CN104617390A - Satellite-borne large-size phased array antenna beam control device - Google Patents
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Abstract
The invention discloses a satellite-borne large-size phased array antenna beam control device. A satellite platform digital management computer is used for sending beam pointing data to a beam control computer; the beam control computer is used for obtaining a beam control code according to the beam pointing data and sending the beam control code and a working time sequence to each beam control unit; after each beam control unit receives the beam control code and the working time sequence, the beam control code is checked and identified and each code value is sent to a phase shifter and an attenuator of a controlled device; beam appointing switching of a whole antenna array is finished according to the requirements of the working time sequence. The application of a phased array antenna spanning across to a satellite platform from a ground platform is realized so that the beam electric scanning control of a two-dimensional large-size phased array is finished. The satellite-borne large-size phased array antenna beam control device can be widely applied to the fields including communication satellites, measurement satellites, scouting satellites and the like, has the characteristics of small volume, light weight and high reliability, and meets the requirements that satellite-borne electronic equipment can work for long time on orbit and cannot be repaired.
Description
Technical field
The present invention relates to a kind of satellite antenna load observation and control technology, in particular a kind of spaceborne massive phased array antenna beam control device.
Background technology
Phased array antenna system is widely used in the field of engineering technology such as radar, navigation and electronic countermeasures.The general principle of phased array antenna system each array element to phased-array antenna array transmits and receives the amplitude of signal and phase place controls, and makes in the specific direction of the beam position of space combination, or form zero in some specific direction and fall into.Have beam position flexibly, directional diagram can be comprehensive etc. advantage.
Phased array antenna overcomes large, the slow-footed shortcoming of mechanical means rotable antenna inertia, adopt computer control current feed phase, pace of change fast (Millisecond), control flexibly, Iarge-scale system can be coordinated to complete multiple-working mode, reasonably the energy of aerial radiation is utilized at maximize, improve the task performance of Iarge-scale system.Because of the huge advantage of phased array antenna, and apply in the maturation of ground radar and airborne platform, in recent years, also gradually phased array antenna is applied to satellite platform, and is developed to large-scale antenna array by the bay of small-scale.But the environment residing for satellite platform and ground and low hollow panel completely different, particularly face the impact of Energetic particle radiation, cosmic ray, electronic equipment easily produces ionization total-dose damage, various single particle effect (as: single-particle inversion, single-ion transient state, single event latch-up, single event function interrupt), cause electronic functionalities not normal, even produce permanent inefficacy.Space electronic equipment also requires that low weight, small size, low heat dissipation design simultaneously.To require in life cycle reliably working, non-maintaining in-orbit.Therefore, ground surface platform has not met completely the instructions for use of spaceborne environment for the Beamsteering Unit of phased array antenna.
Summary of the invention
The object of the invention is to overcome the deficiencies in the prior art, provide a kind of spaceborne massive phased array antenna beam control device, Energetic particle radiation can be adapted to, avoid electronic equipment surface discharge and recharge.
The present invention is achieved by the following technical solutions, the present invention includes satellite platform number pipe computer, beam guidance computer, multiple Beamsteering Unit, C-band T/R assembly, C-band time delay amplifier module, L-band T/R assembly and L-band time delay amplifier module, described satellite platform number pipe computer is by beam position data (β, α) send to beam guidance computer, described beam guidance computer obtains beam-control code according to beam position bearing data, and beam-control code is sent to each Beamsteering Unit together with work schedule, after described each Beamsteering Unit receives beam-control code and work schedule, checksum validation is carried out to beam-control code, the beam-control code of each T/R assembly is added up mutually, compared with the check code that the cumulative check code obtained and Beamsteering Unit receive, if conformed to, then by the beam-control code of respective channel and work schedule extraction and according to after the data format requirement restructuring of each assembly, then the C-band T/R assembly that this Beamsteering Unit is corresponding is forwarded to, C-band time delay amplifier module, L-band T/R assembly and L-band time delay amplifier module, after each T/R assembly receives beam-control code, carry out serioparallel exchange, each code value is given phase shifter and the attenuator of controlled device, according to work schedule requirement, the beam position completing whole antenna array switches.
Described beam-control code is: according to beam pointing-angle, calculate the phase shift code of each phase shifter on antenna array, the decay code of attenuator, the time delay code of time delay amplifier, and be added with the check code that antenna array obtains in power up initialization process, eliminate the inconsistency of each passage, finally obtain the time delay code of the phase shift code of each phase shifter, the decay code of attenuator and delay line, be referred to as beam-control code.
Described Beamsteering Unit comprises anti-fuse FPGA chip, A/D conversion chip, differential signal input and output driver module, many group fuse circuits and storage capacitor, described differential signal input and output driver module comprises differential receive circuitry and difference transtation mission circuit, described anti-fuse FPGA chip receives beam-control code by differential receive circuitry from beam guidance computer, the temperature data of the C-band power supply gathered and L-band power supply and antenna array diverse location is sent into anti-fuse FPGA chip by A/D conversion chip, described anti-fuse FPGA chip carries out prefix differentiation, School Affairs checks, if all correct, the data of each T/R passage are extracted again from the beam-control code received, according to C-band assembly, L-band module data protocol requirement, splicing and the restructuring of data is completed at anti-fuse FPGA chip internal, finally the beam-control code of each passage is sent to corresponding T/R assembly according to timeticks serial, state information is uploaded to beam guidance computer by difference transtation mission circuit according to the agreement of regulation by anti-fuse FPGA chip, many groups fuse circuit is connected on+9V the power supply of C-band T/R assembly successively, storage capacitor is connected in parallel on+9V the power supply of C-band T/R assembly.
Described beam-control code data send at the trailing edge of clock, and T/R assembly gathers serial data at the rising edge of clock.
The prototype verification method of described anti-fuse FPGA chip is as follows: first generate net meter file to the compiling of antifuse device design document, then the net meter file of generation is converted to the net table of the ProAsic chip based on flash technique, the sequential of antifuse chip and prototype adapter flash chip is mated, carries out the pin conversion of two kinds of chips simultaneously.After completing the prototype verification in antifuse chip early stage, just real antifuse chip can be fallen to being soldered on circuit board.Completely the same owing to encapsulating, Beamsteering Unit, without the need to correcting, highly shortened the construction cycle, reduces design risk.
The model of described anti-fuse FPGA chip is A54SX72A-CQ208B.
Described Beamsteering Unit totally 54, beam guidance computer and whole antenna array amount to 9 interfaces, each interface connects 6 Beamsteering Unit, each Beamsteering Unit controls 12 C-band T/R assemblies, 4 C-band time delay amplifier modules, 8 L-band T/R assemblies and 4 L-band time delay amplifier modules, 12 C-band T/R assemblies are divided into 4 groups, often group comprises 3 C-band T/R assemblies and 1 C-band time delay amplifier module, 8 L-band T/R assemblies are divided into 2 groups, and often group comprises 4 L-band T/R assemblies and 2 L-band time delay amplifier modules.
Described each Beamsteering Unit and adopt RS422 differential bus mode to transmit data between beam guidance computer and each T/R assembly, one is adopted to drive many connected modes, namely send source one road signal, drive multipath reception end, connect build-out resistor in distalmost end.
Described A/D conversion chip has two, selects TLC2543 as A/D conversion chip, one in order to gather the temperature of C-band T/R assembly power supply-5V, 9V and each position of antenna array, another is in order to gather L-band T/R assembly power supply-5V ,+5V, 28V.
Described often group fuse circuit and storage capacitor comprise two fuse protective circuits and three Large Copacity storage capacitors; fuse circuit is connected on C-band T/R assembly+9V power supply; three Large Copacity storage capacitors are connected in parallel on C-band T/R assembly+9V power supply; in described two fuse protective circuits, in parallel with another fuse protective circuit again after one of them fuse protective circuit series connection high-power resistance.
The present invention has the following advantages compared to existing technology: present invention achieves phased array antenna is crossed satellite platform application by ground surface platform, and the wave beam electric scanning completing two-dimentional massive phased array controls.The present invention can meet the strenuous vibration of rocket firing ascent stage, under spatial complex environment, reliability application under particularly Energetic particle radiation, vacuum condition, whole Beamsteering Unit board design, production and paster are in strict accordance with aerospace processing flow process, select the high-quality level device with radioresistance index, adopt two point two-wire without connection cable between isolated large-area metal conductor, unit, ic power end adds and current-limiting resistance, plate adds metal reinforcing, dispel the heat more than the device conducts of 300mw, surface mounting component needs a glue to fix.Spaceborne massive phased array antenna beam control unit, can be widely used in the fields such as communication satellite, instrumented satellite and reconnaissance satellite.There is small size, low weight, highly reliable feature, meet the electronic equipment on satellite operation on orbit time long, not maintainable requirement.
Accompanying drawing explanation
Fig. 1 is whole antenna array three grades of wave beam control flow block diagrams;
Fig. 2 is the interface network figure between beam guidance computer and Beamsteering Unit;
Fig. 3 is the schematic diagram that each Beamsteering Unit controls 4 kinds of T/R assemblies and time delay amplifier;
Fig. 4 is the composition frame chart of Beamsteering Unit;
Fig. 5 is ACTEL anti-fuse FPGA prototype verification flow chart in Fig. 4;
Fig. 6 is the schematic diagram of A/D conversion chip in Fig. 4;
Fig. 7 is RS422 differential signal receiving circuit schematic diagram in Fig. 4;
Fig. 8 is RS422 differential signal transtation mission circuit schematic diagram in Fig. 4;
Fig. 9 is Large Copacity storage capacitor and fuse protective circuit schematic diagram in Fig. 4;
Figure 10 is the communication succession schematic diagram of Beamsteering Unit and ripple control computer in Fig. 4.
Embodiment
Elaborate to embodiments of the invention below, the present embodiment is implemented under premised on technical solution of the present invention, give detailed execution mode and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
As shown in Figure 1, the present embodiment comprises satellite platform number pipe computer 1, beam guidance computer 2, the phase shifter of multiple Beamsteering Unit 3, C-band and L-band T/R assembly 4, controlled device and attenuator, C-band and L-band T/R assembly 4 comprise C-band T/R assembly, C-band time delay amplifier module, L-band T/R assembly and L-band time delay amplifier module, described satellite platform number pipe computer 1 is by beam position data (β, α) send to beam guidance computer 2, described beam guidance computer 2 calculates beam-control code according to beam position bearing data according to bidimensional rectangular grid phased array antenna principle, and beam-control code is sent to together with work schedule each Beamsteering Unit 3, after described each Beamsteering Unit 3 receives beam-control code and work schedule, checksum validation is carried out to beam-control code, the beam-control code of each T/R assembly is added up mutually, compared with the check code that the cumulative check code obtained and Beamsteering Unit 3 receive, if conformed to, then by the beam-control code of respective channel and work schedule extraction and according to after the data format requirement restructuring of each assembly, then the C-band T/R assembly of this Beamsteering Unit 3 correspondence is forwarded to, C-band time delay amplifier module, L-band T/R assembly and L-band time delay amplifier module, after each T/R assembly receives beam-control code, carry out serioparallel exchange, each code value is given phase shifter and the attenuator of controlled device, according to work schedule requirement, the beam position completing whole antenna array switches.Beam-control code is: according to beam pointing-angle, phase shift code, the decay code of attenuator, the time delay code of time delay amplifier of each phase shifter on antenna array is calculated according to bidimensional rectangular grid phased array antenna principle, and be added with the check code that antenna array obtains in power up initialization process, eliminate the inconsistency of each passage, finally obtain the time delay code of the phase shift code of each phase shifter, the decay code of attenuator and delay line, be referred to as beam-control code.
As shown in Figure 2, beam guidance computer 2 and whole phased array antenna amount to 9 interfaces, and each interface connects 6 Beamsteering Unit 3, and for beam guidance computer 2 interface, data wire DATA0 ~ DATA5 independently uses, can transmitting data in parallel.Other ripple control instructions input: TR_R_C, TR_T_C, TR_R_L, TR_T_L, CLK, SYN, READY.Digital telemetering: RS422 bus mode that FLAG, DATA2 all adopt " drives six " connects.
As shown in Figure 3, the Beamsteering Unit 3 of whole antenna array totally 54, beam guidance computer 2 and whole antenna array amount to 9 interfaces, each interface connects 6 Beamsteering Unit 3, for a Beamsteering Unit 3, a Beamsteering Unit 3 controls 12 C-band T/R assemblies, 4 C-band time delay amplifier modules, 8 L-band T/R assemblies and 4 L-band time delay amplifier modules, and the signal be connected between Beamsteering Unit 3 with T/R assembly comprises TR_T, TR_R, DATA, CLK, SYN, READY, BITE.Only have DATA signal will transmit different beam-control code, other signal can according to the connected mode of RS422 shared bus, in order to reduce the weight of connection cable between Beamsteering Unit 3 and assembly, 12 C-band T/R assemblies are divided into 4 groups, often group comprises 3 C-band T/R assemblies and 1 C-band time delay amplifier module, shares TR_T, TR_R, CLK, SYN, READY, BITE.8 L-band T/R assemblies are divided into 2 groups, and often group comprises 4 L-band T/R assemblies and 2 L-band time delay amplifier modules.
As shown in Figure 4, Beamsteering Unit 3 comprises anti-fuse FPGA chip, A/D conversion chip, differential signal input and output driver module, many group fuse circuits and storage capacitor, described differential signal input and output driver module comprises differential receive circuitry and difference transtation mission circuit, described anti-fuse FPGA chip receives beam-control code by differential receive circuitry from beam guidance computer 2, the temperature data of the C-band power supply gathered and L-band power supply and antenna array diverse location is sent into anti-fuse FPGA chip by A/D conversion chip, described anti-fuse FPGA chip carries out prefix differentiation, School Affairs checks, if all correct, the data of each T/R passage are extracted again from the beam-control code received, according to C-band assembly, L-band module data protocol requirement, splicing and the restructuring of data is completed at anti-fuse FPGA chip internal, finally the beam-control code of each passage is sent to corresponding T/R assembly according to timeticks serial by difference interface circuit, state information is uploaded to beam guidance computer 2 by difference transtation mission circuit according to the agreement of regulation by anti-fuse FPGA chip, fuse circuit is connected on C-band T/R assembly+9V power supply, storage capacitor is connected in parallel on C-band T/R assembly+9V power supply.Beam-control code data send at the trailing edge of clock, and T/R assembly gathers serial data at the rising edge of clock, guarantees that data can correctly be obtained.
Ripple control instruction input, digital telemetering two kinds is divided into upper level beam guidance computer 2 interface signal.Ripple control instruction inputs: T TR_R_C, TR_T_C, TR_R_L, TR_T_L, CLK, DATA, SYN, READY.Digital telemetering: FLAG, DATA2.Wherein TR_T_C, TR_T_L are the emission control pulse of C-band assembly and L-band assembly, and TR_R_C, TR_R_L are the reception control impuls of C-band assembly and L-band assembly.Beam-control code is sent to Beamsteering Unit 3 by CLK, DATA, SYN, after Beamsteering Unit 3 completes the distribution of all T/R module datas by the time, is refreshed the beam position of antenna array by READY signal.DATA2 is the output interface of antenna array telemetry, under FLAG and CLK controls, export antenna subsystem digital telemetering data to beam guidance computer 2 by DATA2.
FPGA is the core devices of Beamsteering Unit 3, and its stability directly affects the control of antenna beam.Current FPGA mainly contains 3 types, based on SRAM type, FLASH type and anti-fuse type.Under spaceborne high rail environment, FPGA is faced with the space radiation problems such as ionization total-dose, single-particle inversion, locking single particle, SRAM type FPGA the most easily produce single-particle inversion (SingleEvent Upset SEU) although, FLASH type FPGA reliability is higher than SRAM type, can not avoid the variety of problems of space single particle effect.Anti-fuse type FPGA is that most suitable aeronautical field uses, there is height reliability and stability that other structure FPGA device do not have, it is strong that anti-fuse FPGA has Radiation hardness, the features such as power-on time is short, low in energy consumption, antifuse chip is in a lot of satellite successful Application, and reliability is fully verified.But anti-fuse FPGA has disposable programming, not reproducible programming, feature that device capacitance is less simultaneously.Therefore, the design function checking before programming anti-fuse FPGA, timing verification and calculation of natural resources are extremely important.The antifuse device prototype verification solution based on Actel ProAsic device that the present embodiment adopts ALDEC company and Actel company jointly to release.The present embodiment selects the anti-fuse FPGA chip of ACTEL company, and model is A54SX72A-CQ208B, anti-fuse FPGA chip prototype verification flow process as shown in Figure 5, employing be the antifuse adapter of ALDEC company, model is: I-ACT-RTSXi-CQ208.First in the Libero software development environment of ACTEL, select antifuse device A54SX72A-CQ208B, net meter file is generated to design document compiling, then the net table switching software of ALDEC company is used, the net table of A54SX72A-CQ208B device generation is converted to the net table of the ProAsic chip based on flash technique, net table transform software mainly solves the time sequence difference of antifuse chip and prototype adapter flash chip, makes both sequential couplings, carries out the pin conversion of two kinds of chips simultaneously.After completing the prototype verification in antifuse chip early stage, just can fall real antifuse chip weldering, and completely the same owing to encapsulating, Beamsteering Unit 3, without the need to correcting, highly shortened the construction cycle, reduces design risk.
As shown in Figure 6, the A/D conversion chip of the present embodiment selects TLC2543 as A/D conversion chip, and use simple, hard wires is few.Anti-fuse FPGA chip output chip selects the control signal such as AD_/CS1, clock AD_CLK1 and serial data AD_DATAIN1, the highest 4.1MHZ that is no more than of clock, and serial data comprises channel selecting and data bit width, can the external analog amount input of acquisition time 11 tunnel.A/D conversion chip be mainly used in multiple voltage on antenna array measurement, comprise the temperature of C-band T/R assembly power supply-5V, 9V, L-band T/R assembly power supply-5V ,+5V, 28V and antenna array.Each Beamsteering Unit 3 uses 2 A/D conversion chips, the serial data AD_DATAOUT1 collected is sent into anti-fuse FPGA chip, in anti-fuse FPGA chip, complete all state informations (comprise A/D data, the BIT state of each assembly, the checksum error of beam-control code, sequential combination fault) integrated, beam guidance computer 2 is uploaded to according to the agreement of regulation, after beam guidance computer 2 collects the state information of 54 Beamsteering Unit 3 respectively, obtain whole antenna array supply voltage, temperature, each component states, check sum mistake and sequential combination fault etc.
In order to improve the reliability of Signal transmissions, increase the antijamming capability of signal, Signal transmissions between unit is (between beam guidance computer 2 and Beamsteering Unit 3, between Beamsteering Unit 3 and T/R assembly) adopt RS422 level transmissions, it is fast that RS422 has transmission speed, long transmission distance, antijamming capability is strong, can the advantage such as bus connection.
As shown in Figure 7, DS96F175 is differential received chip, READY+/READY-, SYN+/SYN-, CLK+/CLK-, DATA1+/DATA1-are differential input signals, be connected with beam guidance computer 2 with twisted-pair feeder, because beam guidance computer 2 adopts RS422 bus connecting mode to drive 6 pieces of Beamsteering Unit 3 simultaneously, and transmission range is comparatively far away, so being connected in series 1K resistance R77 ~ 84 respectively near DS96F175 chip signal end, alleviate load.240 Ω build-out resistor R91 ~ 94 in parallel between positive negative differential signal, positive end signal pull-up 10K resistance R100 ~ 103 to+5V, negative terminal drop-down 10K resistance R109 ~ 112 to GND.
As shown in Figure 8, DS96F174 is that differential signal sends chip, DATA1-C, DATA2-C, DATA3-C, DATA4-C are the data-signal that Beamsteering Unit 3 is sent to C-band assembly, are connected in series current-limiting resistance R216 ~ 223 of 56 Ω at output signal end DATA1-C+/DATA1-C-, DATA2-C+/DATA2-C-, DATA3-C+/DATA3-C-, DATA4-C+/DATA4-C-respectively.
As shown in Figure 9, need+9V power supply during C-band T/R component operation, pulsed operation, the duty ratio of pulse is about about 10%, during external emittance, needs larger transient current.Two C-band secondary power supplies need three groups of fuse circuits and storage capacitor respectively.Therefore, often group fuse circuit and storage capacitor need to provide Large Copacity storage capacitor C103, C104, C105 at+9V, for preventing storage capacitor short-circuit failure, add fuse circuit F3, F4 in the front end of storage capacitor.Adopt two fuse circuit parallel connections, improve reliability.Wherein a road uses high-power 120m Ω resistance R287 to connect, and be no more than 10% of way circuit by the electric current of R287 under normal condition, thus F4 branch road has larger anti-surge ability.When load generation temporary over-current, first F3 fuses, and F4 branch road still maintains path.
As shown in Figure 10, TR_R_C and TR_T_C is receive path control impuls and the transmission channel control impuls of C-band assembly, TR_R_L and TR_T_L is receive path control impuls and the transmission channel control impuls of L-band assembly, Beamsteering Unit 3 is at CLK trailing edge image data DATA1, data are transmitted between SYN low period, after the rising edge of SYN completes data receiver, start check sum inspection, check errorless after, extract the T/R beam-control code of each passage, then within the Tdis time cycle, send data to each T/R assembly simultaneously, after T/R assembly completes beam-control code reception, when REDAY low level, new beam position comes into force.DATA2 is the digital telemetering data of Beamsteering Unit 3, and between FLAG low period, CLK rising edge transfers data to beam guidance computer 2.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, all any amendments done within the spirit and principles in the present invention, equivalent replacement and improvement etc., all should be included within protection scope of the present invention.
Claims (10)
1. a spaceborne massive phased array antenna beam control device, it is characterized in that, comprise satellite platform number pipe computer, beam guidance computer, multiple Beamsteering Unit, C-band T/R assembly, C-band time delay amplifier module, L-band T/R assembly and L-band time delay amplifier module, described satellite platform number pipe computer is by beam position data (β, α) send to beam guidance computer, described beam guidance computer obtains beam-control code according to beam position bearing data, and beam-control code is sent to each Beamsteering Unit together with work schedule, after described each Beamsteering Unit receives beam-control code and work schedule, checksum validation is carried out to beam-control code, the beam-control code of each T/R assembly is added up mutually, compared with the check code that the cumulative check code obtained and Beamsteering Unit receive, if conformed to, then by the beam-control code of respective channel and work schedule extraction and according to after the data format requirement restructuring of each assembly, then the C-band T/R assembly that this Beamsteering Unit is corresponding is forwarded to, C-band time delay amplifier module, L-band T/R assembly and L-band time delay amplifier module, after each T/R assembly receives beam-control code, carry out serioparallel exchange, each code value is given phase shifter and the attenuator of controlled device, according to work schedule requirement, the beam position completing whole antenna array switches.
2. one according to claim 1 spaceborne massive phased array antenna beam control device, it is characterized in that, described beam-control code is: according to beam pointing-angle, calculate the phase shift code of each phase shifter on antenna array, the decay code of attenuator, the time delay code of time delay amplifier, and be added with the check code that antenna array obtains in power up initialization process, eliminate the inconsistency of each passage, finally obtain the time delay code of the phase shift code of each phase shifter, the decay code of attenuator and delay line, be referred to as beam-control code.
3. one according to claim 1 spaceborne massive phased array antenna beam control device, it is characterized in that, described Beamsteering Unit comprises anti-fuse FPGA chip, A/D conversion chip, differential signal input and output driver module, many group fuse circuits and storage capacitor, described differential signal input and output driver module comprises differential receive circuitry and difference transtation mission circuit, described anti-fuse FPGA chip receives beam-control code by differential receive circuitry from beam guidance computer, the temperature data of the C-band power supply gathered and L-band power supply and antenna array diverse location is sent into anti-fuse FPGA chip by A/D conversion chip, described anti-fuse FPGA chip carries out prefix differentiation, School Affairs checks, if all correct, the data of each T/R passage are extracted again from the beam-control code received, according to C-band assembly, L-band module data protocol requirement, splicing and the restructuring of data is completed at anti-fuse FPGA chip internal, finally the beam-control code of each passage is sent to corresponding T/R assembly according to timeticks serial, state information is uploaded to beam guidance computer by difference transtation mission circuit according to the agreement of regulation by anti-fuse FPGA chip, many groups fuse circuit is connected on+9V the power supply of C-band T/R assembly successively, storage capacitor is connected in parallel on+9V the power supply of C-band T/R assembly.
4. one according to claim 3 spaceborne massive phased array antenna beam control device, is characterized in that, described beam-control code data send at the trailing edge of clock, and T/R assembly gathers serial data at the rising edge of clock.
5. one according to claim 3 spaceborne massive phased array antenna beam control device, it is characterized in that, the prototype verification method of described anti-fuse FPGA chip is as follows: first generate net meter file to the compiling of antifuse device design document, then the net meter file of generation is converted to the net table of the ProAsic chip based on flash technique, the sequential of antifuse chip and prototype adapter flash chip is mated, carries out the pin conversion of two kinds of chips simultaneously.
6. one according to claim 5 spaceborne massive phased array antenna beam control device, is characterized in that, the model of described anti-fuse FPGA chip is A54SX72A-CQ208B.
7. one according to claim 3 spaceborne massive phased array antenna beam control device, it is characterized in that, described Beamsteering Unit totally 54, beam guidance computer and whole antenna array amount to 9 interfaces, each interface connects 6 Beamsteering Unit, each Beamsteering Unit controls 12 C-band T/R assemblies, 4 C-band time delay amplifier modules, 8 L-band T/R assemblies and 4 L-band time delay amplifier modules, 12 C-band T/R assemblies are divided into 4 groups, often group comprises 3 C-band T/R assemblies and 1 C-band time delay amplifier module, 8 L-band T/R assemblies are divided into 2 groups, often group comprises 4 L-band T/R assemblies and 2 L-band time delay amplifier modules.
8. one according to claim 3 spaceborne massive phased array antenna beam control device, it is characterized in that, described each Beamsteering Unit and adopt RS422 differential bus mode to transmit data between beam guidance computer and each T/R assembly, one is adopted to drive many connected modes, namely source one road signal is sent, drive multipath reception end, connect build-out resistor in distalmost end.
9. one according to claim 3 spaceborne massive phased array antenna beam control device, it is characterized in that, described A/D conversion chip has two, select TLC2543 as A/D conversion chip, one in order to gather the temperature of C-band T/R assembly power supply-5V, 9V and each position of antenna array, another is in order to gather L-band T/R assembly power supply-5V ,+5V, 28V.
10. one according to claim 3 spaceborne massive phased array antenna beam control device; it is characterized in that; described often group fuse circuit and storage capacitor comprise two fuse protective circuits and three Large Copacity storage capacitors; fuse circuit is connected on C-band T/R assembly+9V power supply; three Large Copacity storage capacitors are connected in parallel on C-band T/R assembly+9V power supply; in described two fuse protective circuits, in parallel with another fuse protective circuit again after one of them fuse protective circuit series connection high-power resistance.
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