MALAYSIA'S SPACE ACTIVITIES
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Transcript of MALAYSIA'S SPACE ACTIVITIES
Space Related Developments in Malaysia
60’s: First communication satellite receiving station established1988: Establishment of Malaysian Centre for Remote Sensing (MACRES)1989: First Planetarium in Malaysia (Kuching) officiated1990: JUPEM started using GPS for mapping1994: National Planetarium officially opened
First professional astronomical observatory established in Malaysia (Terengganu) 1995
1995: Initiation of National Microsatellite Programme1996: Launch into space of MEASAT-1 and MEASAT-21997: Cabinet approval of the MIGHT National Blueprint for the Development of the Malaysian Aerospace Industry1998: First graduating batch of aerospace engineers from Universiti Putra Malaysia1998: Malaysian Communication and Multimedia Commission established1999: First Malaysian science payload launched onboard SunSAT
Space Related Developments in Malaysia (cont.)
2000: Launch into space of microsatellite TiungSAT-1 Initiation of Medium-sized Aperture Camera (MAC)
Programme First graduating batch of BSc. (Remote Sensing) from
Universiti Teknologi Malaysia2001: Establishment of National Aerospace Council Commencement of MACSAT Programme2002: Establishment of National Space Agency (ANGKASA)
Cabinet approval for Near Equatorial Low Earth Orbit (NEqO) Satellite Constellation Programme
Commissioning of MACRES Ground Receiving Station 2003: MEASAT-3 Procurement Announcement
Announcement of National Astronaut Programme Renaming of MACSAT to RazakSAT University Nanosat
2004: National Space Centre Commenced
Space Related Developments in Malaysia (cont.)
2005: National Observatory Construction at Langkawi completed Assembly, Integration and Test Facility commenced
2006: Launch of MEASAT-3 Feasibility studies for telecommunication satellite
2007 : Completion of feasibility studies for telecommunication satellite
Launch of Malaysia’s ANGKASAWAN
OUTLINE
• ANGKASA Overview- Division and Functions - Malaysia Space Centre
• Micro-Satellite Program• Small Satellite Program• Research Satellite• Educational Satellite
VISIONTo capitalize on space as a platform for enhancing the nation’s social, economic and strategic development.
MISSIONTo enhance, stimulate and nurture the nation’s potential in the field of space through integrated and coordinated efforts in the development and application of space technology with a view to : Providing a support system for solving national problems; Adding value to national policies; Promoting international cooperation; and Advancing knowledge
for the benefit of the people of Malaysia in particular and humankind in general.
Divisons and Locations
Headquarters, Putrajaya (5th floor)
National Planetarium, Kuala Lumpur
National Observatory, Langkawi
Malaysia Space Centre, Banting
MALAYSIA SPACE CENTRE
Development Phases:
Phase 1 – Mission Control Facility
Phase 1B – Optical Calibration Lab
Phase 2 – Quarters & Mes
Phase 3 – Satellite Technology Facilities
Development began towards the end of 2004.
Situated in a 400 acre land in Sungai Lang, Banting, Selangor.
Phase 1 – Mission Control Facility
TT&C Centre
RazakSAT Satelit-satelit LEO & MEO
TT & C
X-band data
X-BAND DATARECEPTION
Phase 1B – Optical Calibration Lab
NORAD TLE No: 26548U Launch Date: 26th Sept 2000, 10:05 UT Launch Site – Baikonor, Kazakhstan Orbital Elements
•Orbital inclination: 64.5 degree •Orbit type :LEO circular •Altitude: 650 km •Periods: 97 min
Micro-Satellite Program
TiungSAT-1
Structure & Bus:• Weight : 50 kg (35kg platform, 15kg payloads)• Dim : 690 x 366 x 366 mm • ADCS : 3 axis stabilized (experimental)• Comms: Amateur Satellite Frequencies VHF/UHF
Payload:•CCD cameras (1 WAC and 3 NAC) •Cosmic ray Energy Deposition Experiment (CEDEX)•Digital Signal Processing Experiment (DSPE)
Mission Lifetime : 3 years
TiungSAT-1 PayloadCCD cameras characteristics
NAC (Narrow Angle Camera)
WAC (Wide Angle Camera)
GSD 78 x 78 m 0.9 x 0.9 km
Swath width 78km 900 km
Spectral bands 3 (500-590, 610-690 & 810-890 nm)
1 (810-890 nm)
Quantization 8 bit 8 bit
TiungSAT-1 Payload (cont)
• CEDEX characteristics– characterize the TiungSat-1 orbit radiation
environment in terms of the observed particle LET (Linear Energy Transfer) spectrum at the spacecraft.
– Multi-channel analyzer with 512 channels and a 0.5 pC (pico-coulomb) charge resolution
• DSPE characteristics– used for processing audio transmission for
rebroadcast
Image of Penang Island acquired from TiungSAT-1 on 6th April, 2001.
Small Satellite ProgramRazakSAT™
Structure & Bus: Mass – 200 kg
Ø 1200 x 1200 mm hexagonal shape
ADCS: 3-axis stabilization based on 4 reaction wheels
Sun tracking system
Designed Life Time – 3 years
RazakSAT™ Payload
Characteristics: Medium Aperture Camera (MAC)
GSD – 2.5m (PAN), 5m (Multi-Spectral)
PAN Band – 510-730 nm, MS Band - 450-520, 520-600, 630-690, 760-890 nm
Swath Width – 20km
Data Rate – 30 Mbps
Quantization – 8 bit
Mass Storage – 32 Gbit
RazakSAT Orbital LocationA Comparison
Sun-synchronous orbitAltitude: 822 kmInclination: 98.7 deg
RAZAKSATNear Equatorial OrbitAltitude: 685 kmInclination: 9 deg
TIUNGSATAltitude: 650 kmInclination: 64 deg
Omelek Island, 9º2.890’N, 167º44.585’E
Falcon-1
RazakSAT – Launch Vehicle
Research SatelliteCubeSat
• Pico-satellite• 10cm cubes, with mass <1kg• Using commercial off-the-shelf components• Typical lifetime: 6 months• Use of standard deployment system P-POD• Advantage
– “Smaller, Cheaper, Faster, Better”– able to perform as a test bed for new systems and core space
technologies to be applied to space programs
INNOSAT
Also known as Innovative SatelliteParticipation from Malaysia universitiesStack from 3U CubeSat kitSome subsystem design & develop by universities, e.g. ADCS & powerWill be launched together with RazakSAT™
Educational SatelliteSiswaSAT
• Well known as CanSat.• Weighing 350 to 1050 g• CanSat is a simulation of a real satellite
– Include most subsystems found in satellite– Simulate subsystem requirements of real satellite
• All basic functions of a satellite, such as those of power and communications, are fitted into a soda can of 350 ml
• Usually, CanSat launch as the payload in an amateur rocket up to altitude of 3000m and have their own recovery system; usually a parachute or parafoil that will allow a slow drift about 20 minutes.
Malaysia SiswaSAT competition
• New initiative for national space educational programs• Provide entry level platform to undergraduate student in experiencing
satellite development process• Development, launch and operation of SiswaSAT
– Standard kit which only covers main subsystem will be provided; allow them to have flexibility and innovative idea in designing their SiswaSAT
– Participants will be evaluated based on compliance to mission requirements, documentation and presentation during PDR & CDR, engineering and management aspect. Bonus point will be given for their creativity & innovative.
– SiswaSAT will be carried by captive balloon with helium gas up to 150m from ground and launch.