Nanosatellite means small satellites where the total mass are less than 10kg including the main payloads an Small satellite missions was not only driven by reduction of the space budgets but it was also made possible by of the technology and miniaturization of component. The new advancement of technology trends allow the applic sensing, communications and space science to benefit from the development of small satellites

Allaudin, Mohd Faizal

Kamal Adnan, Muhammad Shamsul

Md. Said, Assoc. Professor Md. Azlin

Othman, Mohd Helmi

Syed Hassan, Professor Syed Idris

Zakaria, Kamal Azli

English

Md. Said, Md. Azlin

Syed Hassan, Syed Idris

Repository@USM

Th~ Preliminary Design of a Nano Satellite Engineering Model for Remote Sensing Expe... Page 1 of 4Md. Azlin Md. SaidAssoc. ProfessorThe Preliminary Design of a Nano Satellite Engineering Model for Remote Sensing Expe11 ~10Syed Idris Syed HassanProfessorMuhammad Shamsul Kamal Adnan and Mohd Faizal AllaudinLecturerMohd Helmi Othman and Kamal Azli ZakariaResearch Officerd-V'V? I;' ~ -I~ Oc.:t·It-/.-·School of Aerospace Engineering,Universiti Sa ins Malaysia, 14300 Nibong Tebal, SPS, Pulau PinangTel: 04-5937788 ext. 6500 Fax: 04-5941026Email:aero@en9.LJSm.mVIntroductionNanosatellite means small satellites where the total mass are less than 10kg incuding the main payloads anSmall satellite missions was not only driven by reduction of the space budgets but it was also made possible byof the technology and miniaturization of component. The new advancement of technology trends allow the applic;sensing, communications and space science to benefit from the development of small satellites.This paper highlights on Preliminary Design of a Nanosatellite Engineering Model for Remote Sensing Experimethat it will promote the public interest in science, technology, space research, and international co-operation this Ito promote the public interest in science, technology, space research, and international co-operation.Mission DefinitionThe primary mission for the nanosatellite is remote sensing experiment and the secondary mission is communicnaosatellite, KA band will be used. All the communication set will be developed in house. The secondary payloaduse only one antenna as receiver and transmitter.Mission AnalysisThe real breakthrough with nanosatellite is not in capabilities but in cost. The nanosatellite's total mass is only 1various subsystems and payloads are given in Table 1. As it is small in size, it can be launched as a second.other missions, thus lowering the cost of launching it. Nanosatellite takes advantage of the low radiation environrearth orbit (LEO) by using commercial off-the-shelf components, which lowers non-recurring engineering costs.satellites simple command and control system requires only a basic ground station for operation, making thecosts a fraction of large competing earth imaging systems.B d tT bl 1 Ma e : ass u JaeSYSTEM MASS(kg) MARGIN MASS(kg) TOTAL MASS(kg) TOTAL MASS (%)Structure 1.5 0.5 2.0 20Propulsion 0.6 0.2 0.8 8ADCS 0.8 0.4 1.2 12Thermal 0.8 0.4 1.2 12Power 0.7 0.3 1.0 10C&DH 0.5 0.2 0.7 7Communication 0.5 0.2 0.7 7Payload 1.2 0.5 1.7 17Margin 0.5 0.2 0.7 7TOTAL 7.1 2.9 10 100file://D:\Technology Trends\250.htm 11/22/2004The Preliminary Design of a Nano Satellite Engineering Model for Remote Sensing Expe... Page 2 of 4Low earth orbit (LEO) will be used in this mission. Because of the primary mission is remote sensing, this is the bespecially for small satellite. Is also low in cost but still can archive the mission. The satellite orbit is approximatpolar orbit. At 10kg mass, nanosatellite is much smaller than competing Earth Imaging satellite. Refer to it small :nanosatellite can be launch as a secondary payload for a fraction of the cost a dedicated launch.StructureThe nanaosatellite will be constructed using a cubic structure of dimensions 300mm x 300mm x 300mm as showfive sides of its panel will be used to place the solar panels and the remaining facewill place the various payloadssensing camera and antenna, and the various sensors. Honeycomb structure will be used for each panel of thiinner side of the panel will be place all the main and subsystem.Figure 1: Nanosatellite main structurePayload Design AnalysisRemote Sensing PayloadThe remote sensing system it is a fundamental subsystem in a mission that has remote sensing as its primal)imagers are commons Le. a pan-chromatic imager and a multi spectral imagerThe multi spectral imager is camera, operating in a spectral band (Cyan, Yellow and Magenta). The main sub:CCO camera consist of optical system, beam splitting system, CCO devices and CCO imaging electronic (auxiliary subsystems of the CCO camera are side-looking reflector, relative calibration mechanism, foetemperature controller with their structures, control circuits, remote control and remote measurement circuits andpower units etc. They are divided into four packages mounted on the interior of the satellite, which is the body of eand mechanical control box, temperature controller, and CCO imaging circuit. For remote sensing system, it conslens, frame grabber and OSP and software to support the operation as shown in Fig. 2. A simplified block diagransensing system can be seen in Figure 3.Wi!LOOKIl~G tENSFJiFLECTQRCAWEUEUC1lI:ONlCC'IltcttfFigure 2: Block diagram of CCD Camerafi1e://D:\Techno1ogy Trends\250.htm 11/22/2004------ ----------------------Th,e Preliminary Design of a Nano Satellite Engineering Model for Remote Sensing Expe... Page 3 of4BUS8\'S1"BlI.JSFigure 3: Remote Sensing SystemsCommunication PayloadThe communication system of this nanosatellite featuring a Ka-band system. The KA-band has been selected beefrequencies offer many advantages The primary advantages of KA-band operation versus KU- and C-band incavailable bandwidth, reduced interference with terrestrial systems, smaller RF components (especially antennas),to provide mUltiple, narrow, high-gain spot beams for extensive frequency reuse. Bandwidth is the scarce resosystem capacity. C- and KU-band provide allocated bandwidth of about 500 MHz each, while Ka-bandFurthermore, most components limit the bandwidth that is usable in any specific application to a small percenta{Since component bandwidth is generally a percentage of the absolute operating frequency, KA-band permitsoperating bandwidth nearly double that of KU-band.Transmission of microwave signals to a satellite creates radiation which can also interfere with terrestrial microwcThis is particularly true at C-band, where relatively small antennas create large amounts of side lobe enenterrestrial microwave equipment operates in essentially the same part of the frequency spectrum. At KA-band, bEnarrower, antennas are relatively larger, and there is very little terrestrial equipment with which to interfere (althechange if the 30 GHz Local Multipoint Distribution System equipment population grows). The reduction in poteinterference will make it easier and less costly to locate transmit sites in populous areas.A significant benefit of the higher operating frequencies of KA-band is the reduced size of the RF components theThe shorter wavelength of KA-band requires smaller antennas, waveguide structures, and microwave componento obtain comparable performance to KU-band and C-band systems. KA-band very small aperture terminal (\sizes as small as 0.25 to 0.6 meters can provide the same gain, beam width and side lobe performance as 1.:systems at KU-band and 3.2- to 4.5-meter systems at C-band. RF components such as upconverters, downcinoise amplifiers and solid state power amplifiers can be made small enough to install directly on these Slproviding highly efficient integrated RF packages.For communication payload, it consists of modulator, demodulator, transceiver and antenna. A simplified blockcommunication system can be seen in figure 4 below.MODEMBUSSYS'TEMSFigure 4: Communication SystemsRT/duroid 5870 glass micro fiber reinforced PTFE composites are designed for exacting strip lines and micapplications. Glass reinforcing micro fibers is randomly oriented to maximize benefits of fiber reinforcement inmost valuable to circuit producers and in the final circuit application. The dielectric constant of RT/duroid 587uniform from panel to panel and is constant over a wide frequency range. Its low dissipation factor extends thERT/duroid 5870 to KU-band and above. We choose rectangUlar micro strip patch antenna in our design.fi1e://D:\Technology Trends\250.htm 11/22/2004The Preliminary Design of a Nano Satellite Engineering Model for Remote Sensing Expe... Page 4 of4.Figure 5: 8x8 Micro strip Patch Antenna before and after achingUsing ADS software, antenna is choosing to use in KA band (20 - 30 GHz). The objective with using the ADS is tstrip patch antenna - corporate feed network with good accuracy and set up the frequency/reflection coefficiercan be operate with ADS simulation. The reflection coefficient show that the antenna in simulated cases.Current StatusMost of the remote sensing payload components except the DSP are determined and under procurement.software of the remote sensing payload are being developed locally. The telecommunications payload is also bEsince most of the components such as the patch antennas, transceiver and the modem are in the final stage of dEThe main bus subsystems of the satellite such as the main structural frame, power (solar panel & batteriesdetermincation control (ADCS), thermal control, TT&C, etc ar being finalized and developed. The groundnanosatellite is being designed. Most of the SUbsystems and ground station will be designed, developed anchouse'.It is expected that the engineering model for remote sensing and communication system payload will be ready witConclusionThe nanosatellite will be the first small size «10kg) national satellite using some new technologies developEdesign manual of the satellite development will be used for other small satellite project in the future. It is expectengineering model will be ready in a year time and the design manual soon after that. Design and develcnanosatellite engineering model is a stepping stone for USM to involve in future national and international saprogram.AcknowledgementThis paper is made possible from the IRPA EA Research Grant 04-02-05-2126 EA 003 "Design of Nano-Satelli'<1 Okg and Low Cost Satellites) For Remote Sensing Experiments".References1. M. Richharia, 1995. Satellite Communication Systems-Design Principles: Macmillan New Electronics Serie2. F.J.Hale, 1994. Introduction to Space Flight: Prentice Hall3. P.Fortescue & J.Stark, 1995. Spacecraft Systems Engineering: John Wiley & Sons4. Mark Williamson, 1990. The Communication Satellite: Adam Hilger5. T.Pratt, C.W. Bostian, 1986. Satellite Communication: John Wiley & Sonsfile://D:\Technology Trends\250.htm 11/22/2004

Introduction to Space Flight:

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Spacecraft Systems Engineering:

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The Preliminary Design Of A Nano Satellite Engineering Model For Remote Sensing Expe

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The Preliminary Design Of A Nano Satellite Engineering Model For Remote Sensing Expe.

The Preliminary Design Of A Nano Satellite Engineering Model For Remote Sensing Expe.

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