04-04-2017, 10:44 PM
hi i would like to get details about laser satellite communication
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optical satellite communication seminar report pdf
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hi i would like to get details about laser satellite communication
12-04-2017, 11:58 AM
Optical satellite communication
The European Space Agency (ESA) has ongoing programs to place satellites carrying optical terminals into GEO orbit within the next decade. The first is the ARTEMIS technology demonstration satellite that carries both the microwave optical interorbit communications terminal and SILEX (Semiconductor Laser Intro). SILEX employs direct detection technology and GaAIAs diode laser technology; The optical antenna is a reflecting telescope 25 cm in diameter.
The SILEX GEO terminal is capable of receiving modulated data to an incoming laser beam at a transmission speed of 50 Mbps and is equipped with a high power headlamp for the initial acquisition of the link together with a low (and unmodulated) divergence beam, Which is tracked by the Interlocutor. ARTEMIS will be followed by the operational European Data Relay System (EDRS) which is planned to have data retransmission satellites (DRS). They will also carry SILEX optical data relay terminals.
Once these elements of the European Space Infrastructure are in place, it will be necessary to have optical communications terminals on LEO satellites capable of transmitting data to the GEO terminals. A wide range of LEO space craft are expected to fly in the next decade, including Earth observation and science, manned and military reconnaissance system.
The LEO terminal is known as a user terminal as it allows the real-time transfer of the LEO instrument data back to the ground to a user accessing the DRS s LEO instruments generating data over a range of speeds Of Mbps bits depending on the function of the instrument. A significant proportion have data rates falling in the region around and below 2 Mbps. And the data would normally be transmitted through an S-branded microwave IOL
ESA started a development program in 1992 for the LEO optical IOL terminal aimed at the user community segment. This is known as SMALL OPTICAL USER TERMINALS (SOUT) with low mass characteristics, small size and compatibility with SILEX.
The program is in two phases. Phase I was to produce a terminal flight configuration and detailed design and modeling of the subsystem. Phase 2, which began in September 1993, consists of building an elegant full-board breadboard.
Phase I was to produce a terminal flight configuration and detailed design and modeling of the subsystem. Phase 2, which began in September 1993, consists of building an elegant full-board breadboard.
The LEO ground link through the GEO terminal is known as the interorbital return link (RIOL). The SOUT RIOL data rate is specified as any data rate of up to 2 Mbps with a bit error rate (BER) of better than 106. The interorbit forward (FIOL) ground link to LEO was a nominal data rate of 34 K although some missions may not require data transmissions in these directions, so the link is highly asymmetric with respect to the data rate.
The technical LEO is mounted on the anti-earth side of the LEO satellite and must have a clear line of sight to the GEO terminal over a large part of the LEO orbit. This implies that there must be adequate height on the platform to avoid line-of-sight obstruction by solar platform platforms, antenna and other appertages. On the other hand, the terminal must be able to be housed inside the casing of the launcher. Because these limitations vary greatly with different LEO platforms, the SOUl configurations have been designed to be adaptable to a wide range of platforms.
The in-orbit life time required for a LEO mission in typically 5 years and adequate reliability has to be built in each subsystem for improved redundancy provision in recent years. And the GaAIAs devices are available with a mean time projected up to the failure of 1000 hours to an output power of 100 MW.
The terminal design that has been produced to meet these requirements includes a series of naval features, primarily a small refractive telescope (CPA), fiber-coupled lasers and receivers, a fiber-based scoring mechanism (PAA) Vibration Mounting) and combined acquisition and tracking sensor (ATDU). This combination has allowed to produce a unique terminal design that is small and lightweight. These characteristics are described in the following sections.
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