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AME TRISYS DRIVER
AME Trisys CAN bus is a high-integrity serial data communications bus for real-time applications. It AME Trisys at data rates of up to 0. CAN was originally developed in Europe for use in cars, and is now being used in many other industrial automation and control applications. Data Transfer Rates. PICOSat does not provide highspeed data transfer to or from the spacecraft while it is in orbit. With limited line-of-sight contact from the ground station and inherent restrictions in on-board components, the estimated maximum data transfer rate is approximately 4 Mbytes per day.
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Electromagnetic Compatibility EMC. The satellite makes use of sun sensors and magnetometers to provide attitude information and magnetic torque generators to provide attitude adjustment. The magnetic torque generators are a set of 3 or 4 independently controlled wire coils that steer the satellite. When a current flows in a coil, it interacts with the AME Trisys magnetic field to create a force. More importantly, there was concern that various magnets and electrically-generated magnetic fields within SUITE would interfere with proper operation of the magnetometers.
The main result for the design of HXA was the addition of extensive magnetic shielding. These goals will be met ultimately in AME Trisys on-orbit demonstration of capabilities during the month PICOSat mission. The goals are a series of benchmarks for achieving and recording vibration isolation. Because PICOSat is a small specialized spacecraft, sources of vibrational disturbances on the satellite are few. There are no reaction wheels, cryocoolers, or solar array drives, or articulating payloads aboard. The only two known events that will disturb the satellite are the deployment of the six-meter gravity gradient stabilization boom and the deployment of the antenna for another payload.
Because the boom is critical to satellite operation and because it will be deployed before the satellite is fully operational, it is unlikely that SUITE itself will be functioning during that deployment. However, there is a question concerning the available power should SUITE and the other payload be turned on simultaneously. The experiment goals below assume the use of these disturbance generators. The vibration transmitted between the spacecraft bus and the isolated payload, measured as a root mean square quantity above 5 Hz, should be reduced in each of six axes by 20 dB a factor of 10 in the presence of vibration sources located on the satellite.
The upper limit to the frequency range of interest for the RMS calculation shall be determined by the measurement capability of the experiment, but shall reach at least Hz.
A reduction of less than 20 dB will be acceptable in one or more but not all axes depending AME Trisys the absolute level of motion introduced into the satellite bus. The order of importance of the degrees of freedom for demonstrating vibration reduction is 1 the two rocking i. The z rotation degree-of-freedom is expected to be difficult to exercise because of the geometry constraints. Although the stated goal addresses vibration above 5 Hz, a secondary goal is to reduce vibration by dB between 1 and 5 Hz Narrowband Vibration Isolation The vibration transmitted between the spacecraft bus and the isolated payload, measured as the narrowband sinusoidal amplitude, shall be reduced in each of six axes by 30 dB a factor of Tests shall be conducted at three separate frequencies, nominally 5 Hz, 25 Hz, and Hz.
A reduction of AME Trisys than 30 dB will be acceptable in one or more but not all axes depending on the absolute level of motion introduced into the satellite bus.
Satellite Ultraquiet Isolation Technology Experiment (SUITE)
Additional Goals Combined Broadband and Narrowband Isolation The performance goal is to achieve simultaneously the two goals described above. Narrowband Vibration Isolation from Payload-Attached Disturbance This criterion set is essentially the reverse of the AME Trisys goals described above.
The vibration transmitted between the payload and the spacecraft bus, measured as the narrowband AME Trisys amplitude, shall be reduced in each of six axes by 20 dB a factor of 10 or greater in the presence of vibration sources located on the payload. A reduction of less than 20 dB will be acceptable in one or more but not all axes depending on the absolute level of motion introduced into the payload. AME Trisys order of importance of the degrees of freedom for demonstrating vibration reduction is 1 the three rotation modes and 2 the three translation modes.
Results for this set of criteria will be difficult to quantify because of the presence of the passive isolation system and the inability to deactivate it. Because of the anticipated effectiveness of the passive isolation system, a demonstration of 10 dB reduction of satellite vibration beyond that achieved with the passive system will be acceptable at Hz. Narrowband Vibration Suppression of Payload-Attached Disturbance The payload is to quieted in response to AME Trisys originating on the payload. The payload vibration, measured as the narrowband sinusoidal amplitude, shall be reduced in each of six axes by 20 dB AME Trisys factor of 10 or greater in the presence of vibration sources located on the payload.
Reduction of the vibration transmitted between the payload AME Trisys the spacecraft bus is not a goal, although it will be measured. The order of importance of the degrees of freedom for demonstrating vibration AME Trisys is 1 the two rocking or tilt x and y rotation modes, 2 the three translation modes, and 3 the twisting or z rotation mode. Other Intended Experiments Vibration reduction on the payload due to uncontrolled spacecraft disturbances.
Demonstration of performance in response to oscillation of the major spacecraft boom. AME Trisys of performance in response to tailored disturbance sources.
TFTrisy (Hana) DeviantArt
Demonstration of longevity of experiment. Microprecision pointing. Demonstration of performance over a wide temperature range. Broadband vibration isolation between the payload and satellite in the presence of payload-attached sources Broadband vibration suppression on the payload due to payload-attached sources Vibration suppression on the payload using the payload disturbance source as a control actuator 4. The active isolation principle is presented. The approach to vibration isolation and strut-to-strut coupling in the hexapod configuration are discussed. Find many great new & used options and get the best deals for Ame & Lulu A&l Tinsley AME Trisys - Clover Sports Accessorie at the best online prices at eBay!
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