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