Space Related Developments in Malaysia  60’s:  First communication satellite receiving station established  1988:  Establishment of Malaysian Centre for Remote Sensing (MACRES)  1989:  First Planetarium in Malaysia (Kuching) officiated  1990:  JUPEM started using GPS for mapping  1994:  National Planetarium officially opened  First professional astronomical observatory established in Malaysia (Terengganu) 1995  1995:  Initiation of National Microsatellite Programme  1996:  Launch into space of MEASAT-1 and MEASAT-2  1997:  Cabinet approval of the MIGHT National Blueprint for the Development of the Malaysian Aerospace Industry  1998:  First graduating batch of aerospace engineers from Universiti Putra Malaysia  1998:  Malaysian Communication and Multimedia Commission established  1999:  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 Malaysia  2001:  Establishment of National Aerospace Council  Commencement of MACSAT Programme  2002:  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

VISION To capitalize on space as a platform for enhancing the nation’s social, economic and strategic development. MISSION To 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  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 DATA RECEPTION

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 Payload CCD cameras characteristics NAC (Narrow Angle Camera) WAC (Wide Angle Camera) GSD78 x 78 m0.9 x 0.9 km Swath width78km900 km Spectral bands3 ( , & nm) 1 ( nm) Quantization8 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 6 th April, 2001.

Small Satellite Program RazakSAT ™ 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 – nm, MS Band , , , nm  Swath Width – 20km  Data Rate – 30 Mbps  Quantization – 8 bit  Mass Storage – 32 Gbit

RazakSAT Orbital Location A Comparison Sun-synchronous orbit Altitude: 822 km Inclination: 98.7 deg RAZAKSAT Near Equatorial Orbit Altitude: 685 km Inclination: 9 deg TIUNGSAT Altitude: 650 km Inclination: 64 deg

Omelek Island, 9º2.890’N, 167º44.585’E Falcon-1 RazakSAT – Launch Vehicle

Research Satellite CubeSat 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 Satellite  Participation from Malaysia universities  Stack from 3U CubeSat kit  Some subsystem design & develop by universities, e.g. ADCS & power  Will be launched together with RazakSAT™

Educational Satellite SiswaSAT 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.

CanSat Sample

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.