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S3-A-MECH-1-0-Mechanisms

S3-A-MECH-1-0-Mechanisms - Date Issue 1 Rev 0 Page 1 of 27...

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Date : 16/06/2006 Issue : 1 Rev : 0 Page : 1 of 27 Phase A Antenna Deployment System Prepared by: Mario Greber Checked by: Approved by: y EPFL Lausanne Switzerland y 16/06/2006 y
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Issue : 1 Rev : 0 Date : 16/06/2006 Page : 2 of 27 Ref.: S3-A-MECH-1-0-Mechanisms.doc R ECORD OF REVISIONS ISS/REV Date Modifications Created/modified by 1/0 16/06/2006 Initial Issue M. Greber
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Issue : 1 Rev : 0 Date : 16/06/2006 Page : 3 of 27 Ref.: S3-A-MECH-1-0-Mechanisms.doc RECORD OF REVISIONS ................................................................................................................................... 2 INTRODUCTION .................................................................................................................................................. 4 1 PROJECT OBJECTIVES AND REQUIREMENTS ................................................................................ 4 2 DESIGN TRADES/ANALYSES ................................................................................................................. 4 2.1 A CTUATOR 4 2.1.1 Magnetic actuator 4 2.1.2 Melting wire actuator 5 2.2 A NTENNA MATERIAL AND SHAPE 6 2.2.1 Flat and flexible 6 2.2.2 Flat/flexible, with "v" shape 7 2.2.3 Material criteria 7 2.3 P LACE AND ORIENTATION 8 2.3.1 Satellites surface (one side) 9 2.3.2 Inside the Satellite 10 2.3.3 Around the satellite 10 2.4 P ACKAGING 11 2.4.1 Slots 11 2.4.2 Guide 12 2.5 E LECTRICAL ISOLATION 12 2.6 P OWER SWITCH AND TIMER 13 3 BASELINE DESIGN RECOMMENDATIONS ....................................................................................... 14 3.1 S OLUTIONS SUMMARY AND PRELIMINARY CHOICE 14 3.2 D ISCUSSION OF BASE LINE RECOMMENDATION 15 3.2.1 Connection time 15 3.2.2 Mass-, Volume- and Power budget 18 3.2.3 Antenna Eigen frequency 23 3.3 P ROTOTYPING 23 3.3.1 Nichrome wire fixation 24 3.3.2 Material choice 25 3.4 T ESTS 25 CONCLUSIONS, FUTURE WORK .................................................................................................................. 26 REFERENCES ..................................................................................................................................................... 27
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Issue : 1 Rev : 0 Date : 16/06/2006 Page : 4 of 27 Ref.: S3-A-MECH-1-0-Mechanisms.doc I NTRODUCTION 1 P ROJECT OBJECTIVES AND REQUIREMENTS All exchanged information between the satellite and the ground station are effected by radio transmitters on amateur radio frequencies. The used antennas will have a length of up to 2 meters. During the take off, the satellite mustn’t exceed a cube with slightly more than 10cm side length and a mass of 1kg. Therefore a system to deploy the antennas is needed. The first requirement of the deployment system is the high reliability. This has to be achieved with several other constraints like mass, volume and power consumption. The mass for the antenna system is budgeted to 25g. The used volume in the interior of the satellite has to be kept as small as possible and it mustn't exceed the cube more than 6.5mm. In addition to that, the system has to fulfil all the compatibility criteria for space applications. 2 D ESIGN T RADES /A NALYSES 2.1 Actuator Around 15 minutes after the launch of our Cubesat the antennas have to deploy autonomously. The most critical part is the activation mechanism to start the deployment. In other Cubesat projects there have mainly 2 different actuators been used. A magnetic actuator and an actuator by melting wire. The system has to guarantee a fixation of the antenna during the 15g accelerations of the rocket launch, vibrations and shocks. All this without any energy consumptions, because the launching conditions specify the complete shutdown of the electrical system.
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