CN104617390B - A kind of spaceborne massive phased array antenna beam control device - Google Patents
A kind of spaceborne massive phased array antenna beam control device Download PDFInfo
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- CN104617390B CN104617390B CN201510073210.8A CN201510073210A CN104617390B CN 104617390 B CN104617390 B CN 104617390B CN 201510073210 A CN201510073210 A CN 201510073210A CN 104617390 B CN104617390 B CN 104617390B
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Abstract
The invention discloses a kind of spaceborne massive phased array antenna beam control device, satellite platform number pipe computer is by beam position data is activation to beam guidance computer, the beam guidance computer obtains beam-control code according to beam position data, and beam-control code and work schedule are sent collectively to into each Beamsteering Unit, after described each Beamsteering Unit receives beam-control code and work schedule, checksum validation is carried out to beam-control code, phase shifter and the attenuator of controlled device are given by each code value, require according to work schedule, complete the beam position switching of whole antenna array.Present invention achieves phased array antenna is crossed the application of satellite platform by ground surface platform, the wave beam electric scanning control of two-dimentional massive phased array is completed.Can be widely applied to telecommunication satellite, measurement satellite and reconnaissance satellite etc. field.With small size, low weight, highly reliable feature, it is long to meet the electronic equipment on satellite operation on orbit time, not maintainable requirement.
Description
Technical field
The present invention relates to a kind of satellite antenna load observation and control technology, more particularly to 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 countermeasure.Phased array day
The ultimate principle of linear system system transmitting and is received the amplitude and phase place of signal and carries out in each array element to phased-array antenna array
Control so that in the specific direction of the beam position of space combination, or null is formed in some specific directions.With wave beam
The advantages of sensing is flexible, directional diagram can be comprehensive.
Phased array antenna overcomes that mechanical means rotable antenna inertia is big, slow-footed shortcoming, is presented using computer controls
Electric phase place, pace of change are fast (Millisecond), and control is flexible, big system can be coordinated to complete multiple-working mode, reasonably by antenna
The energy of radiation is maximally utilized in space, improves the task performance of big system.Because of the huge advantage of phased array antenna, Yi Ji
Phased array antenna in recent years, is also gradually applied to satellite platform by the maturation application of ground radar and airborne platform, and
Developed from the bay of small-scale to large-scale antenna array.But due to the environment residing for satellite platform and ground and low
Hollow panel is entirely different, particularly faces Energetic particle radiation, the impact of cosmic ray, and electronic equipment easily produces ionization
Total dose damage, various single particle effects are (such as：In single-particle inversion, single-ion transient state, single event latch-up, simple grain subfunction
It is disconnected), cause electronic functionalities not normal, or even produce permanent failure.Simultaneously space electronic equipment also requires low weight, little
Volume, low heat dissipation design.Require in-orbit reliably working, non-maintaining in life cycle.Therefore, it is used for phased array day in ground surface platform
The Beamsteering Unit of line has not met the use requirement of spaceborne environment completely.
The content of the invention
It is an object of the invention to overcome the deficiencies in the prior art, there is provided a kind of spaceborne massive phased array antenna beam control
Device processed, can adapt to Energetic particle radiation, avoids the discharge and recharge of electronic equipment surface.
The present invention is achieved by the following technical solutions, and the present invention includes satellite platform number pipe computer, wave beam control
Computer, multiple Beamsteering Units, C-band T/R components, C-band time delay amplifier module, L-band T/R components and L-band prolong
When amplifier module；Beam position data (β, α) are sent to beam guidance computer by the satellite platform number pipe computer, described
Beam guidance computer obtains beam-control code according to beam position bearing data, and beam-control code and work schedule are sent collectively to respectively
Individual Beamsteering Unit, after described each Beamsteering Unit receives beam-control code and work schedule, verifies to beam-control code
And checking, the beam-control code of each T/R component is mutually added up, the verification that the cumulative check code for obtaining is received with Beamsteering Unit
Code-phase compares, if be consistent, the beam-control code of respective channel and work schedule is extracted and according to the data form of each component
After requiring restructuring, the corresponding C-band T/R components of the Beamsteering Unit, C-band time delay amplifier module, L-band are subsequently forwarded to
T/R components and L-band time delay amplifier module, after each T/R component receives beam-control code, carry out serioparallel exchange, by each code value
Phase shifter and the attenuator of controlled device are given, is required according to work schedule, complete the beam position switching of whole antenna array.
The beam-control code is：According to beam pointing-angle, phase shift code, the attenuator of each phase shifter on antenna array are calculated
Decay code, the time delay code of time delay amplifier, and be added with the check code that antenna array is obtained in power up initialization process, disappear
Except the discordance of each passage, the phase shift code of each phase shifter, the decay code of attenuator and the time delay of delay line are finally obtained
Code, is referred to as beam-control code.
The Beamsteering Unit includes that anti-fuse FPGA chip, A/D conversion chips, differential signal input and output drive mould
Block, multigroup fuse circuit and storage capacitor；The differential signal input and output drive module includes differential received circuit and difference
Transtation mission circuit, the anti-fuse FPGA chip is divided to receive beam-control code from beam guidance computer by differential received circuit, A/D turns
Change chip and the temperature data of the C-band power supply for gathering and L-band power supply and antenna array diverse location is sent into into anti-fuse FPGA
Chip, the anti-fuse FPGA chip carry out prefix differentiation, verification and check, if it is all correct, then from the ripple for receiving
The data of each T/R passage are extracted in control code, according to C-band component, L-band module data protocol requirement, in anti-fuse FPGA
Chip internal completes the splicing and restructuring of data, and finally the beam-control code of each passage is sent to correspondence according to timeticks serial
T/R components, anti-fuse FPGA chip according to regulation agreement status information is uploaded to into wave beam control by difference transtation mission circuit
Computer processed, multigroup fuse circuit are sequentially connected in series on+9V the power supplys of C-band T/R components, and storage capacitor is connected in parallel on C-band
On+9V the power supplys of T/R components.
The beam-control code data are sent in the trailing edge of clock, rising edge collection serial data of the T/R components in clock.
The prototype verification method of the anti-fuse FPGA chip is as follows：First the compiling of antifuse device design document is generated
Net meter file, then the net meter file of generation is converted into the netlist of the ProAsic chips based on flash techniques so that anti-molten
The sequential coupling of silk chip and prototype adapter flash chip, while carrying out the pin conversion of two kinds of chips.Complete antifuse core
After the prototype verification of piece early stage, it is possible to which real antifuse chip falls to being soldered on circuit board.Due to encapsulating completely the same, ripple
Beam control unit highly shortened the construction cycle, reduce design risk without the need for correcting.
Model A54SX72A-CQ208B of the anti-fuse FPGA chip.
The Beamsteering Unit totally 54, beam guidance computer amount to 9 interfaces with whole antenna array, and each connects
Mouth 6 Beamsteering Units of connection, each Beamsteering Unit control 12 C-band T/R components, 4 C-band time delay amplification groups
12 C-band T/R components are divided into 4 groups by part, 8 L-band T/R components and 4 L-band time delay amplifier modules, and per group includes 3
8 L-band T/R components are divided into 2 groups by individual C-band T/R components and 1 C-band time delay amplifier module, and per group includes 4 L ripples
Section T/R components and 2 L-band time delay amplifier modules.
It is total using RS422 difference between described each Beamsteering Unit and beam guidance computer and each T/R component
Line mode transmission data, drives many connected modes, i.e. transmission source port signal all the way using one, drives multipath reception end, farthest
Hold and connect build-out resistor.
The A/D conversion chips have two, and from TLC2543 as A/D conversion chips, one to gather C-band T/R
The temperature of component power supply -5V, 9V and each position of antenna array, another to gather L-band T/R component power supply -5V ,+5V,
28V。
Every group of fuse circuit and storage capacitor include two electric fuse protection circuits and three Large Copacity energy storage electricity
Hold, fuse circuit is connected on C-band T/R component+9V power supplys, and three Large Copacity storage capacitors are connected in parallel on C-band T/R components
On+9V power supplys, in described two electric fuse protection circuits, after one of electric fuse protection circuit series connection high-power resistance again
It is in parallel with another electric fuse protection circuit.
The present invention has advantages below compared to existing technology：Present invention achieves phased array antenna is crossed by ground surface platform
The application of satellite platform, completes the wave beam electric scanning control of two-dimentional massive phased array.The present invention is disclosure satisfy that in rocket firing
The strenuous vibration in the stage of liter, under spatial complex environment, particularly Energetic particle radiation, reliability application under vacuum condition are whole
Individual Beamsteering Unit board design, production and paster are selected with radioprotective index in strict accordance with aerospace processing flow process
High-quality level device, adopts two point two-wire, ic power without connection cables between isolated large-area metal conductor, unit
Metal reinforcing, the device conducts radiating more than 300mw, surface mounting component is added to need dispensing to fix on end plus current-limiting resistance, plate.Star
Massive phased array antenna beam control unit is carried, telecommunication satellite, measurement satellite and reconnaissance satellite etc. field is can be widely applied to.Tool
There are small size, low weight, highly reliable feature, it is long to meet the electronic equipment on satellite operation on orbit time, not maintainable requirement.
Description of the drawings
Fig. 1 is whole antenna array three-level wave beam control flow block diagram；
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 components and time delay amplifier；
Fig. 4 is the composition frame chart of Beamsteering Unit；
Fig. 5 is ACTEL anti-fuse FPGA prototype verification flow charts in Fig. 4；
Fig. 6 is the schematic diagram of A/D conversion chips in Fig. 4；
Fig. 7 is RS422 differential signal receiving circuit schematic diagrams in Fig. 4；
Fig. 8 is RS422 differential signal transtation mission circuit schematic diagrams in Fig. 4；
Fig. 9 is Large Copacity storage capacitor and electric fuse protection circuit schematic diagram in Fig. 4；
Figure 10 is the communication succession schematic diagram of Beamsteering Unit and ripple control computer in Fig. 4.
Specific embodiment
Below embodiments of the invention are elaborated, the present embodiment is carried out under premised on technical solution of the present invention
Implement, give detailed embodiment and specific operating process, but protection scope of the present invention is not limited to following enforcements
Example.
As shown in figure 1, the present embodiment includes satellite platform number pipe computer 1, beam guidance computer 2, multiple wave beam controls
Unit processed 3, C-band and the L-band T/R components 4, phase shifter of controlled device and attenuator；C-band and L-band T/R components 4 are wrapped
Include C-band T/R components, C-band time delay amplifier module, L-band T/R components and L-band time delay amplifier module；The satellite platform
Beam position data (β, α) are sent to beam guidance computer 2 by number pipe computer 1, and the beam guidance computer 2 is according to ripple
Shu Zhixiang bearing datas are calculated beam-control code according to bidimensional rectangular grid phased array antenna principle, and by when beam-control code and work
Sequence is sent collectively to 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 component is mutually added up, the cumulative check code for obtaining is controlled with wave beam
The check code that unit 3 is received compares, if be consistent, the beam-control code of respective channel and work schedule is extracted and according to each
After the data format requirement restructuring of individual component, 3 corresponding C-band T/R components of Beamsteering Unit, the C-band is subsequently forwarded to
Time delay amplifier module, L-band T/R components and L-band time delay amplifier module, after each T/R component receives beam-control code, are gone here and there
And change, phase shifter and the attenuator of controlled device are given by each code value, require according to work schedule, complete whole antenna array
The beam position switching in face.Beam-control code is：According to beam pointing-angle, calculate according to bidimensional rectangular grid phased array antenna principle
The phase shift code of each phase shifter, the decay code of attenuator, the time delay code of time delay amplifier on antenna array, and exist with antenna array
The check code obtained in power up initialization process is added, and eliminates the discordance of each passage, finally obtains each phase shifter
Phase shift code, the decay code of attenuator and the time delay code of delay line, are referred to as beam-control code.
As shown in Fig. 2 beam guidance computer 2 amounts to 9 interfaces with whole phased array antenna, each interface connects 6
Beamsteering Unit 3, by taking an interface of beam guidance computer 2 as an example, data wire DATA0～DATA5 is independently operated, can be simultaneously
Row transmission data.Other ripple control instruction inputs：TR_R_C、TR_T_C、TR_R_L、TR_T_L、CLK、SYN、READY.Numeral is distant
Survey：FLAG, DATA2 are using " one drives six " RS422 bus modes connection.
As shown in figure 3, the Beamsteering Unit 3 totally 54 of whole antenna array, beam guidance computer 2 and whole antenna
Front amounts to 9 interfaces, and each interface connects 6 Beamsteering Units 3, by taking a Beamsteering Unit 3 as an example, a wave beam
Control unit 3 controls 12 C-band T/R components, 4 C-band time delay amplifier modules, 8 L-band T/R components and 4 L-bands
Time delay amplifier module, the signal connected between Beamsteering Unit 3 and T/R components include TR_T, TR_R, DATA, CLK, SYN,
READY、BITE.Only DATA signal will transmit different beam-control codes, and other signals can be according to RS422 shared buses
Connected mode, in order to reduce the weight of connection cables between Beamsteering Unit 3 and component, 12 C-band T/R components is divided into
4 groups, per group includes 3 C-band T/R components and 1 C-band time delay amplifier module, share TR_T, TR_R, CLK, SYN,
READY、BITE.8 L-band T/R components are divided into into 2 groups, per group includes that 4 L-band T/R components and 2 L-band time delays are amplified
Component.
As shown in figure 4, Beamsteering Unit 3 includes that anti-fuse FPGA chip, A/D conversion chips, differential signal input are defeated
Go out drive module, multigroup fuse circuit and storage capacitor；The differential signal input and output drive module includes differential received
Circuit and difference transtation mission circuit, the anti-fuse FPGA chip is by differential received circuit from 2 received wave of beam guidance computer
The temperature data of the C-band power supply for gathering and L-band power supply and antenna array diverse location is sent into by control code, A/D conversion chips
Anti-fuse FPGA chip, the anti-fuse FPGA chip carry out prefix differentiation, verification and check, if it is all correct, then from
The data of each T/R passage are extracted in the beam-control code for receiving, according to C-band component, L-band module data protocol requirement,
Anti-fuse FPGA chip internal completes the splicing and restructuring of data, finally by the beam-control code of each passage according to timeticks serial
Sent to corresponding T/R components by difference interface circuit, status information is led to by anti-fuse FPGA chip according to the agreement of regulation
Cross difference transtation mission circuit and upload to beam guidance computer 2, fuse circuit is connected on C-band T/R component+9V power supplys, store up
Energy electric capacity is connected in parallel on C-band T/R component+9V power supplys.Beam-control code data are sent in the trailing edge of clock, and T/R components are in clock
Rising edge collection serial data, it is ensured that data correctly can be obtained.
It is divided into two kinds of ripple control instruction input, digital telemetering with 2 interface signal of upper level beam guidance computer.Ripple control is instructed
Input：T TR_R_C、TR_T_C、TR_R_L、TR_T_L、CLK、DATA、SYN、READY.Digital telemetering：FLAG、DATA2.Its
Middle TR_T_C, TR_T_L are the emission control pulse of C-band component and L-band component, and TR_R_C, TR_R_L are C-band component
Reception control pulse with L-band component.Beam-control code is sent to Beamsteering Unit 3 by CLK, DATA, SYN, when when ripple
After beam control unit 3 completes the distribution of all T/R module datas, the beam position of antenna array is refreshed by READY signal.
Output interfaces of the DATA2 for antenna array telemetry, exports antenna subsystem number by DATA2 under FLAG and CLK controls
Word telemetry is to beam guidance computer 2.
FPGA is the core devices of Beamsteering Unit 3, and its stability directly affects the control of antenna beam.Current FPGA
Mainly there are 3 types, based on SRAM type, FLASH types and anti-fuse type.Under spaceborne high rail environment, it is total that FPGA is faced with ionization
The space radiation problem such as dosage, single-particle inversion, locking single particle, SRAM type FPGA are easiest to produce single-particle inversion
(Single Event Upset SEU) although, FLASH type FPGA reliabilities it is higher than SRAM type, space simple grain can not be avoided
The variety of problems of sub- effect.Anti-fuse type FPGA is that most suitable aeronautical field is used, and is not had with other structures FPGA device
Some height reliabilities and stability, anti-fuse FPGA have Radiation hardness strong, power-on time is short, it is low in energy consumption the features such as,
Antifuse chip is fully verified in many satellite successful Applications, reliability.But anti-fuse FPGA has disposable burning simultaneously
Write, not reproducible programming, the less feature of device capacitance.Therefore, before programming anti-fuse FPGA design function checking, when
Sequence is verified and calculation of natural resources is extremely important.The present embodiment is using the common release of ALDEC companies and Actel companies based on Actel
The antifuse device prototype verification solution of ProAsic devices.Anti-fuse FPGA core of the present embodiment from ACTEL companies
Piece, model A54SX72A-CQ208B, anti-fuse FPGA chip prototype verification flow process is as shown in figure 5, to use ALDEC public
The antifuse adapter of department, model：I-ACT-RTSXi-CQ208.First in the Libero software development environments of ACTEL,
From antifuse device A54SX72A-CQ208B, net meter file is generated to design document compiling, then with the net of ALDEC companies
The netlist of A54SX72A-CQ208B device generations is converted into the ProAsic chips based on flash techniques by table switching software
Netlist, netlist conversion software mainly solve the time sequence difference of antifuse chip and prototype adapter flash chip, make both sequential
Matching, while carrying out the pin conversion of two kinds of chips.After completing the prototype verification of antifuse chip early stage, it is possible to will be real
Antifuse chip falls to welding, completely the same due to encapsulating, and Beamsteering Unit 3 highly shortened construction cycle, drop without the need for correcting
Low design risk.
As shown in fig. 6, the A/D conversion chips of the present embodiment select TLC2543 as A/D conversion chips, use simply, firmly
Part line is few.Anti-fuse FPGA chip output chip selects AD_/CS1, clock AD_CLK1 and serial data AD_DATAIN1 etc. to control
Signal, clock not more than 4.1MHZ, serial data include channel selecting and data bit width, can be with 11 tunnel of acquisition time outside
Analog input.A/D conversion chips are mainly used in the measurement of multiple voltage on antenna array, including C-band T/R components electricity
Source -5V, 9V, the temperature of L-band T/R component power supply -5V ,+5V, 28V and antenna array.Each Beamsteering Unit 3 uses 2
Serial data AD_DATAOUT1 for collecting is sent into anti-fuse FPGA chip, in anti-fuse FPGA chip by A/D conversion chips
Inside completing all status informations (includes A/D data, the BIT states of each component, the checksum error of beam-control code, sequential combination
Failure) it is integrated, beam guidance computer 2 is uploaded to according to the agreement of regulation, beam guidance computer 2 collects 54 wave beams respectively
After the status information of control unit 3, whole antenna array supply voltage, temperature, each component states, data check and mistake are obtained
Mistake and sequential combination failure etc..
In order to improve the reliability of signal transmission, increase the capacity of resisting disturbance of signal, the signal transmission (wave beam between unit
Between control computer 2 and Beamsteering Unit 3, between Beamsteering Unit 3 and T/R components) transmitted using RS422 level,
RS422 has transmission speed fast, long transmission distance, strong antijamming capability, can the advantage such as bus connection.
As shown in fig. 7, DS96F175 be differential received chip, READY+/READY-, SYN+/SYN-, CLK+/CLK-,
DATA1+/DATA1- is differential input signal, is connected with beam guidance computer 2 with twisted-pair feeder, because beam guidance computer 2
6 pieces of Beamsteering Units 3 are driven simultaneously using RS422 bus connecting modes, and transmission range is farther out, so close
DS96F175 chip signals end concatenates 1K resistance R77～84 respectively, mitigates load.240 Ω matchings in parallel between positive negative differential signal
Resistance R91～94, positive end signal pull up 10K resistance R100～103 to+5V, drop-down 10K resistance R109～112 to the GND of negative terminal.
As shown in figure 8, DS96F174 is differential signal sends chip, DATA1-C, DATA2-C, DATA3-C, DATA4-C
Send for Beamsteering Unit 3 to the data signal of C-band component, in output signal end DATA1-C+/DATA1-C-, DATA2-
C+/DATA2-C-, DATA3-C+/DATA3-C-, DATA4-C+/DATA4-C- concatenate respectively the current-limiting resistance R216 of 56 Ω～
223。
As shown in figure 9 ,+9V power supplys are needed during C-band T/R component operations, pulsed operation, the dutycycle of pulse are about
10% or so, during external emittance, need larger transient current.Two C-band secondary power supplies are respectively necessary for three groups of insurances
Silk circuit and storage capacitor.Therefore, every group of fuse circuit and storage capacitor need to provide Large Copacity storage capacitor in+9V
C103, C104, C105, to prevent storage capacitor short-circuit failure, add fuse circuit F3, F4 in the front end of storage capacitor.Using
Two fuse circuit parallel connections, improve reliability.Wherein connected using high-power 120m Ω resistance R287 all the way, under normal condition
By the electric current of R287 less than the 10% of way circuit, thus F4 branch roads have larger anti-surge ability.When load occurs
During temporary over-current, F3 is fused first, and F4 branch roads still maintain path.
As shown in Figure 10, TR_R_C and TR_T_C are the receiving channel control pulses and transmission channel control of C-band component
Pulse, TR_R_L and TR_T_L are the receiving channel control pulse of L-band component and transmission channel control pulse, and wave beam controls single
Unit 3 completes data receiver in the rising edge of SYN in CLK trailing edge gathered datas DATA1, transmission data between SYN low periods
Afterwards, start data check and inspection, check it is errorless after, extract the T/R beam-control codes of each passage, then within the Tdis time cycles
Send data to each T/R component simultaneously, after T/R components complete beam-control code to be received, in REDAY low levels, new ripple
Shu Zhixiang comes into force.Digital telemetering data of the DATA2 for Beamsteering Unit 3, between FLAG low periods, the transmission of CLK rising edges
Data are to beam guidance computer 2.
Presently preferred embodiments of the present invention is the foregoing is only, not to limit the present invention, all essences in the present invention
Any modification, equivalent and improvement made within god and principle etc., should be included within the scope of the present invention.
Claims (9)
1. a kind of spaceborne massive phased array antenna beam control device, it is characterised in that including satellite platform number pipe computer, ripple
Beam control computer, multiple Beamsteering Units, C-band T/R components, C-band time delay amplifier module, L-band T/R components and L
Wave band time delay amplifier module；Beam position data (β, α) are sent to wave beam control and are calculated by the satellite platform number pipe computer
Machine, the beam guidance computer obtain beam-control code according to beam position bearing data, and by beam-control code and work schedule together
Each Beamsteering Unit is sent to, after described each Beamsteering Unit receives beam-control code and work schedule, to beam-control code
Checksum validation is carried out, the beam-control code of each T/R component is mutually added up, the cumulative check code for obtaining is received with Beamsteering Unit
To check code compare, if be consistent, the beam-control code of respective channel and work schedule are extracted and according to each component
After data format requirement restructuring, the corresponding C-band T/R components of the Beamsteering Unit, C-band time delay amplification group are subsequently forwarded to
Part, L-band T/R components and L-band time delay amplifier module, after each T/R component receives beam-control code, carry out serioparallel exchange, will
Each code value gives the phase shifter of controlled device and attenuator, requires according to work schedule, completes the wave beam of whole antenna array
Point to switching；
The Beamsteering Unit include anti-fuse FPGA chip, A/D conversion chips, differential signal input and output drive module,
Multigroup fuse circuit and storage capacitor；The differential signal input and output drive module includes that differential received circuit and difference are sent out
Power transmission road, the anti-fuse FPGA chip receive beam-control code, A/D conversion core from beam guidance computer by differential received circuit
The temperature data of the C-band power supply for gathering and L-band power supply and antenna array diverse location is sent into anti-fuse FPGA chip by piece,
The anti-fuse FPGA chip carries out prefix differentiation, verification and checks, if it is all correct, then from the beam-control code for receiving
The data of each T/R passage are extracted, according to C-band component, L-band module data protocol requirement, in anti-fuse FPGA chip
Portion completes the splicing and restructuring of data, and finally the beam-control code of each passage is sent to corresponding T/R according to timeticks serial
Status information is uploaded to wave beam control by difference transtation mission circuit according to the agreement of regulation and is calculated by component, anti-fuse FPGA chip
Machine, multigroup fuse circuit are sequentially connected in series on+9V the power supplys of C-band T/R components, and storage capacitor is connected in parallel on C-band T/R components
+ 9V power supplys on.
2. a kind of spaceborne massive phased array antenna beam control device according to claim 1, it is characterised in that the ripple
Control code is：According to beam pointing-angle, the phase shift code of each phase shifter on antenna array, the decay code of attenuator, time delay are calculated
The time delay code of amplifier, and be added with the check code that antenna array is obtained in power up initialization process, eliminate each passage
Discordance, finally obtains the phase shift code of each phase shifter, the decay code of attenuator and the time delay code of delay line, is referred to as ripple control
Code.
3. a kind of spaceborne massive phased array antenna beam control device according to claim 1, it is characterised in that the ripple
Control code data are sent in the trailing edge of clock, rising edge collection serial data of the T/R components in clock.
4. a kind of spaceborne massive phased array antenna beam control device according to claim 1, it is characterised in that described anti-
The prototype verification method of fuse fpga chip is as follows：Net meter file is generated to the compiling of antifuse device design document first, then
The net meter file of generation is converted into into the netlist of the ProAsic chips based on flash techniques so that antifuse chip and prototype are suitable
The sequential coupling of orchestration flash chip, while carrying out the pin conversion of two kinds of chips.
5. a kind of spaceborne massive phased array antenna beam control device according to claim 4, it is characterised in that described anti-
Model A54SX72A-CQ208B of fuse fpga chip.
6. a kind of spaceborne massive phased array antenna beam control device according to claim 1, it is characterised in that the ripple
Beam control unit totally 54, beam guidance computer amount to 9 interfaces with whole antenna array, and each interface connects 6 wave beams
Control unit, each Beamsteering Unit control 12 C-band T/R components, 4 C-band time delay amplifier modules, 8 L-band T/
12 C-band T/R components are divided into 4 groups by R components and 4 L-band time delay amplifier modules, and per group includes 3 C-band T/R components
With 1 C-band time delay amplifier module, 8 L-band T/R components are divided into into 2 groups, per group includes 4 L-band T/R components and 2 L
Wave band time delay amplifier module.
7. a kind of spaceborne massive phased array antenna beam control device according to claim 1, it is characterised in that described every
RS422 differential bus mode transmission datas are adopted between individual Beamsteering Unit and beam guidance computer and each T/R component,
Many connected modes, i.e. transmission source port signal all the way is driven using one, multipath reception end is driven, in distalmost end and build-out resistor is connect.
8. a kind of spaceborne massive phased array antenna beam control device according to claim 1, it is characterised in that the A/
D conversion chips have two, and from TLC2543 as A/D conversion chips, one to gather C-band T/R component power supply -5V, 9V
With the temperature of each position of antenna array, another is to gather L-band T/R component power supply -5V ,+5V, 28V.
9. a kind of spaceborne massive phased array antenna beam control device according to claim 1, it is characterised in that described every
Group fuse circuit and storage capacitor include two electric fuse protection circuits and three Large Copacity storage capacitors, fuse circuit string
It is associated on C-band T/R component+9V power supplys, three Large Copacity storage capacitors are connected in parallel on C-band T/R component+9V power supplys, described
In two electric fuse protection circuits, after one of electric fuse protection circuit series connection high-power resistance again with another electric fuse
Protection circuit is in parallel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510073210.8A CN104617390B (en) | 2015-02-11 | 2015-02-11 | A kind of spaceborne massive phased array antenna beam control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510073210.8A CN104617390B (en) | 2015-02-11 | 2015-02-11 | A kind of spaceborne massive phased array antenna beam control device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104617390A CN104617390A (en) | 2015-05-13 |
| CN104617390B true CN104617390B (en) | 2017-03-29 |
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| CN106773957A (en) * | 2016-12-16 | 2017-05-31 | 中国电子科技集团公司第三十八研究所 | It is a kind of be applied to airborne radar countermeasure system detect receipts beam steering system and method |
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| CN109830805B (en) * | 2019-03-19 | 2020-09-11 | 北京遥感设备研究所 | Satellite-borne phased array antenna beam control circuit |
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| CN112259964B (en) * | 2020-09-28 | 2022-09-02 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Multi-subarray phased array antenna beam control device |
| CN112332112B (en) * | 2020-10-28 | 2023-03-28 | 成都天锐星通科技有限公司 | Phased array antenna |
| CN112596030B (en) * | 2020-12-04 | 2023-12-01 | 南京理工大学 | Wave control method and system based on X-band unmanned aerial vehicle SAR |
| CN115000704B (en) * | 2022-06-22 | 2024-04-12 | 中国电子科技集团公司第二十九研究所 | Hierarchical calculation two-dimensional phased array beam control method and system |
| CN115167256A (en) * | 2022-09-05 | 2022-10-11 | 江苏万邦微电子有限公司 | TR component beam control module based on built-in data check |
| CN116094579B (en) * | 2023-04-07 | 2023-06-30 | 湖南鲸瓴智联信息技术有限公司 | High-low speed cooperative low-orbit satellite communication system and method |
| CN117134792A (en) * | 2023-10-26 | 2023-11-28 | 南京纳特通信电子有限公司 | K-band phased array wave control system based on FPGA control |
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