CN209821289U - Very low frequency solar radio observation system for satellite-borne - Google Patents
Very low frequency solar radio observation system for satellite-borne Download PDFInfo
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- CN209821289U CN209821289U CN201920427619.9U CN201920427619U CN209821289U CN 209821289 U CN209821289 U CN 209821289U CN 201920427619 U CN201920427619 U CN 201920427619U CN 209821289 U CN209821289 U CN 209821289U
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Abstract
The utility model discloses a very low frequency solar radio observation system for satellite-borne, which observes the low frequency solar radio signal of 100KHz-20MHz, and comprises three electric field sensors, three sets of analog receivers, a data acquisition and processing module, a time frequency module, a power supply module and a storage module; the three electric field sensors are respectively connected with three sets of analog receivers, the three sets of analog receivers and the time frequency module are respectively connected with the data acquisition processing module, the data acquisition processing module is connected with the storage module, and the data acquisition processing module and the three sets of analog receivers are respectively connected with the power supply module; the utility model discloses the motion condition of corona projecting material can be judged to the system, can predict, prejudge future space weather event.
Description
Technical Field
The utility model relates to a very low frequency solar radio observation system for satellite-borne is applicable to the solar radio observation of 100KHz-20MHz frequency channel based on satellite platform, adopts the three-dimensional electric field sensor of space quadrature can survey the electromagnetic wave of corona projectile material CME on three dimension, and then judges CME's direction of motion.
Background
The sun is the celestial body most closely related to human production and life, and its light and heat warm the earth and provide a proper environment for all life activities on the earth. The sun is a very active celestial body, often with vigorous activity and outbreaks. A number of observations and theoretical studies have been carried out on a number of solar outbreak events, including flare, coronage substance ejection (CME), dark stripe/daylight outbreak and jet, etc. Of these, flare and coronages ejection (CME) are the most intense solar burst. In ultraviolet and X-ray wave bands, the flare generates ultraviolet and X-ray radiation with the intensity which is hundreds of thousands of times higher than that of ordinary solar radiation, which causes severe disturbance to the earth ionosphere and directly influences short-wave radio communication on the ground. The coronagraph ejection (CME) carries a large amount of plasma substances, the coronagraph ejection carries the plasma substances to be ejected to interplanetary space at a speed of over kilometres per second, severe disturbance is generated on the space environment of the coronagraph and the geomagnetic field, the health of communication, navigation, launching and operation of space aircrafts, astronauts and flying personnel crossing polar regions is influenced, the safety of a remote power transmission network and an oil-gas transmission pipeline is influenced, and the like, and a lot of adverse effects are caused on the production and life of human beings.
Solar storms are solar burst events represented by strong solar flares and ejection of coronages that sweep through the interplanetary space, propagate, interact in the interplanetary space and affect the entire physical process of the space environment. Solar storms originate from complex electromagnetic interactions in the solar atmosphere, with extreme destructiveness and burstiness, like tornadoes, typhoons and strong tropical storms in the earth's atmosphere. The intense increase of solar electromagnetic radiation in solar storms severely affects the day-to-ground environment and leads to paralysis of the human electronic technology system. Due to the research on the aspect of solar electromagnetic radiation, the solar storm forecasting and early warning system is not only beneficial to people to know the physical essence of the solar storm, but also beneficial to people to forecast and early warn the disastrous space weather caused by the solar storm.
The disaster space weather or solar storm is usually caused by solar flares and CME, so that forecasting and early warning of the disaster space weather require real-time and all-weather monitoring of the solar flares and CME. The phenomenon that the radio-frequency flow is enhanced when strong flare spots and coronages are thrown is called as solar radio-frequency burst, the radio-frequency burst is mainly coherent plasma radiation in the wave bands of meter wave, ten meter wave and kilometer wave, the property of the plasma radiation determines that the frequency of the radio-frequency burst corresponds to different coronages positions and physical environments, and the solar radio-frequency burst can be divided into I, II, III, IV and V type radio-frequency bursts and accompanying fine structures according to the frequency spectrum form. Among them, type II radiostorms are the best tracer for CME shock waves. CME moves rapidly in space of coronages and interplanetals, when the speed of CME exceeds the local alfen speed, CME shock waves are generated and are difficult to observe on a coronagraph, therefore, when the movement range of CME exceeds the observation range of the coronagraph, or because the CME is just opposite to the earth and does not have any response on the coronagraph, the CME shock wave is detected to become a unique means for knowing the CME, and therefore, the CME shock wave early warning and forecasting method has important practical value for the early warning and forecasting of the weather of the disaster space for the observation of II type radio storms (namely tracers of the CME shock waves); the type III radiostorm is an optimal tracer for the movement of high-energy electron beams in solar corona, and is a precursor of solar outbreaks such as flare spots/CME (China general electronics and electronics engineers) because the type III radiostorm reflects physical processes such as solar outbreak energy release and particle acceleration; the radio fine structure reflects a tiny energy release process in the coronages and a small-scale change process of the coronages magnetic field during solar burst.
The ten-meter, hectometer and kilometer waves (or the radio frequency range below 30MHz, currently redefined as ultra-long wavelegnth (ULW)) belong to the observation category of very low frequency radio. The interplanetary II-type radio storm and the interplanetary III-type radio storm observed in the wave band can track interplanetary CME shock waves and high-energy electron beams, and the speed of the CME/shock waves and the time of arrival at the earth can be predicted according to a density model of the coronaries, so that the very-low frequency radio observation has irreplaceable effects on the aspects of forecasting and early warning of space weather. Due to the absorption and reflection of the earth atmosphere on electromagnetic waves, observation of very low frequencies must be carried out in a space outside the earth atmosphere, and observation of the frequency band is not available at home at present. Therefore, with the improvement of the demand of China on the early warning and forecasting of the space weather, the establishment of the very low frequency space weather radio frequency spectrometer is very important.
Disclosure of Invention
The utility model aims at a very low frequency solar radio observation system for satellite-borne mainly is applicable to the electromagnetic wave observation that produces when realizing throwing the corona material below being less than 20MHz on satellite platform, can judge the direction of motion that the corona throws the material simultaneously through the electric field sensor of three quadrature, and then makes preliminary judgement to the space weather event that probably takes place in the future.
The utility model discloses a realize through following technical scheme:
the utility model is used for satellite-borne very low frequency solar radio observation system receives the electromagnetic wave of three direction through the electric field sensor of three quadrature, through the independent analog receiver filtering of three routes, enlargies the back, is gathered and carries out spectral analysis by analog receiver, and the time frequency module provides time information to entire system, including second signal, AD drive signal etc. power module provides different voltage output to entire system.
The utility model discloses a very low frequency solar radio observation system for satellite-borne is to the low frequency solar radio outbreak of 100KHz-20MHz observes, and it includes three electric field sensor, three sets of analog receiver, data acquisition processing module, time frequency module, power module, storage module; the three electric field sensors are respectively connected with the three sets of analog receivers, the three sets of analog receivers and the time frequency module are respectively connected with the data acquisition and processing module, the data acquisition and processing module is connected with the storage module, and the data acquisition and processing module and the three sets of analog receivers are respectively connected with the power supply module.
The following respectively introduces three orthogonal electric field sensors, three sets of analog receivers, a data acquisition processing module, a time-frequency module, a power module and the like;
1. three orthogonal electric field sensors
The three electric field sensors are contracted and arranged on the outer surface of the satellite when the satellite is launched, the three electric field sensors are expanded after the satellite enters the orbit by a conventional space expanding device, the electric field sensors are low-loss metal rods, for example, the low-loss metal is beryllium copper alloy, the length of the electric field sensors is more than 5 meters, the three electric field sensors are arranged on the satellite in an X, Y, Z three-orthogonal distribution state through a support, wherein the X direction is towards the sun, the Y axis is parallel to the sun, and the Z axis is perpendicular to a plane formed by the X axis and the Y axis, so that an orthogonal test three-dimensional coordinate system facing the sun is formed and is used for measuring the electric field intensity E in the X, Y, Z directionX、EY、EZ。
2. Analog receiver
The three sets of analog receivers form an analog receiver module, and each set of analog receiver corresponds to one electric field sensor;
firstly, the analog receiver mainly realizes the functions of amplifying, filtering and the like of signals received by an antenna (an electric field sensor). Because plasma quasi-thermal noise radiation exists below 100KHz, a filter is required to be adopted to filter the plasma quasi-thermal noise radiation, so that interference is prevented; in addition, in order to prevent aliasing of interference above 20MHz into the ADC sampling band, a low pass filter must be employed inside the receiver.
The analog receiver is formed by sequentially connecting a front-end low-noise amplifier module, an analog high-pass filter (the pass band is more than 80kHz), a secondary amplifier and an analog low-pass filter (the pass band is less than 50MHz), wherein the low-noise amplifier module is connected with the electric field sensor, and the analog low-pass filter is connected with the data acquisition and processing module;
the front-end low-noise amplifier module plays a role in amplifying signals and requires noise less than that of the signalsThe gain of the amplifier is not less than 30dB, the amplifier is powered by a low noise drop out (LDO) module in a power supply module, and the amplifier is mainly placed outside a satellite cabin and connected with the input of the analog high-pass filter through a connector on the surface of a satellite;
the analog high-pass filter mainly plays a role in inhibiting low-frequency shot noise and plasma local radiation noise, and because the noise is mainly below 80kHz, the analog high-pass filter with a pass band larger than 80kHz is adopted to inhibit the noise; the output of the analog high-pass filter is connected with the input of the second-stage amplifier, and the analog high-pass filter is mainly placed outside the satellite cabin and is connected with the input of the second-stage amplifier through a connector on the surface of the satellite;
the second-stage amplifier plays a role in further amplifying the signal, the gain of the amplifier is not less than 30dB, a high-power DC-DC module in a power supply system provides power, and the output of the high-power DC-DC module is connected with the input of the analog low-pass filter;
the analog low-pass filter mainly filters interference signals inside the whole device and prevents the data acquisition processing module from aliasing with out-of-band interference.
3. Data acquisition processing module
The data acquisition processing module is formed by sequentially connecting 3 high-speed analog-to-digital converters (ADC), an FPGA signal processing core chip and a signal sending unit, and the analog low-pass filter is connected with the high-speed analog-to-digital converters; according to the Nyquist sampling theorem and the dynamic range of the solar radio explosion signaling, the sampling rate of the ADC is not lower than 80Msps, and according to the characteristic that the solar radio explosion flow is more than 30-40dB higher than the quiet flow, an ADC chip with more than 10bit of quantization digit is adopted; the data collected by the data collecting and processing module is temporarily stored by the storage module or/and is transmitted back to the ground center by the signal transmitting unit.
4. Time-frequency module
The module consists of a satellite-borne high-precision clock and a clock driving chip, wherein the satellite-borne high-precision clock is connected with the clock driving chip, and the clock driving chip is respectively connected with a high-speed analog-to-digital converter (ADC) and an FPGA signal processing core chip;
the satellite-borne high-precision clock outputs 1pps signals which are amplified by a clock driving chip and used as synchronous signals for signal processing of an ADC (analog to digital converter) acquisition and FPGA (field programmable gate array) signal processing core chip, and meanwhile, 5MHz or 10MHz standard signals output by the satellite-borne high-precision clock are multiplied by a clock driving chip amplification phase-locked loop to frequency required by ADC acquisition and frequency required by the work of the FPGA signal processing core chip and used as clock driving signals of the ADC and FPGA signal processing core chip.
5. Power supply module
The power supply module consists of a high-power DC-DC module and a low-noise LDO module, wherein the high-power DC-DC module is respectively connected with the secondary amplifier, the high-speed analog-to-digital converter, the FPGA signal processing core chip, the low-noise LDO module and the storage module and supplies power; and the low-noise LDO module mainly supplies power to a front-end low-noise amplifier module of the analog receiver.
6. Layout arrangement
Due to consideration on electromagnetic compatibility, the whole system is divided into two parts: the satellite external part comprises three orthogonal electric field sensors, a low noise amplifier module in an analog receiver module, an analog high-pass filter and a low noise LDO (low dropout regulator) module in a power module, and the low noise amplifier module, the analog high-pass filter and the low noise LDO module are arranged in independent shielding bins outside the satellite; through star surface aviation socket connection, include: an LDO input voltage cable, an electric field sensor control cable, a low noise amplifier output signal cable and the like; the remaining components in the system are placed inside the satellite capsule.
The utility model discloses an effect:
1. the method adopts three orthogonal electric field sensors to construct observation of solar radio outbreak, can judge the signal source direction through different induced voltage values on the three sensors, further judge the motion condition of the coronage projectile substance, and can predict and predict future space weather events;
2. the low noise amplifier module which is easy to be interfered is arranged outside the satellite cabin by adopting a scheme of distributing the inside and the outside of the satellite cabin, the strong electromagnetic radiation interference such as FPGA, DC-DC power supply and the like in the satellite is isolated through the surface of the satellite cabin body, the influence of the electromagnetic interference is reduced, and meanwhile, the influence of the instability of the power supply on the amplifier is reduced by adopting the independent low noise LDO module;
3. the system adopts the high-speed signal processor, can realize the work such as the processing of signals on the satellite, greatly reduces the transmission data volume and lightens the transmission pressure between satellite-ground links.
Drawings
FIG. 1 is a schematic diagram of the system of the present invention;
FIG. 2 is a schematic diagram of an analog receiver architecture;
FIG. 3 is a schematic diagram of a three-orthogonal electric field sensor for measuring incoming wave directions;
FIG. 4 is a circuit diagram of a low noise amplifier module and an analog high pass filter;
fig. 5 is a circuit diagram of a two-stage amplifier and an analog low-pass filter.
Detailed Description
The invention is explained in more detail below with reference to the figures and examples, without limiting the scope of the invention to the details.
Example 1: as shown in fig. 1-3, the satellite-borne very-low-frequency solar radio observation system observes low-frequency solar radio outbreaks of 100KHz to 20MHz, and comprises three electric field sensors, three sets of analog-digital receiver connections, a data acquisition and processing module, a time-frequency module, a power supply module and a storage module; the three electric field sensors are respectively connected with three sets of analog-digital receivers, the three sets of analog receivers and the time frequency module are respectively connected with the data acquisition processing module, the data acquisition processing module is connected with the storage module, and the data acquisition processing module and the three sets of analog receivers are respectively connected with the power supply module;
the electric field sensors are beryllium copper alloy rods, the three electric field sensors are arranged on the satellite in an X, Y, Z tri-orthogonal distribution state through a bracket, wherein the X direction is towards the sun, the Y axis is parallel to the sun, and the Z axis is perpendicular to a plane formed by the X axis and the Y axis, namely, a formed three-dimensional space faces the sun;
the analog receiver is formed by sequentially connecting a low-noise amplifier module, an analog high-pass filter, a secondary amplifier and an analog low-pass filter; the low-noise amplifier module is connected with the electric field sensor, and the analog low-pass filter is connected with the data acquisition and processing module; the data acquisition processing module is formed by sequentially connecting 3 high-speed analog-to-digital converters, an FPGA signal processing core chip and a signal sending unit, and the analog low-pass filter is connected with the high-speed analog-to-digital converters;
low noise amplifier module
Due to the size limitation of the interplanetary very low frequency radio detection antenna, according to the introduction of relevant foreign references and satellite experience, the input resistance of a detection system should be above 106 ohms, and the input capacitance should be below 3.0pF, which obviously cannot be achieved by directly adopting a radio frequency LNA or balun, so that a pre-amplifier needs to be added at the input end of the detector to carry out impedance conversion. For a receiver with a frequency range of 100kHz-20MHz, a low-noise voltage feedback type radio frequency operational amplifier can be adopted for construction.
The utility model discloses in, AD8004SQ (aerospace level) is adopted as first order low noise amplifier (low noise amplifier module) to first order, and its working noise only is:the chip is built into a first-stage low-noise amplifier when the lowest noise is lower than the required detection noiseTo effectively reduce the input noise of the overall receiver system (fig. 4).
Simultaneously after first order low noise amplifier, because interplanetary very low frequency radio detection system work is in the baseband, need restrain low frequency quasi-thermal noise (shot noise) and local resonance noise fp and generally be less than 100kHz simultaneously, have stronger noise hardly to deduct noise and sun radio signal at 100kHz, for this reason the utility model discloses following closely after first order low noise amplifier simulation high pass filter, the above-mentioned noise of filtering.
The sensitivity of the front-end low noise amplifier module is as follows:
first is the guarantee of noise:
the high-speed analog-to-digital converter adopts AD6645, the minimum recognizable signal power is +/-0.5 LSB (r.m.s), and the minimum recognizable signal power is as follows: pmin-116 dBw; the required amplification factor of the secondary amplifier is calculated to be about (power gain): g is 50 dB.
As shown in fig. 5, the present embodiment adopts AD8021SQ (aerospace level) as a core chip of the second-stage amplifier; the amplifier adopts a two-stage AD8021SQ two-stage amplification scheme, and the power gain of an amplification circuit formed by two stages of AD8021SQ reaches about 50-60dB approximately, so that the observation requirement is met; meanwhile, the output of the ADC is connected with a fourth-order Butterworth low-pass filter, so that high-frequency interference is filtered, and aliasing signals are prevented from being generated during ADC acquisition.
The data acquisition and processing module
The AD converter adopts AD6645 as an analog-to-digital converter, and the main indexes are as follows
1. The four-channel synchronous acquisition is realized in the single chip, and the sampling speed is as follows: 80 Msps;
2. quantization bit number: 14 bit;
3. spurious free dynamic range: 100 dBFs;
4. the reading speed can be set through the FPGA, and the seamless switching of the tranquility mode and the explosion mode is realized;
5. the internal part of the circuit is provided with a T/H acquisition and holding circuit, so that the design of peripheral circuits is reduced;
6. meanwhile, the high-energy particle resistant material has good high-energy particle resistant performance.
From the viewpoint of anti-interference and reliability, the biggest difficulty in designing an interplanetary electronic system is to select a proper digital system implementation mode; in the whole system, a digital system has the largest function density, the design difficulty of devices is higher, and the anti-interference capability and reliability of the digital system are the worst; according to international practice, the IGLOO aerospace-level FPGA of Actel corporation is adopted to construct the digital part of the observation system. IGLOO is realized by adopting a unique Flash non-volatile process, and the speed and the large capacity of the IGLOO cannot be compared with those of a mainstream FPGA (the maximum D trigger capacity is only 75K, and the maximum working frequency is about 100 MHz). But also because of adopting the non-easy Flash technology, the cosmic high-energy particle radiation has natural immunity and the static power consumption is extremely low. The advantages just meet the requirement of space electronics, so the series of FPGA has the full name in the field of aerospace.
In order to meet the frequency resolution requirement, the FFT algorithm in the FPGA must have a sufficient length, and according to the prior art, we apply an FFT with a length of 8192 points to the FFT algorithm, respectively, and the frequency resolution of the FFT algorithm will reach about 6 kHz.
The power supply module consists of a high-power DC-DC module and a low-noise LDO module;
most international satellites adopt a switching power supply mode, so that large noise and ripples are generated, and with the development of electronic technology, the noise and power consumption of an advanced low-power-consumption LDO chip (linear voltage converter) are improved well;
however, the LDO chip is low in output power and cannot completely support power supply of all loads, so that the LDO is used at a front-end low-noise part, a DC-DC or high-power linear voltage regulator scheme with strong loading capacity is adopted at a rear-end digital part, and noise is reduced through shielding isolation between an analog part and the digital part;
therefore, the load adopts an LDO linear regulator ADP7142 to supply power for a front-end first-stage low noise amplifier, and the main indexes of the regulator are as follows:
1. low noise: 11 μ Vrms, independent of the fixed output voltage;
2. power Supply Rejection Ratio (PSRR): 88dB (10 KHz), 68dB (100 KHz) and 50dB (1 MHz) (VOUT is less than or equal to 5V, and Vin is 7V);
3. input voltage range: 2.7V to 40V (fully compatible satellite supply voltage);
4. maximum output current: 200 mA;
5. line, load and temperature range accuracy ± (TJ-40 ℃ to +85 ℃), ± (TJ-40 ℃ to +125 ℃);
the rear end adopts a conventional high-power linear voltage stabilization chip to provide 3.3V and 1.2V for the FPGA, 5V for the storage module and 1.8V for the AD chip as working voltage and reference voltage.
The time-frequency module comprises a satellite-borne high-precision clock and a clock driving chip, the satellite-borne high-precision clock is connected with the clock driving chip, and the clock driving chip is respectively connected with the high-speed analog-to-digital converter and the FPGA signal processing core chip;
the time and frequency require the following signals:
1. the satellite-borne atomic clock provides a 5MHz or 10MHz standard signal, is used for being injected into a clock driving chip on a signal processing board, and is subjected to frequency multiplication to a frequency required by ADC acquisition and FPGA work through an internal amplification phase-locked loop of the clock driving chip to be used as a clock driving signal of the ADC and the FPGA;
2. standard second signal for the synchronization and the FPGA synchronizing signal that three channels were gathered, because the satellite-borne atomic clock provides 1pps standard second signal, the utility model discloses in with this standard second signal input clock driver chip, drive three routes ADC and FPGA chip.
Claims (7)
1. A very low frequency solar radio observation system for satellite-borne is characterized in that: the system is used for observing low-frequency solar radio signals of 100KHz-20MHz and comprises three electric field sensors, three sets of analog receivers, a data acquisition and processing module, a time-frequency module, a power supply module and a storage module; the three electric field sensors are respectively connected with the three sets of analog receivers, the three sets of analog receivers and the time frequency module are respectively connected with the data acquisition and processing module, the data acquisition and processing module is connected with the storage module, and the data acquisition and processing module and the three sets of analog receivers are respectively connected with the power supply module.
2. The very low frequency solar photovoltaic observation system for spaceborne according to claim 1, characterized in that: the electric field sensors are low-loss metal rods, the length of each electric field sensor is more than 5 meters, the three electric field sensors are arranged on the satellite in an X, Y, Z three-orthogonal distribution state through a support, wherein the X direction is towards the sun, the Y axis is parallel to the sun, the Z axis is perpendicular to a plane formed by the X axis and the Y axis, namely, a formed three-dimensional space faces the sun and is used for measuring the electric field intensity E in the X, Y, Z directionX、EY、EZ。
3. The very low frequency solar photovoltaic observation system for spaceborne according to claim 1, characterized in that: the analog receiver is formed by sequentially connecting a low-noise amplifier module, an analog high-pass filter, a secondary amplifier and an analog low-pass filter; wherein the low noise amplifier module has less noise thanThe amplification gain is not less than 30dB, the passband of the analog high-pass filter is more than 80kHz, the passband of the analog low-pass filter is less than 50MHz, the gain of the second-stage amplifier is not less than 30dB, the low-noise amplifier module is connected with the electric field sensor, and the analog low-pass filter is connected with the data acquisition and processing module.
4. A very low frequency solar radio observation system for spaceborne according to claim 3, characterized in that: the data acquisition processing module is formed by sequentially connecting 3 high-speed analog-to-digital converters, an FPGA signal processing core chip and a signal sending unit, and the analog low-pass filter is connected with the high-speed analog-to-digital converters; the sampling rate of the high-speed analog-to-digital converter is not lower than 80Msps, and a high-speed analog-to-digital converter chip with the quantization digit of more than 10bit is adopted.
5. The very low frequency solar photovoltaic observation system for spaceborne according to claim 4, characterized in that: the time-frequency module comprises a satellite-borne high-precision clock and a clock driving chip, the satellite-borne high-precision clock is connected with the clock driving chip, and the clock driving chip is respectively connected with the high-speed analog-to-digital converter and the FPGA signal processing core chip;
the satellite-borne high-precision clock outputs 1pps signals which are amplified by a clock driving chip and used as synchronous signals for signal processing of a high-speed analog-digital converter and an FPGA signal processing core chip, and meanwhile 5MHz or 10MHz standard signals output by the satellite-borne high-precision clock are multiplied by a frequency of a clock driving chip internal amplification phase-locked loop to frequencies required by the high-speed analog-digital converter for acquisition and the FPGA signal processing core chip to be used as clock driving signals of the high-speed analog-digital converter and the FPGA signal processing core chip.
6. Very low frequency solar photovoltaic observation system for spaceborne according to claim 3 or 5, characterized in that: the power supply module consists of a high-power DC-DC module and a low-noise LDO module, wherein the high-power DC-DC module is respectively connected with the secondary amplifier, the high-speed analog-to-digital converter, the FPGA signal processing core chip, the low-noise LDO module and the storage module and supplies power; the low-noise LDO module is connected with the low-noise amplifier module and supplies power.
7. The very low frequency solar photovoltaic observation system for spaceborne according to claim 6, characterized in that: the three electric field sensors, the low-noise amplifier module, the analog high-pass filter and the low-noise LDO module are arranged outside the satellite cabin, and the low-noise amplifier module, the analog high-pass filter and the low-noise LDO module are arranged in independent shielding cabins outside the cabin; the rest components of the system are placed in the satellite cabin.
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