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.

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.