path.
Meteorological Earth Imaging System (MEIS)
The MEIS provides high quality meteorological wide-field images (Near Infra-Red) with 1.2 km ground sampling using 1024x1024 pixel 2-dimensional CCD array detectors digitised to 8 bits radimetric resolution (256 levels). The images swath width is 1200 km and the imager can collect images contiguously along the flight path.
Digital Store-&-Forward Communications (S&F)
S&F communications provides global, frequency-agile, communications for any form of digitised data: e-mail, voice-mail, scientific data exchange, fax, images, or even Internet mail for remote regions. The low cost and direct access offered by theTiungSAT-1 microsatellite in orbit also makes it ideal for use by scientists, engineers and students based in institutes, universities and even schools throughout the world.
Digital Signal Processing Experiment (DSPE)
The DSPE consists of TM320C31 low power Digital Signal Processor suitable for special or general purpose signal processing tasks on LEO satellites.

Payload Information

Spacecraft
...........................
Spacecraft Mass 50 kg (platform: 35 kg; payload: 15 kg)
Spacecraft Envelope 690 x 360 x 360 mm
Communication Systems Supporting data rates from 9.6 kbps to 76.8 kbps at VHF/UHF
On-board Computers Primary 186EX OBC (16 Mbytes of SRAM EDAC). Secondary 386EX OBC with 387 co-processor (128 Mbytes of SRAM). They both use an in-orbit reloadable on-board real-time, multi-tasking operating system with high level, user friendly (C-language) application software.
On-board Data Handling Via Controller Area Network (CAN) between platform and payloads
Attitude Determination Using 3-axis vector magnetometer (+/- 60,000 nT, 30 nT resolution) and 2-dimensional sun angle sensors provides attitude restitution to within 0.5 degree.
Attitude Control Earth pointing to within 3 degrees using 6-metre boom gravity-gradient stabilisation and advanced on-board Kalman filter to control the magnetorquer.
Orbit Determination Using a 12-channel GPS receiver provides on-board positioning within 100m and autonomous Keplerian orbit determination.
Power Generated from high-efficiency 35W GaAs solar arrays provides 50W peak and 20W continuous orbit-average spacecraft power, which is stored using 7Ah NiCd batteries.
Science Payload
Cosmic-Ray Energy Deposition Experiment (CEDEX) The purpose of CEDEX is to characterise the TiungSAT-1 (Sun-Synchronous) orbit radiation environment in terms of the observed particle Linear Energy Transfer (LET) spectrum at the spacecraft. The data returned by the instrument are directly comparable to that obtained by similar instruments such as U.K.'s Cosmic-ray Effects and Dosimetry (CREDO) and Cosmic-Ray Effect and Activation Monitor (CREAM) experiments which have flown on-board Corcorde, the U.S. Space-Shuttle and UoSAT-3, and the Cosmic-Ray Experiment (CRE) flown on KITSAT-1 and PoSAT-1. These data are also be of great use in evaluating the radiation performance of the electronics used in the TiungSAT-1 satellite.
The primary sensor consists of a 30mm x 30mm PIN diode detector (900 mm2 active area), 300 microns in depth, housed in a separate screened aluminium unit mounted on the CEDEX module box. This is connected to a charge amplifier and a pulse-shaping circuit which, in turn, are connected to an event-driven, hardware-logic controlled pulse-height multi-channel analyser. The experiment is controlled autonomously by a CAN-microcontroller with its own data-storage RAM and built-in data-compression software. This sends data to an internal CAN-controller which formats and sends them on to the primary OBC via the spacecraft's CAN bus.
Ionespheric Space Science An advanced 12-channel GPS receiver on-board the TiungSAT-1 microsatellite will be used primarily for determining the orbit and position of the microsatellite to within 100 metres and also to provide precise and accurate timing for spacecraft timing for spacecraft functions and payloads.
By positioning two GPS antennas on-board TiungSAT-1, the position of the microsatellite can be determined from GPS satellites in good view and compared with signals received from other GPS satellites as they dip down through the Earth's ionosphere. The timing delays and phase changes due to the diffraction that result can yield information on the electron density profile of the ionosphere and its fluctuations.

Communications

The RF communications subsystem enables the ground stations to communicate both telemetry, telecommand and payload data to and from the space craft in orbit. It consists of UHF (435 to 438 MHz) downlink transmitters with modulator and VHF (144 to 146 MHz) uplink receivers with demodulator. The exact operating frequency of the uplink and/or the downlink can be selected under ground or on-board control, within a limited range. Communications for telemetry, telecommand and payload data are provided using error-protected digital packet communications at VHF and UHF at rates from 9.6 and 38.4 kbps, and experimentally at 76.8 kbps.
The downlink system consists of two transmitters, primary and one cold standby (secondary). One transmitter has a variable power output of up to 10 W, the second transmitter has a fixed power level of 1.5W measured at the transmitter output when the battery is at maximum charge and operated at the expected operating temperature.
The uplink system is triple redundant. Two primary uplink receivers are provided. Each has a separate LNA and two-frequency switch. A third receiver is the command receiver and does not have a LNA, this makes it both more reliable and less susceptible to interference. Once past the antenna, the uplink system includes no single point failure nodes. All three uplink receivers operate at 9.6 kbps rate.
The uplink VHF antenna consists of 4 monopoles. The antenna is linearly polarised and has a gain of approximately 0 dBi. The downlink UHF antenna system consists of 4 monopoles. Either the primary or the redundant transmitter chain can be connected to the downlink antenna through a latching relay controlled by on-board or ground-initiated telecommand.
Power Subsystem
The power subsystem conditions and distributes solar-generated electrical energy for the entire spacecraft. It provides regulated voltage supplies at +5V and ±10V along with an unregulated supply which fluctuates between 12V and 14V (depending upon the battery state of charge).
Four 330 x 530 mm solar array panels are mounted directly to the satellite body. These panels comprise Gallium-Arsenate (GaAs) solar cells for high conversion efficiency. The overall panel efficiency typically delivered from these panels is 19.5%, and the beginning of life (BOL) orbit-average power available is 20W.
The spacecraft battery is built from 10 NiCd cells. The battery has a capacity, at standard operating temperature, of 7Ah and a nominal operating voltage of 12 - 14V. The battery permits operation of payload and platform subsystems throughout eclipse periods and also provides limited-duration peak powers in excess of the capability of the solar panels.
Groundstation
A comprehensive satellite mission operations and control groundstation is being installed at Department of Physics, Universiti Kebangsaan Malaysia (Latitude: 2.917 degree North and, Longitude: 101.78 degree East). A standard Mission & Control Groundstation (MOCGS) to provide a cost-effective primamry station for mircosatellite mission has been designed. All components of the ground station, from uplink and downlink antennas to data archiving computers, have been chosen to provide an optimal compromise between cost, reliability and performance.

http://www.ee.surrey.ac.uk/SSC/CSER/UOSAT/missions/tiungsat/index.htm


8 Comments:

  • Thanks for your information on this satellite.It is supposed to have amateur radio communications but so far I have not heard anybody using this facility.It is a pity that the government spent millions of riggit and we amateurs are not using it.Can somebody knowledgable about this matter enlighten us and share your info with us but please do not bullshit if you dont know.People at Planetorium Negara or UKM Bangi ( 9M2DX Dr Faizal ) my throw some light as they were involved in the launching

    Katak bawah tempurung

    By Anonymous Anonymous, at 6:46 PM  

  • Okay... Don't lah like that... perli our friend! He is just sharing information what? No harm mah... Then you have any information to share with us?

    By Anonymous Anonymous, at 9:47 PM  

  • Dear 9W2SSJ,

    Keep up the good work... I think there is a ham friend 9W2QC SION who is a expert in satellite communication. I think he can be located at http://www.mares.org.my/

    Regards,

    9W2YJ
    Rodney

    By Blogger Rodney 9W2YJ, at 10:01 PM  

  • Dear All,

    Anyone here know what is the 70cm band plan?

    Well I have seen the 2meters band plan once in MARTS website.

    Well it will be usefull for new hams to know it as it will guide us to know which frequency to use what mode.

    Like Simplex, Duplex and Digital modes plus many more.

    Can anyone experience give a tinker?

    73

    Thanks

    Regards,

    Rodney
    9W2YJ

    By Blogger Rodney 9W2YJ, at 10:09 PM  

  • In my earlier comment I said peole who do not know about this sattellite please do not bullshit. I was not referring to 9w2ssj, it was to others.Suchart is a gentleman. I have met him a few times.IF Suchart is offended my sincere apologies.There was some politics involved in this project... betweem University of Surrey, UKM,UTM and Planetorium Negara. To know more
    get in touch with the various horses , each have their own version,These old timers can throw some light , 9m2ss, 9m2rs, 9m2za and 9m2cj.

    Mata kelabu.

    By Anonymous Anonymous, at 8:58 AM  

  • Hello All,
    Just stopped by this web site, and saw this post regarding Tiungsat.

    Well, first of all, let me inform you that Tiungsat is no longer operational due to a battery problem (that was what I last heard). Although in the amsat website, it is still listed as operational.

    Basically, Tiungsat, or known as MO-46 is a store and forward type amateur radio satellite. It transmits on its 70 cm downlink, packet data at 38.4 kbps, which means you need to modify your rig (you need to add a broader IF demodulater) and purchase a special TNC to use this high speed data mode. However, for the uplink, any 9600 baud ready rig will work.

    Although Tiungsat is a store and forward type amateur radio satellite, it also has camera to take pictures of the earth, and this is also accessible by amateurs. You will need the WISP satellite suite or a PB/PG client to access it.

    To the anonymous poster, please note that I am not bullshitting here. I have capabilities to receive packet (AX.25) at 1200, 9600 and 38400 baud as well as PSK data at 400 baud and 1200 baud. To make things short, I have the capability and am operating on all amateur radio digital satellites available today. If possible, please also include your name when you post here.

    Tiungsat requires the amateur to turn on the satellite in order to converse power. I have tried a turn on command 2 weeks ago, but it does not seem to be operational. Will try it again soon when I get my antennas up again.

    Hope this helps explain a bit about Tiungsat. Kindly post any questions or comments here. Thanks

    73,
    Sion Chow Q. C.,
    9W2QC.

    By Anonymous Sion Chow Q. C. (9W2QC), at 11:03 AM  

  • Dear Sion Chow,

    May I know what model or type of TNC is suitable to be used with IC-208H? I would like to try this SAT DXing experiment.

    Thank you for the last eyeball QSO at your QTH? I hope to learn new thing about this Amateur Radio Digital Communication hobby from you!

    Since we did not have a change to exchange QSL contact cards, could you exchange LL info via SMS.

    Nice to meet you and regards to you and your family.

    73

    Rodney
    9W2YJ
    H/P:013-3301736
    QTH:Klang.

    By Blogger Rodney 9W2YJ, at 4:04 PM  

  • Hi Rodney,

    Well, first of all I don't think the IC-208 is suitable for sat work because it is not a full duplex rig. However, it can be used for the ISS which does not require full duplex.

    The best TNC of course will be the Symek TNC3S. You can either get the 1200/9600 baud version or the 9600/38400 baud version. (this is the version I have) However, this TNC will cost you nearly the price of 2 ICOM IC-208s.

    You can go for alternate TNCs like the Kantronics KPC-3+ (1200 baud only) or KPC-9612+ (1200 & 9600 baud) or the PK-96 from Timewave.

    However, in order to receive data from the sats, you need precise doppler correction and a very reliable signal on the downlink. The use of preamps and directional antennas is a must I can say for 9600 baud and above.

    Of course, you can try soundcard solutions like AGW Packet Engine. They work very well for 1200 baud, but I did not have any success for 9600 baud. No soundcard solution works for 38400 baud at the moment, and for 38400 baud, you will need to add an IFD into your rig.

    Good luck and hope to hear you on the sats in the very near future. 73 de 9W2QC.

    By Anonymous Sion Chow Q. C. (9W2QC), at 12:47 AM  

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