CN109742843A

CN109742843A - A kind of power supply and distribution Reconfigurable Control system and method towards mass flight validation

Info

Publication number: CN109742843A
Application number: CN201811608467.9A
Authority: CN
Inventors: 张绍林; 胡洪凯; 肖爱斌; 刘迎辉; 张洪伟; 刘辉; 邓峥; 魏志超; 王喆; 张竞择; 汪洋
Original assignee: China Academy of Space Technology CAST
Current assignee: China Academy of Space Technology CAST
Priority date: 2018-12-27
Filing date: 2018-12-27
Publication date: 2019-05-10
Anticipated expiration: 2038-12-27
Also published as: CN109742843B

Abstract

The present invention relates to a kind of power supply and distribution Reconfigurable Control system and method towards mass flight validation.For the power supply and distribution cell failure and dynamic power changes in demand problem during the in-orbit mass flight validation of the following component, is realized in power supply and distribution output end using four set magnetic latching relays and intersect recombination output control to what power supply and distribution exported；During aerospace in-orbit flight test, needs can be controlled according to the dynamic power demand and task fault-tolerance of test unit, by intersecting the in-orbit dynamic restructuring for recombinating and power supply and distribution unit can be achieved and control for electricity output.The present invention improves the flexibility and scalability of power supply and distribution output control, while enhancing the reliability of power supply and distribution output, provides key technology support for the following in-orbit mass flight validation.

Description

A kind of power supply and distribution Reconfigurable Control system and method towards mass flight validation

Technical field

The present invention relates to a kind of power supply and distribution Reconfigurable Control system and method towards mass flight validation, specific to The power supply and distribution demand of the following in-orbit mass flight validation of component provides on the basis of controlling cost of hardware design A kind of inexpensive, highly reliable power supply and distribution Reconfigurable Control method based on concentration supply power.

Background technique

The domestic component of large quantities of aerospace and component are applicable in up for carrying out in-orbit flight test with verifying its space environment Property.The following in-orbit flight validation will become the important way and effective means of the domestic aerospace component maturity of fast lifting, I State also will be in the first autonomous space station of establishment in 2022 or so, and the following in-orbit mass flight validation of 10 years components will become A kind of normality test mission.It is for matching for supporting interface the most key in the in-orbit flight control of a variety of flight test units Electric supporter.Power supply and distribution unit supporting interface needs to meet the output power demand of all test units, should also provide simultaneously Necessary Reliability Measures, it is ensured that the appearance of Test to Failure unit will not influence the normal work of other test units.Power supply and distribution Unit design is always the important component in aerospace flight validation support Platform Designing, and is related to flight test mission The key element of success or failure.

Logical that analysis is investigated to the design of power supply and distribution unit, external spacecraft power supply and distribution unit design successively experienced biography System TT&C Management stage, primary power supply and distribution management phase and intelligent independent manage three phases.

First stage tradition TT&C Management is mainly supplied artificial ground monitoring and by way of sending telecommand Distribution management.Specific product design mainly using fuse and simple current foldback circuit carry out power supply and distribution failure isolation and Protection is a kind of simplest " hard processing " mode；

Second stage is primary power supply and distribution management phase, mainly by using " software " and " hardware " phase on spacecraft In conjunction with mode, solve power supply and distribution subsystem Fault Isolation and accumulator cell charging and discharging, the autonomous management such as adjust again, such as NASA space flight Aviation power supply fault management technology and the in-orbit power supply adjustment administrative skill of " Hubble " space telescope etc.；

Three phases are the intelligent independent management phases given priority in current aerospace model, be mainly directed towards the long-life, Highly reliable, the high complicated aerial mission demand such as in real time.The management of spacecraft power supply and distribution, monitoring are not only carried out at this stage, also answered While guaranteeing safety and reliability, automatic fault diagnosis and prediction are carried out, while intelligence is proposed to power supply and distribution unit Change and small form factor requirements.In-orbit spacecraft power supply and distribution management should make full use of the in-orbit advantage handled in real time, according to power supply and distribution reality When monitoring parameters and mission phase task execution situation, completed without ground intervening surface self-powered fault diagnosis, Isolation and recovery.If the U.S. jet propulsion laboratory JPL returns to the moon and Mars program mission requirements for NASA, system-level The intelligent power supply and distribution Managed Solution of device level and component-level is proposed on the basis of power supply management.

The design for power supply and distribution of country's aerospace electron product mostly uses " cold standby/warm back-up+independently cuts machine " controlling party at present Formula is designed, the changeover portion in above-mentioned second stage to phase III.Cold standby is to mention for different power supply and distribution targets For input/output interface, identical two physical modules (circuit board unit) of interior design, there was only one in actual work Part is working on power, another unit is then powered off in off-mode, once the unit just to work breaks down, then platform passes through Telecommand or autonomous closing fault unit start backup units.Warm back-up design is then for same power supply and distribution target design Two parts of identical power supply circuits, the output and the homologous design of input use of two parts of circuits, simultaneously powered up in actual work Work, is mutually backups, and can be compensated by another to output electric current when certain point of power supply and distribution exception, realize that a redundancy is held Mistake design.

Power supply and distribution unit development in the following aerospace model will be towards miniaturization, highly reliable, independence and long-life direction Development is made a concrete analysis of as follows:

1) it minimizes

As spacecraft is towards miniaturization and integrated direction development, the design of power supply and distribution unit is equally proposed small-sized Change demand, often structure, weight, size are larger for traditional power supply and distribution unit, have been unable to satisfy the following high integration spacecraft Mission requirements；

2) highly reliable

By counting to domestic and international in-orbit spacecraft or deep space probe, it is found that most of detectors are due to for matching Electric unit failure and cause task execution to be obstructed, No. 2 sound power supply troubles of lunar rover for emitting such as the former Soviet Union, interior overheat cause to appoint Business terminates.The in-orbit flight of Future Spacecraft has higher reliability requirement to power supply and distribution unit；

3) independence

With the surge of in-orbit spacecraft quantity, ground observing and controlling load and pressure are increasingly heavier, for deep space exploration such as " gal Benefit slightly " number the observing and controlling period be up to more than one hours, therefore tradition rely on ground observing and controlling complete orbit aerocraft power supply and distribution safeguard Mode be unable to satisfy mission requirements, need spacecraft and independently carry out power supply and distribution output control and real-time monitoring, realize autonomous Ability to work；

4) long-life

The aerospace model task such as navigation of two generations, moon exploration program, space station and Mars program etc. is to the spacecraft operation on orbit longevity Life proposes higher demand, and it is highly reliable not that the following space product power supply and distribution unit design must meet the in-orbit long-time of model task The mission requirements operated intermittently.

As " in emerging event " exposes the critical defect of component production domesticization, the following aerospace component be faced with needs from Main controllable demand, the in-orbit flight validation of component is at important means to solve this problem.Component and parts pass through Rail flight validation can examine its aerospace applicability using spatial synthesis ambient stress, quickly improve the maturity of component, push away It moves and is applied in type product.

Future space platform will provide batch, long period and the flight of normalization for the domestic component of aerospace and component Verification platform meets the in-orbit flight test verifying demand of component.Therefore a support bulge test unit flight validation is designed Highly reliable, inexpensive and restructural power supply and distribution scheme, provide key technology branch for in-orbit flight validation Platform Designing from now on Support, is the needs of the in-orbit flight validation task of the following component, and improves the horizontal needs of autonomous flight verifying.

Summary of the invention

Technical purpose of the invention is: overcome the deficiencies in the prior art, proposes one kind towards mass flight validation Power supply and distribution Reconfigurable Control system and method, for solving the reliability of the following mass flight validation test unit power supply and distribution With function expansibility demand.Due to the long-range control particularity of in-orbit flight validation, trouble unit can not be replaced in time And reparation, while the mode for increasing backup units design increases the development hardware cost and product weight of space product again, this Invention by meeting test unit power adjustment demand based on the switch control of magnetic latching relay, and successfully manage it is in-orbit can The power supply and distribution failure that can occur carries out dynamic reconfigurable control by the output to power supply and distribution, improves the output of power supply and distribution unit Reliability and flexibility.

The technical solution adopted by the present invention are as follows:

A kind of power supply and distribution Reconfigurable Control system towards mass flight validation, comprising: power supply and distribution unit, power supply and distribution are surveyed Control interface and test unit interface；Primary power source input, telecommand communication of the power supply and distribution observing and controlling interface for power supply and distribution unit Pass under power supply and distribution location mode parameter telemetering, test unit interface between power supply and distribution unit and test unit for electricity output And command communication；

Power supply and distribution unit includes communication interface circuit, memory, DC/DC voltage transformation module, the friendship of test unit power supply and distribution Pitch recombination module, Current Voltage Acquisition Circuit, instruction interface circuit and FPGA module；

DC/DC voltage transformation module, which is sent into, by the primary power source that power supply and distribution observing and controlling interface inputs carries out power supply conversion, it is raw At secondary power supply be other module for power supply in power supply and distribution unit, meanwhile, the primary power source of input passes through test unit power supply and distribution Test unit interface is sent into after intersecting recombination module processing as test unit power supply；

The telecommand inputted by external load interface and telemetering request are sent into communication interface circuit and carry out data conversion After be transmitted to FPGA module, FPGA module parses the telecommand received, and sends command signal to test unit Power supply and distribution intersects the power supply selection output that recombination module realizes power supply and distribution unit to test unit, meanwhile, FPGA module passes through finger Enable interface circuit that control is powered up or powered off to test unit；FPGA module parses the telemetering request received, will FPGA module oneself state parameter and the collected test unit power supply state parameter of voltage and current acquisition module are sent into communication Interface circuit is sent to power supply and distribution observing and controlling interface after converting by communication interface circuit；Memory is for storing FPGA module Configuration information, power supply and distribution unit control parameter and test unit power supply and distribution status information, are read out access for FPGA module.

Power supply and distribution observing and controlling interface include spacecraft power supply and distribution observing and controlling need telecommand interface, telemeter communication interface and Primary power source input；Telecommand interface is for realizing the command communication of power supply and distribution unit, and telemeter communication interface is for for matching The status data of electric unit passes under carrying out periodically, with realizing star remote data transmission.

Test unit interface includes two group interfaces, and every group of test unit interface includes that power supply output interface and instruction connect Mouthful；Output interface of powering is used to power to each test unit, and instruction interface is for realizing the switching on and shutting down to each test unit Control.

Power supply and distribution unit control parameter in memory include test unit overcurrent threshold value and test unit it is preferential Grade, the overcurrent threshold value and priority of test unit are all made of physically-isolated triplication redundancy storage.

Instruction interface circuit receives the test unit switching signal that FPGA module is sent, and generates test unit booting or closes Machine instructs electric signal, is sent to test unit, realizes the powered on and off of test unit.

The Current Voltage acquisition module includes A/D chip, voltage collection circuit and multiple current collection circuits；Each electricity Flow the corresponding test unit of Acquisition Circuit；

Current collection circuit includes resistance R1~R6, amplifier V1 and diode D5；

Secondary power supply after power supply and distribution cells D C/DC conversion is output to test unit after resistance R5 is divided Power supply and distribution input terminal, resistance R1~R4 are that amplifier V1 amplification factor adjusts resistance, by the partial pressure of resistance R1~R4 by resistance R5 After the voltage difference △ V at both ends is amplified by amplifier, so that current signal is converted to voltage signal, by AD after amplifying at double Acquisition chip is acquired；According to AD collection value V_AD△ V is calculated with amplification factor M, and then passes through electric current calculation formula: I =V_AD/ (M × R5) obtains the supply current of test unit；Resistance R6 is protective resistance, and diode D5 is defeated for realizing A/D chip Enter the pull-up of signal；

Voltage acquisition module includes amplifier V2, resistance R7~R9 and capacitor C1；Test unit power supply and distribution input voltage After the partial pressure of resistance R7 and R8, AD acquisition chip is output to by amplifier V2 amplification and carries out voltage acquisition, is acquired according to AD Value V_AD, use formula: V=V_ADTest unit voltage value is calculated in × (R7+R8)/R8；Resistance R9 is protective resistance, Capacitor C1 is connected between the output end and ground of amplifier V2.

The test unit power supply and distribution intersects recombination module and includes a pair of fuse in parallel, relay K1, intersects recombination Control circuit, filter module, the first intersection recombination DC/DC module, the second intersection recombination DC/DC module and diode D1~ D4；

Primary power source carries out the protection of power supply anti-overflow by fuse in parallel, is sent into filtering mould by relay K1 later Output simultaneously intersects recombination DC/DC module and the second intersection recombination DC/DC to first after block progress primary power source filtering processing Module；Two DC/DC modules be output to intersection recombination control circuit in, intersect recombination control circuit include relay K2~ K5 is combined under the control of the control instruction signal of FPGA module output by the closing or opening of relay K2~K5, Realize the switching to test unit difference powering mode；

First intersect recombination DC/DC module pass through diode D1, D2 for being connected in parallel carry out anti-reverse input protect and Sharing control, second, which intersects recombination DC/DC module, passes through the anti-reverse input protection of diode D3, D4 progress being connected in parallel And sharing control.

FPGA module include remote-control romote-sensing processing module, test unit switch control module, power consumption monitoring with it is expected that module And intersect recombination control module；

Remote-control romote-sensing processing module receives the telecommand that communication interface circuit is sent and telemetering request；To telecommand Validity check is carried out according to preset rules, invalid instruction sequence is abandoned, effective telecommand sequence is parsed, is obtained To the concrete operations type to be executed；Telemeter communication is requested, FPGA is by power supply and distribution unit oneself state parameter and test unit Power supply state parameter transmits communication interface circuit, realizes the telemeter communication with power supply and distribution observing and controlling interface；

Intersect the effective telecommand for recombinating control module reception remote-control romote-sensing processing module and power consumption monitoring and it is expected that mould The system real time power consumption data of block, Control experiment unit power supply and distribution intersect recombination module work in different modes；

Power consumption monitoring with it is expected that the real-time collection voltages current collection circuit of module output data, to test unit total power consumption It is monitored with test unit power supply and distribution state；The real-time of two groups of test units is calculated according to test unit operating voltage and electric current Total power consumption, the intersection recombination control module being sent to inside FPGA；If test unit electric current exceeds set current threshold, lead to Overtesting unit switch control module and instruction interface circuit send test unit shutdown command, break to Test to Failure unit Electric protection；

Test unit switch control module receive intersect recombination control module and power consumption monitoring with it is expected that module output number According to by instruction interface circuit to the powered on and off instruction of test unit transmission, to realize that the switching on and shutting down to test unit control.

The operating mode that test unit power supply and distribution intersects recombination module includes two-shipper normal power supply mode, single machine failure power supply Mode, two-shipper centrally connected power supply mode, single machine are fully loaded with powering mode and two-shipper failure powering mode；It is specific as follows:

Two-shipper normal power supply mode: the mode is the default mode of operation after the power-up initializing of power supply and distribution unit, is divided into two Kind situation: the first mode is that relay K2, K5 are closed and relay K3, K4 are disconnected；Second of mode is that relay K3, K4 are closed It closes and relay K2, K5 is disconnected；Two DC/DC modules that test unit power supply and distribution is intersected in recombination module are exported respectively to two Test unit interface, and two DC/DC module outputs are mutually isolated, and are powered respectively to two groups of test units；

Single machine failure powering mode: synchronization relay K2~K5 only has a relay under single machine failure powering mode In closed state, the relay that failure DC/DC module is connected is in off-state, and health status DC/DC module is only right Single test unit interface is powered；System runs health DC/DC module switching output relay switch after the fixed cycle, It powers to another test unit interface, two groups of test units are powered in turn carries out in-orbit test, carries out flight validation task；

Single machine is fully loaded with powering mode: under this state, the relay of health status DC/DC module connection is switched to closed form State, i.e. relay K2, K3 closure, relay K4, K5 disconnect or relay K2, K3 are disconnected, relay K4, K5 closure；Health DC/DC module for power supply is exported to two test unit interfaces, power consumption monitoring and it is expected that module and test unit switch control module Successively start test unit work according to test unit priority, until health status DC/DC module output power reaches its volume Determine the output power upper limit；

Two-shipper centrally connected power supply mode: test unit power supply and distribution intersect recombination module in two DC/DC modules with it is same The relay of test unit interface connection is in closed state, and the relay connecting with another test unit interface is disconnected It opens, i.e. relay K2, K4 closure, relay K3, K5 disconnect or relay K3, K5 closure, relay K2, K4 disconnect；The mould Two DC/DC modules are powered to single test unit interface simultaneously under formula, meet the connected test unit power demands of the interface； The input of another test unit interface unpowered, corresponding test unit are in off-position；

Two-shipper failure mode: two DC/DC modules that test unit power supply and distribution is intersected in recombination module fail, relay K2~K5 is in an off state entirely, and two groups of test units all power off, and power supply and distribution unit supplies test unit by relay K1 Distribution, which intersects recombination module, is restarted；If intersecting two DC/DC output voltages inside recombination module after restarting restores normal It is then transferred to the work of two-shipper normal power supply mode, only individual module output is electric if intersecting two DC/DC inside recombination module after restarting Pressure restores normal, then is transferred to single machine failure powering mode；If after restarting three times, intersecting two DC/DC moulds inside recombination module Block output voltage keeps abnormal, then powers off to K1, and system is reworked after failure is further repaired.

A kind of control method that the power supply and distribution Reconfigurable Control system towards mass flight validation according to is realized, Steps are as follows:

(1) power supply and distribution unit powers on rear DC/DC voltage transformation module and starts to work, and primary power source is converted to secondary power supply The work of other modules of power supply and distribution unit is supplied, FPGA completes configuration file load and initial work；Relay K1~K5 locates In off-state, (2) are gone to step；

(2) FPGA sends telecommand closing relay K1, and activation experiment unit power supply and distribution intersects recombination module；

(3) FPGA intersects recombination module transmission telecommand to test unit power supply and distribution, successively closing relay K2 and K5, Relay K3 and K4 are off-state；Or successively closing relay K3, K4, relay K2 and K5 are in an off state；Power supply and distribution Cell operation under two-shipper normal power supply mode, intersect two DC/DC modules in recombination module and generate by test unit power supply and distribution Secondary power supply be respectively outputted to two test unit interfaces, go to step (4)；

(4) power supply and distribution unit is sent to the test unit of off-position by instruction interface circuit and is instructed, and each group is tested Unit is successively powered on according to priority, starts in-orbit flight test, meanwhile, the voltage and current Acquisition Circuit inside power supply and distribution unit Acquisition test unit supply voltage and electric current in real time are sent into the power consumption monitoring of FPGA module and it is expected that module, calculate test in real time Simultaneously whether the supply voltage of monitoring test unit and supply current there is exception to the dynamic power consumption of unit；

If the supply current of test unit exceeds the test unit current threshold that FPGA internal preset is set, test unit Switch control module sends telecommand by instruction interface circuit and carries out power-off protection to the test unit, and failure is waited to repair It is multiple；Other test units continue to be powered on work；

If the relay that some in relay K2~K5 should be closed can not be closed or abnormal disconnection, pass through telecommand The relay of another closed state is closed, the relay being in an off state before this in rear closing relay K2~K5 is real Switching between existing two-shipper normal power supply both of which；

If certain moment test unit input supply voltage is abnormal and not sent overcurrent, connected test unit is for matching Electricity intersects the DC/DC module failure in recombination module, FPGA by test unit switch control module and instruction interface circuit to This group of test unit sends remote power-off instruction, closes this group of total Test unit；Disconnection is connected with failure DC/DC module afterwards Relay realizes single machine failure power supply, goes to step (5)；

If certain moment battery of tests unit needs test unit power supply and distribution to intersect two DC/DC modules in recombination module It powers simultaneously, to complete the execution of in-orbit test mission, ground sends telecommand and gives power supply and distribution unit at this time, and FPGA passes through examination Verification certificate member switch control module and instruction interface circuit send cut-offing instruction, close another group of test unit and the relay that is connected Device connects the test unit that two groups of DC/DC modular power sources for intersecting recombination module output is switched to the connection of this group of test unit Mouthful, it realizes two-shipper centrally connected power supply, enters step (6)；

(5) power supply and distribution unit receives ground remote control instruction or according to predetermined period parameter, switches health DC/DC module Output control relay, periodically to two groups of test unit interleaved powers；The alternately in-orbit flight test of two groups of test units；

If the single machine fails, failure DC/DC module is completed by reset, reboot operation reparation under powering mode, voltage output Normally, then power supply and distribution unit is closed the relay between the DC/DC module of the reparation and the test unit interface in off-position, Restore two-shipper normal power supply mode, returns to step (4)；

If it is different to monitor that the output voltage of healthy DC/DC module occurs for power supply and distribution unit under single machine failure powering mode Often, then power supply and distribution unit send first instruction close total Test unit, after will be in closed state DC/DC output relay It disconnects, into two-shipper failure operating mode, goes to step (8)；

If two groups of test units must carry out test simultaneously, ground sends telecommand to power supply and distribution unit, is first shut off complete Portion's test unit, it is rear to be closed two connected relays of health DC/DC module, so that the DC/DC module gives two groups of tests simultaneously Unit power supply, is fully loaded with operating mode into single machine, enters step (7)；

(6) relay switch is switched by sending telecommand according to test mission demand, so that two groups of test units are handed over For power-up work, the two DC/DC module outputs of diode pair for intersecting the power output end in recombination module carry out stream adjustment；

At the end of test unit task execution, ground sends telecommand and gives power supply and distribution unit, and power supply and distribution unit is by one Group DC/DC module is outputted to the power supply of off-position test unit interface, restores two-shipper normal power supply mode, goes to step (4)；

If there is single DC/DC module output voltage abnormal at this time, power supply and distribution unit monitors that the failure disconnects the DC/DC The output relay of module goes to step (5) into single machine failure powering mode；

(7) in the case where single machine is fully loaded with operating mode, single DC/DC module passes through two test unit interfaces to two groups of test sheets Member power supply, power supply and distribution unit pass through test unit switch control and instruction interface circuit according to preset test unit priority It successively sends the instruction of test unit remote-controlled start-up to be powered on test unit, until health status DC/DC module output power reaches Its rated output upper limit；

If the DC/DC module worked normally under the mode breaks down, corresponding test sheet is automatically closed in power supply and distribution unit Member disconnects the output relay of the DC/DC module, into two-shipper failure powering mode, goes to step (8)；

If failure DC/DC module completes fault recovery by restarting, resetting, output voltage is normal, then power supply and distribution unit Arbitrarily a output control relay of DC/DC module that command pulse disconnects work at present is sent, single machine failure power supply mould is switched to Formula goes to step (5)；

(8) two-shipper fail operating mode under total Test unit all in power-down mode, the intersection weight of power supply and distribution unit Two DC/DC modules in group module break down, and power supply and distribution unit sends telecommand, close relay K1, intersect weight Two DC/DC modules in group module power off, and rear FPGA re-closes relay to recombination module transmission telecommand is intersected K1 restarts intersection recombination module, monitors whether two DC/DC modules export normally, is confirmed whether to repair and complete；

If two DC/DC modules repair completion simultaneously, telecommand is sent by ground and gives power supply and distribution unit, by FPGA mould Block intersects recombination module to test unit power supply and distribution and sends instruction, closes relay K2, K5 or K3, K4, returns to two-shipper and normally supply Power mode is transferred to step (4)；

If single DC/DC module failure restores to complete, telecommand is sent by ground and gives power supply and distribution unit, by FPGA mould Block sends instruction to recombination module is intersected, and closes the connected any relay of the DC/DC module repaired and completed, is transferred to step (5)；

If still can not by adding power-off to attempt two DC/DC modules in intersection recombination module three times intersection recombination module It repairs and completes, then termination test task, close relay K1, wait and further repairing.

The advantages of the present invention over the prior art are that:

(1) the present invention is based on the intersections of magnetic latching relay to recombinate power supply control, tests for the following in-orbit mass flight The power supply and distribution demand of card task proposes on the basis of controlling power supply-distribution system design cost towards mass flight validation The design of power supply and distribution Reconfigurable Control system describes power supply and distribution cellular system composition and working principle in detail；

(2) present invention breaks through traditional power supply and distribution output control design case thinking, is recombinated by intersecting in test unit power supply and distribution Two DC/DC modules in module and 4 magnetic latching relays of setting between test sheet tuple, realize and export control to power supply and distribution It is in-orbit restructural.It is reconstructed by redundancy backup with the output of the power supply and distribution based on magnetic latching relay, in control system cost base The function expansibility and reliability of power supply and distribution unit are improved on plinth；

(3) power supply and distribution Reconfigurable Control system power supply pattern definition and control method.The invention proposes related confessions Five kinds of powering modes of power distribution unit: two-shipper normal power supply mode, single machine failure powering mode, two-shipper centrally connected power supply mode, single machine Fully loaded powering mode and two-shipper failure powering mode, are defined five kinds of modes.And combine the in-orbit power of test unit dynamic The failure that state demand and power supply and distribution unit are likely to occur gives the control method of five kinds of powering modes of power supply and distribution unit switching, The in-orbit power supply and distribution output restructuring procedure of power supply and distribution unit is described by step.Power supply and distribution unit can be outer by autonomous control or receiving Portion's telecommand, in-orbit switching that is autonomous or receiving external remote control instruction completion operating mode, meets the height of in-orbit flight validation Reliable and scalability demand.

Detailed description of the invention

Fig. 1 is design for power supply and distribution system block diagram of the present invention；

Fig. 2 is that test unit power supply and distribution of the present invention intersects recombination module design principle schematic diagram；

Fig. 3 is voltage and current Acquisition Circuit design schematic diagram of the present invention；

Fig. 4 is two-shipper normal power supply pattern diagram of the present invention；

Fig. 5 is single machine of the present invention failure powering mode schematic diagram；

Fig. 6 is that single machine of the present invention is fully loaded with powering mode schematic diagram；

Fig. 7 is two-shipper centrally connected power supply pattern diagram of the present invention；

Fig. 8 is two-shipper of the present invention failure powering mode schematic diagram；

Fig. 9 is power supply and distribution cell operation pattern switching state of a control machine of the present invention.

Specific embodiment

The power dynamics and the mistake of DC/DC module that the present invention is faced for the in-orbit flight test of bulge test unit Effect mode proposes the power supply and distribution Reconfigurable Control system and method based on the recombination of power supply and distribution output cross.Below from power supply and distribution Cellular system is realized, intersects reconstruct power supply and distribution principle realization, implements stream based on the power supply and distribution Reconfigurable Control method for intersecting recombination Three aspects of journey are described in detail.

As shown in Figure 1, the present invention proposes that a kind of power supply and distribution Reconfigurable Control system towards mass flight validation includes: Power supply and distribution unit, power supply and distribution observing and controlling interface and test unit interface；Power supply and distribution observing and controlling interface is used for the primary electricity of power supply and distribution unit Passed under source input, telecommand communication and power supply and distribution location mode parameter telemetering, test unit interface for power supply and distribution unit and Between test unit for electricity output and command communication；

FPGA module is the kernel control module of this reconfigurable system, is realized using antifuse A54SX72 type FPGA, with Improve the anti-radiation characteristic of power supply and distribution unit.Memory uses NOR FLASH and SRAM with the EDAC 3D encapsulation verified real Existing, DC/DC is inputted using 100V, and HDCD/100-12R-30/SP the and HDCD/100-5R-30/SP power supply of output ± 12V turns Change the mold+5V and ± the 12V supply input that block realizes itself need of work of power supply and distribution unit.Communication interface is total using standard 1553B Line is as telecommand interface and telemeter communication interface, and timesharing is completed to pass under instruction transmission and telemetry, and interface circuit uses Interface control chip of the BM65170 chip as 1553B bus, and two B3226 type transformers are set and are believed for 1553B bus Breath transmitting-receiving；

DC/DC voltage transformation module (HDCD/100-12R- is sent by the primary power source that power supply and distribution observing and controlling interface inputs 30/SP and HDCD/100-5R-30/SP) power supply conversion is carried out, the secondary power supply (+5V and ± 12V) of generation is power supply and distribution unit Other interior module for power supply, meanwhile, the primary power source of input generates examination after intersecting recombination module processing by test unit power supply and distribution + 12V the voltage of verification certificate member need of work is respectively fed to two test unit interfaces as the power supply of test unit 1~8；

Power supply and distribution observing and controlling interface include spacecraft power supply and distribution observing and controlling need telecommand interface, telemeter communication interface and Primary power source input；Telecommand interface is for realizing the command communication of power supply and distribution unit, and telemeter communication interface is for for matching The status data of electric unit passes under carrying out periodically, with realizing star remote data transmission.Telecommand interface and telemeter communication connect The standard 1553B bus interface of the shared dual redundant of mouth realizes that for power supply and distribution cell operation under RT mode, the address RT is 0x7.

As shown in figure 3, Current Voltage acquisition module includes A/D chip, voltage collection circuit and multiple current collection circuits； The corresponding test unit of each current collection circuit；This power supply and distribution unit output voltage can meet multiple test units simultaneously and supply Electricity demanding, power supply and distribution unit are consistent to the output voltage of each test unit, can only monitor the secondary power supply electricity of power module output Pressure.For each test unit, needs to design individual current collection circuit and monitor its operating current.Due to DC/DC module For composition inside power supply and distribution unit, especially aerospace grade module has higher reliability, therefore examination is mainly considered in the present invention The monitoring and overcurrent protection problem of verification certificate member operating current.

Power supply and distribution unit realizes the monitoring to test unit power supply state by current monitoring circuit, wherein voltage monitoring master Implement to acquire the supply voltage that power supply and distribution unit power module generates, current monitoring is to acquire each test unit input terminal Operating current；One group of voltage collection circuit and multiple groups test unit electric current need to be arranged for all test units in implementing in this system Acquisition Circuit (particular number is consistent with test unit quantity)；Current acquisition trueness error requires as < 3mA, voltage acquisition precision Error requirements are < 3mV.

Current collection circuit includes resistance R1~R6, amplifier V1 and diode D5.After power supply and distribution cells D C/DC conversion Secondary power supply after resistance R5 is divided, be output to the power supply and distribution input terminal of test unit, resistance R1~R4 is amplifier V1 amplification factor adjusts resistance, the partial pressure of resistance R1~R4 by the voltage difference △ V=VCC_OUT-VCC_IN at the both ends resistance R5, Middle VCC_IN is the test unit supply voltage of test unit power module conversion output in power supply and distribution unit, and VCC_OUT is Exporting to the secondary power supply voltage of test unit after divider resistance R5；After △ V is amplified by amplifier, thus by electric Stream signal is converted to voltage signal, is acquired after amplifying at double by AD acquisition chip；According to AD collection value V_ADWith amplification factor M △ V is calculated, and then passes through electric current calculation formula: I=V_AD/ (M × R5) obtains the supply current of test unit；Diode D5 For realizing the pull-up of A/D chip input signal；

AD acquisition chip realizes that R6 is protective resistance using SAD0808RH chip, real using the high-grade resistance of 100K Ω It is existing；Amplifier V1 selects F158A to realize, F158A power end VCC connects+12V input；Diode D5 selects specification for 2CK84F type space Navigate grade diode；Since the electric current of test unit is smaller, to guarantee acquisition precision, acquired after needing to amplify, R0 is in figure Divider resistance is typically chosen the precision resistance less than 1 Ω.Amplification factor then determines by tetra- resistance values of R1, R2, R3, R4, specifically It can be adjusted according to actual current size.Current collection circuit specific implementation can be according to the big of different tests cell operation electric current Small adjustment divider resistance R1~R4 defaults feelings so that meeting the nominal input voltage range of AD by the signal that amplifier is amplified It is the resistance of 10K Ω that resistance R1 and resistance R3, which selects resistance value, under condition, and resistance R2 and resistance R4 use resistance value for the resistance of 90K Ω, Then the amplification factor M of resistance R5 voltage difference of the two ends is 9 times.The accurate electricity of low resistance of the resistance value selection aerospace grade of divider resistance R5 Resistance, herein resistance R5 resistance value suggestion are 0.1 Ω.Electric current calculation formula based on this current collection circuit of the embodiment above are as follows: I =(10 × V_AD)/9 (unit is ampere)；

Voltage acquisition module includes amplifier V2, resistance R7~R9 and capacitor C1；Test unit power supply and distribution input voltage After the partial pressure of resistance R7 and R8, AD acquisition chip is output to by amplifier V2 amplification and carries out voltage acquisition, is acquired according to AD Value V_AD, use formula: V=V_ADTest unit voltage value is calculated in × (R7+R8)/R8, and resistance R9 is protective resistance, Capacitor C1 is connected between the output end and ground of amplifier V2.Voltage collection circuit AD acquisition chip equally uses SAD0808RH core Piece realizes that R9 is protective resistance, realizes that C1 selects 30PF gallbladder capacitor to realize using the high-grade resistance of 100K Ω, V2 is selected LM108A amplifier device.VCC_IN be power supply and distribution unit power module generate test unit power supply, herein divider resistance R7 and The selection of R8 is also required to be determined according to real work voltage and the specified input range of amplifier V2, and R7 resistance value is 20K Ω, R8 herein Resistance value 30K Ω, it is desirable that use precision resistance.The calculation formula of this voltage acquisition are as follows: V=(3 × V_{AD acquisition})/5。

As shown in Fig. 2, it includes a pair of fuse in parallel, relay that the test unit power supply and distribution, which intersects recombination module, K1, intersect recombination control circuit, filter module, first intersect recombination DC/DC module, second intersect recombination DC/DC module and Diode D1~D4；Diode D1~D4 selects specifications and models for the realization of 2DK1080S type Schottky diode, for carrying out The output sharing control of DC/DC module and it is galvanically isolated protection.Diode D1 and D2 are general using parallel way reduction single point failure Rate, similarly diode D3 and D4 also use Parallel Design；Filter circuit selects the standard that specification is HFE-100-461-300 to filter Wave module realizes that DC/DC module M1 and M2 are inputted using 100V, the HDCD/100-12R-30/SP type DC/DC of output ± 12V It realizes.Relay K1 selects the high-grade electromagnetic relay of 2JB1-910-012-2-M type to realize, it is ensured that the reliability of switch control.

Relay K2~K5 selects the high-grade electromagnetic relay of 2JB1-910-012-2-M type to realize, it is ensured that switch control Reliability.Magnetic latching relay is a kind of new type of relay developed in recent years and a kind of automatic switch.With other electricity Magnetic relay is the same, plays turn on automatically and cutting action to circuit.The normally closed and the normally open state of magnetic latching relay is entirely The effect of permanent-magnet steel is relied on, the conversion of switch state is the pulse electrical signal triggering completion by one fixed width.And at contact When hold mode, coil needs not continue to be powered, and only the state of relay can be maintained constant by the magnetic force of permanent magnet.Cause This, the output state of a control of power supply and distribution unit is not by adding power-off to be influenced, until receiving new relay switch telecommand, And the design has the advantages of power saving, performance stabilization and large carrying capacity, exports control electricity especially suitable for in-orbit flight test Road design.

As shown in Fig. 2, the rated disspation output for intersecting DC/DC module M1, M2 in recombination module is 30W, each test Unit maximum power dissipation is 7.5W, therefore each module can support the in-orbit test simultaneously of 4 test units.DC/DC module is for rear It holds two groups of test units (every group 4) to be separately connected by magnetic latching relay K2~K5, is powered by switch order Access control.If the rear end DC/DC in the intersection recombination module in Fig. 2 is provided with 4 group relays altogether, M1 is to examination for DC/DC module Verification certificate member 1~4, DC/DC module M2 power to test unit 5~8.

The operating mode that test unit power supply and distribution intersects recombination module includes two-shipper normal power supply mode, single machine failure power supply Mode, two-shipper centrally connected power supply mode, single machine are fully loaded with powering mode and two-shipper failure powering mode；By control relay K2~ Switching of K5, S the realization power supply and distribution unit between five kinds of power supply and distribution operating modes, five kinds of power supply and distribution modes and relay K2, K3, The occluding relation table of comparisons of K4, K5 are as follows, and each mode is defined as follows:

Five kinds of powering modes and relay status relation table

Five kinds of powering modes are specific as follows:

Two-shipper normal power supply mode: as shown in figure 4, the mode is the default Working mould after the power-up initializing of power supply and distribution unit Formula, be divided into two kinds of situations: the first mode is relay K2, K5 closure and relay K3, K4 are disconnected, so that DC/DC module M1 Power supply is output to test unit 1~4, and DC/DC module M2 power supply is output to test unit 5~8；Second of mode is relay K3, K4 closure and relay K2, K5 disconnection, so that DC/DC module M2 power supply is output to test unit 1~4, DC/DC module M1 Power supply is output to test unit 5~8；Two DC/DC modules that test unit power supply and distribution intersects in recombination module export respectively gives Two test unit interfaces, and two DC/DC module outputs are mutually isolated, and are powered respectively to two groups of test units；

Single machine fail powering mode: as shown in figure 5, single machine failure powering mode under synchronization relay K2~K5 only There is a relay to be in closed state, the relay that failure DC/DC module is connected is in off-state, health status DC/DC module is only powered single test unit interface；System runs health DC/DC module switching output after the fixed cycle Relay switch (is switched to Mode B from the Mode A in Fig. 5, or is switched to mode D from the mode C in Fig. 5), gives another test Unit interface power supply, two groups of test units are powered in turn carries out in-orbit test, carries out flight validation task；

Single machine is fully loaded with powering mode: as shown in fig. 6, the relay of health status DC/DC module connection is cut under this state Closed state is changed to, i.e. relay K2, K3 closure, relay K4, K5 disconnect (connection mode figure on the left of Fig. 6) or relay K2, K3 are disconnected, relay K4, K5 are closed (connection mode figure on the right side of Fig. 6)；Healthy DC/DC module for power supply is exported to be tested to two Unit interface, power consumption monitoring with it is expected that module and test unit switch control module successively start examination according to test unit priority Cell operation is tested, until health status DC/DC module output power reaches its rated output power upper limit 30W, reference value is 29W±5W；

Two-shipper centrally connected power supply mode: as shown in fig. 7, test unit power supply and distribution intersects two DC/DC moulds in recombination module The relay that block M1 and M2 is connect with the same test unit interface is in closed state, connects with another test unit interface The relay connect disconnects, i.e. relay K2, K4 closure, relay K3, K5 disconnect (electrical schematic on the left of Fig. 7), Huo Zheji Electric appliance K3, K5 closure, relay K2, K4 disconnect (electrical schematic on the right side of Fig. 7)；Under the mode two DC/DC modules simultaneously to The power supply of single test unit interface meets the connected test unit power demands of the interface；Another test unit interface is without confession Electricity input, corresponding test unit are in off-position；Power supply and distribution unit can meet test unit big function in short term under this mode Rate test mission is restored to normal power supply mode after executing to high-power processing test mission.

Two-shipper failure mode: as shown in figure 8, two DC/DC modules that test unit power supply and distribution is intersected in recombination module are equal Failure, relay K2~K5 are in an off state entirely, and two groups of test units all power off, and power supply and distribution unit passes through K1 pairs of relay Test unit power supply and distribution intersection recombination module is restarted；If intersecting two DC/DC output voltages inside recombination module after restarting Restore normally then to be transferred to the work of two-shipper normal power supply mode, if it is only single to intersect two DC/DC inside recombination module after restarting Module output voltage restores normal, then is transferred to single machine failure powering mode；If after restarting three times, intersecting two inside recombination module A DC/DC module output voltage keeps abnormal, then powers off to K1, and system is reworked after failure is further repaired.

Power supply and distribution unit refers to according to test unit dynamic power demand, itself DC/DC module output state and external remote control The switching for the mode that is powered is enabled, meets the in-orbit power supply and distribution demand of two groups of test units to greatest extent, realizes power supply and distribution list The in-orbit reconstruct of member output control；Wherein external remote control instruction includes that test unit DC/DC module powers on instruction, test unit DC/DC module cut-offing instruction, two-shipper normal power supply pattern switching to two-shipper centrally connected power supply mode instruction, two-shipper centrally connected power supply mode It is switched to two-shipper normal power supply mode instruction, single machine failure powering mode is switched to the fully loaded powering mode instruction of single machine and single machine is full It carries powering mode and is switched to single machine failure powering mode instruction；Switching between remaining each mode.Towards mass flight validation Power supply and distribution Reconfigurable Control system realize control method implementation steps it is as follows:

(3) FPGA intersects recombination module transmission telecommand to test unit power supply and distribution, successively closing relay K2 and K5, Relay K3 and K4 are off-state；Or successively closing relay K3, K4, relay K2 and K5 are in an off state (such as Fig. 4 institute Show)；For power supply and distribution cell operation under two-shipper normal power supply mode, test unit power supply and distribution intersects two DC/ in recombination module The secondary power supply that DC module generates is respectively outputted to two test unit interfaces, goes to step (4)；

If the relay that some in relay K2~K5 should be closed can not be closed or abnormal disconnection, pass through telecommand The relay of another closed state is closed, the relay being in an off state before this in rear closing relay K2~K5 is real Switching (Fig. 3) between existing two-shipper normal power supply both of which；Magnetic latching relay reliability with higher, through engineering practice table The bright probability that breaks down is extremely low, therefore the present invention only considers the Problem of Failure of single magnetic latching relay；

Since test unit interface is the total Test unit power supply in single grouping, supply input voltage is identical, test Practical unit supply voltage is the DC/DC module output voltage intersected in recombination module；If certain moment test unit input power Electric voltage exception and not sent overcurrent, then connected test unit power supply and distribution intersects the DC/DC module failure in recombination module, FPGA sends remote power-off instruction to this group of test unit by test unit switch control module and instruction interface circuit, closes This group of total Test unit；The relay being connected with failure DC/DC module is disconnected afterwards, is realized single machine failure power supply, is gone to step (5)；

If certain moment battery of tests unit needs test unit power supply and distribution to intersect two DC/DC modules in recombination module It powers simultaneously, to complete the execution of in-orbit test mission.Such as the test unit for some power classes, high-speed computation type, It is lower to deposit power in a rated operation, but needs short time large power supply when running the application of particular flight test mission The case where supply.Ground sends telecommand and gives power supply and distribution unit at this time, and FPGA is by test unit switch control module and refers to Enable interface circuit send cut-offing instruction, close another group of test unit with the relay that is connected, two groups of recombination module will be intersected The output of DC/DC modular power source is switched to the test unit interface of this group of test unit connection, realizes two-shipper centrally connected power supply, enters Step (6)；

(5) two groups of test units only have battery of tests unit in power-up working condition at this time, and another group of test unit is then In off-position (as shown in Figure 5).Power supply and distribution unit receives ground remote control instruction or according to predetermined period parameter, switching health The output control relay of DC/DC module periodically (is switched to mould from the Mode A in Fig. 5 to two groups of test unit interleaved powers Formula B, or mode D is switched to from the mode C in Fig. 5)；The alternately in-orbit flight test of two groups of test units, to a certain extent Guarantee the normal development of in-orbit flight test mission；

(6) two DC/DC modules are powered single group test unit by way of in parallel, meet this group of test unit Short-term high-power input demand.Switch relay switch by sending telecommand according to test mission demand, so that two groups Test unit alternately power-up work, intersect recombination module in power output end two DC/DC modules of diode pair export into Row stream adjustment, guarantees that power is reasonably assigned to two DC/DC modules, the mode is big mainly for test unit in a short time Power task processing requirements, duration are shorter.

(7) in the case where single machine is fully loaded with operating mode, single DC/DC module passes through two test unit interfaces to two groups of test sheets Member power supply, power supply and distribution unit pass through test unit switch control and instruction interface circuit according to preset test unit priority It successively sends the instruction of test unit remote-controlled start-up to be powered on test unit, until health status DC/DC module output power reaches Its rated output upper limit；DC/DC module is being that multiple test units are powered to greatest extent under the mode, guarantees that priority is higher Test mission operation on orbit.

If failure DC/DC module completes fault recovery by restarting, resetting, output voltage is normal, then power supply and distribution unit It sends command pulse and closes battery of tests unit, it is rear to disconnect what work at present DC/DC module was connect with this group of test unit interface Relay, it is (subsequent to be restored to two-shipper normal power supply mould by single machine failure powering mode that system is switched to single machine failure powering mode Formula), go to step (5)；

If two DC/DC modules repair completion simultaneously, telecommand is sent by ground and gives power supply and distribution unit, by FPGA mould Block intersects recombination module to test unit power supply and distribution and sends instruction, closes relay K2, K5 (or closing relay K3, K4), returns To two-shipper normal power supply mode, it is transferred to step (4)；

If single DC/DC module failure restores to complete, telecommand is sent by ground and gives power supply and distribution unit, by FPGA mould Block sends instruction to recombination module is intersected, and closes the connected any relay of the DC/DC module repaired and completed, realizes single machine failure Powering mode is transferred to step (5)；

In conclusion proposed by the present invention a kind of towards the power supply and distribution Reconfigurable Control system of mass flight validation and side Method uses the test based on magnetic latching relay for the power supply and distribution demand of the in-orbit mass flight validation task of the following aerospace Unit power supply and distribution intersection Recombinant design realizes the dynamic reconfigurable control to test unit power supply and distribution.The present invention describes first The Reconfigurable Control system of power supply and distribution unit designs and intersects recombination power supply and distribution circuit theory, and defines the restructural control of power supply and distribution Five kinds of operating modes of system processed.It describes in detail by step based on the in-orbit reconfigurable control stream of power supply and distribution for intersecting recombination control Journey.By the in-orbit dynamic restructuring controlled multiple test unit power supply and distributions, power supply and distribution cells D C/DC can be solved to a certain extent Module export failure, test unit in short term high-power power supply and distribution demand the problems such as, it is ensured that in-orbit flight validation task it is just normally opened Exhibition improves reliability, the flexibility and scalability of power supply and distribution output control.

Claims

1. a kind of power supply and distribution Reconfigurable Control system towards mass flight validation, characterized by comprising: power supply and distribution unit, Power supply and distribution observing and controlling interface and test unit interface；Primary power source input, remote control of the power supply and distribution observing and controlling interface for power supply and distribution unit It is passed under command communication and power supply and distribution location mode parameter telemetering, test unit interface is used between power supply and distribution unit and test unit For electricity output and command communication；

Power supply and distribution unit includes communication interface circuit, memory, DC/DC voltage transformation module, test unit power supply and distribution intersection weight Group module, Current Voltage Acquisition Circuit, instruction interface circuit and FPGA module；

DC/DC voltage transformation module, which is sent into, by the primary power source that power supply and distribution observing and controlling interface inputs carries out power supply conversion, generation Secondary power supply is other module for power supply in power supply and distribution unit, meanwhile, the primary power source of input is intersected by test unit power supply and distribution Test unit interface is sent into after recombination module processing as test unit power supply；

The telecommand inputted by external load interface and telemetering request, which are sent into after communication interface circuit carries out data conversion, to be passed It is delivered to FPGA module, FPGA module parses the telecommand received, and sends command signal to test unit for matching Electricity, which intersects recombination module, realizes that power supply and distribution unit selects output to the power supply of test unit, meanwhile, FPGA module is connect by instruction Mouth circuit is powered up to test unit or powers off control；FPGA module parses the telemetering request received, by FPGA Module oneself state parameter and the collected test unit power supply state parameter of voltage and current acquisition module are sent into communication interface Circuit is sent to power supply and distribution observing and controlling interface after converting by communication interface circuit；Memory is used to store the configuration of FPGA module Information, power supply and distribution unit control parameter and test unit power supply and distribution status information, are read out access for FPGA module.

2. a kind of power supply and distribution Reconfigurable Control system towards mass flight validation according to claim 1, feature Be: power supply and distribution observing and controlling interface includes telecommand interface, the telemeter communication interface and one that spacecraft power supply and distribution observing and controlling needs Secondary source input；Telecommand interface is for realizing the command communication of power supply and distribution unit, and telemeter communication interface is for power supply and distribution The status data of unit passes under carrying out periodically, with realizing star remote data transmission.

3. a kind of power supply and distribution Reconfigurable Control system towards mass flight validation according to claim 1, feature Be: test unit interface includes two group interfaces, and every group of test unit interface includes power supply output interface and instruction interface； Output interface of powering is used to power to each test unit, and instruction interface is for realizing the switching on and shutting down control to each test unit System.

4. a kind of power supply and distribution Reconfigurable Control system towards mass flight validation according to claim 1, feature Be: the power supply and distribution unit control parameter in memory includes the overcurrent threshold value of test unit and the priority of test unit, The overcurrent threshold value and priority of test unit are all made of physically-isolated triplication redundancy storage.

5. a kind of power supply and distribution Reconfigurable Control system towards mass flight validation according to claim 1, feature Be: instruction interface circuit receives the test unit switching signal that FPGA module is sent, and generates test unit booting or shutdown Electric signal is instructed, test unit is sent to, realizes the powered on and off of test unit.

6. a kind of power supply and distribution Reconfigurable Control system towards mass flight validation according to claim 1, feature Be: the Current Voltage acquisition module includes A/D chip, voltage collection circuit and multiple current collection circuits；Each electric current is adopted Collector corresponds to a test unit；

Secondary power supply after power supply and distribution cells D C/DC conversion after resistance R5 is divided, match by the confession for being output to test unit Electrical input, resistance R1~R4 are that amplifier V1 amplification factor adjusts resistance, by the partial pressure of resistance R1~R4 by the both ends resistance R5 Voltage difference △ V amplified by amplifier after, so that current signal is converted to voltage signal, acquired after amplifying at double by AD Chip is acquired；According to AD collection value V_AD△ V is calculated with amplification factor M, and then passes through electric current calculation formula: I= V_AD/ (M × R5) obtains the supply current of test unit；Resistance R6 is protective resistance, and diode D5 is for realizing A/D chip input The pull-up of signal；

Voltage acquisition module includes amplifier V2, resistance R7~R9 and capacitor C1；Test unit power supply and distribution input voltage passes through After the partial pressure of resistance R7 and R8, AD acquisition chip is output to by amplifier V2 amplification and carries out voltage acquisition, according to AD collection value V_AD, Use formula: V=V_ADTest unit voltage value is calculated in × (R7+R8)/R8；Resistance R9 is protective resistance, capacitor C1 It is connected between the output end and ground of amplifier V2.

7. a kind of power supply and distribution Reconfigurable Control system towards mass flight validation according to claim 1, feature Be: the test unit power supply and distribution intersects recombination module and includes a pair of fuse in parallel, relay K1, intersects recombination control Circuit, filter module, first intersect recombination DC/DC module, the second intersection recombination DC/DC module and diode D1~D4；

Primary power source carries out the protection of power supply anti-overflow by fuse in parallel, later by relay K1 be sent into filter module into Output simultaneously intersects recombination DC/DC module to the first intersection recombination DC/DC module and second after the filtering processing of row primary power source； Two DC/DC modules are output in intersection recombination control circuit, and intersecting recombination control circuit includes relay K2~K5, It under the control of the control instruction signal of FPGA module output, is combined, is realized by the closing or opening of relay K2~K5 Switching to test unit difference powering mode；

First, which intersects recombination DC/DC module, passes through the anti-reverse input protection of diode D1, D2 progress being connected in parallel and flows Control, second, which intersects recombination DC/DC module, passes through the anti-reverse input protection of diode D3, D4 progress being connected in parallel and flows Control.

8. a kind of power supply and distribution Reconfigurable Control system towards mass flight validation according to claim 7, feature Be: FPGA module include remote-control romote-sensing processing module, test unit switch control module, power consumption monitoring with it is expected that module and Intersect recombination control module；

Remote-control romote-sensing processing module receives the telecommand that communication interface circuit is sent and telemetering request；To telecommand according to Preset rules carry out validity check, abandon invalid instruction sequence, parse, to effective telecommand sequence The concrete operations type of execution；Telemeter communication is requested, FPGA powers power supply and distribution unit oneself state parameter and test unit State parameter transmits communication interface circuit, realizes the telemeter communication with power supply and distribution observing and controlling interface；

Intersect recombination control module receive remote-control romote-sensing processing module effective telecommand and power consumption monitoring with it is expected that module System real time power consumption data, Control experiment unit power supply and distribution intersect recombination module work in different modes；

Power consumption monitoring with it is expected that the real-time collection voltages current collection circuit of module output data, to test unit total power consumption and examination Verification certificate member power supply and distribution state is monitored；The real-time total work of two groups of test units is calculated according to test unit operating voltage and electric current Consumption, the intersection recombination control module being sent to inside FPGA；If test unit electric current exceeds set current threshold, pass through examination Verification certificate member switch control module and instruction interface circuit send test unit shutdown command, carry out power-off guarantor to Test to Failure unit Shield；

Test unit switch control module receive intersect recombination control module and power consumption monitoring with it is expected that module output data, lead to It crosses instruction interface circuit and sends powered on and off instruction to test unit, to realize that the switching on and shutting down to test unit control.

9. a kind of power supply and distribution Reconfigurable Control system towards mass flight validation according to claim 8, feature Be: the operating mode that test unit power supply and distribution intersects recombination module includes two-shipper normal power supply mode, single machine failure power supply mould Formula, two-shipper centrally connected power supply mode, single machine are fully loaded with powering mode and two-shipper failure powering mode；It is specific as follows:

Two-shipper normal power supply mode: the mode is the default mode of operation after the power-up initializing of power supply and distribution unit, is divided into two kinds of feelings Condition: the first mode is that relay K2, K5 are closed and relay K3, K4 are disconnected；Second mode be relay K3, K4 be closed and Relay K2, K5 are disconnected；Two DC/DC modules that test unit power supply and distribution intersects in recombination module export respectively to be tested to two Unit interface, and two DC/DC module outputs are mutually isolated, and are powered respectively to two groups of test units；

Single machine failure powering mode: synchronization relay K2~K5 only has a relay and is under single machine failure powering mode Closed state, the relay that failure DC/DC module is connected are in off-state, and health status DC/DC module is only to single Test unit interface is powered；System runs health DC/DC module switching output relay switch after the fixed cycle, to another The power supply of test unit interface, two groups of test units are powered in turn carries out in-orbit test, carries out flight validation task；

Single machine is fully loaded with powering mode: under this state, the relay of health status DC/DC module connection is switched to closed state, That is relay K2, K3 closure, relay K4, K5 disconnect or relay K2, K3 are disconnected, relay K4, K5 closure；Healthy DC/ DC module for power supply is exported to two test unit interfaces, power consumption monitoring with it is expected that module and test unit switch control module according to Test unit priority successively starts test unit work, until to reach its specified defeated for health status DC/DC module output power The upper limit of the power out；

Two-shipper centrally connected power supply mode: test unit power supply and distribution intersects two DC/DC modules and the same test in recombination module The relay of unit interface connection is in closed state, and the relay connecting with another test unit interface disconnects, i.e., Relay K2, K4 closure, relay K3, K5 disconnect or relay K3, K5 closure, relay K2, K4 disconnect；Under the mode Two DC/DC modules are powered to single test unit interface simultaneously, meet the connected test unit power demands of the interface；It is another A test unit interface unpowered input, corresponding test unit are in off-position；

Two-shipper failure mode: two DC/DC modules that test unit power supply and distribution is intersected in recombination module fail, and relay K2~ K5 is in an off state entirely, and two groups of test units all power off, and power supply and distribution unit is by relay K1 to test unit power supply and distribution Intersect recombination module to be restarted；Intersect two DC/DC output voltages inside recombination module after restarting to turn if restoring normal Enter the work of two-shipper normal power supply mode, only individual module output voltage is extensive by two DC/DC if intersecting inside recombination module after restarting It is multiple normal, then it is transferred to single machine failure powering mode；If after restarting three times, the two DC/DC modules intersected inside recombination module are defeated Voltage keeps abnormal out, then powers off to K1, and system is reworked after failure is further repaired.

What 10. a kind of power supply and distribution Reconfigurable Control system according to claim 9 towards mass flight validation was realized Control method, it is characterised in that steps are as follows:

(1) power supply and distribution unit powers on rear DC/DC voltage transformation module and starts to work, and primary power source is converted to secondary power supply supply The work of other modules of power supply and distribution unit, FPGA complete configuration file load and initial work；Relay K1~K5 is in disconnected Open state goes to step (2)；

(3) FPGA intersects recombination module transmission telecommand to test unit power supply and distribution, successively closing relay K2 and K5, relay Device K3 and K4 are off-state；Or successively closing relay K3, K4, relay K2 and K5 are in an off state；Power supply and distribution unit Under two-shipper normal power supply mode, test unit power supply and distribution intersects two that two DC/DC modules in recombination module generate for work Secondary source is respectively outputted to two test unit interfaces, goes to step (4)；

(4) power supply and distribution unit is sent to the test unit of off-position by instruction interface circuit and is instructed, by each group test unit It is successively powered on according to priority, starts in-orbit flight test, meanwhile, the voltage and current Acquisition Circuit inside power supply and distribution unit is real-time Test unit supply voltage and electric current are acquired, is sent into the power consumption monitoring of FPGA module and it is expected that module, calculates test unit in real time Dynamic power consumption and monitoring test unit supply voltage and supply current whether there is exception；

If the supply current of test unit exceeds the test unit current threshold that FPGA internal preset is set, test unit switch Control module sends telecommand by instruction interface circuit and carries out power-off protection to the test unit, waits fault restoration；Its His test unit continues to be powered on work；

If the relay that some in relay K2~K5 should be closed can not be closed or abnormal disconnection, passes through telecommand and close The relay of another closed state, the relay being in an off state in rear closing relay K2~K5 before this are realized double Switching between machine normal power supply both of which；

If certain moment test unit input supply voltage is abnormal and not sent overcurrent, connected test unit power supply and distribution are handed over The DC/DC module failure in recombination module is pitched, FPGA passes through test unit switch control module and instruction interface circuit to the group Test unit sends remote power-off instruction, closes this group of total Test unit；The relay being connected with failure DC/DC module is disconnected afterwards Device realizes single machine failure power supply, goes to step (5)；

If certain moment battery of tests unit needs test unit power supply and distribution to intersect two DC/DC modules in recombination module while supplying Electricity, to complete the execution of in-orbit test mission, ground sends telecommand and gives power supply and distribution unit at this time, and FPGA passes through test unit Switch control module and instruction interface circuit send cut-offing instruction, close another group of test unit with the relay that is connected, will hand over Two groups of DC/DC modular power sources output of fork recombination module is switched to the test unit interface of this group of test unit connection, realizes Two-shipper centrally connected power supply enters step (6)；

(5) power supply and distribution unit receives ground remote control instruction or according to predetermined period parameter, switches the output control of health DC/DC module Relay processed, periodically to two groups of test unit interleaved powers；The alternately in-orbit flight test of two groups of test units；

If the single machine fails, failure DC/DC module is completed by reset, reboot operation reparation under powering mode, and voltage output is just Often, then power supply and distribution unit is closed the relay between the DC/DC module of the reparation and the test unit interface in off-position, extensive Multiple two-shipper normal power supply mode, returns to step (4)；

If it is abnormal to monitor that the output voltage of healthy DC/DC module occurs for power supply and distribution unit under single machine failure powering mode, Power supply and distribution unit send first instruction close total Test unit, after will in closed state DC/DC output relay disconnect, Into two-shipper failure operating mode, (8) are gone to step；

If two groups of test units must carry out test simultaneously, ground sends telecommand to power supply and distribution unit, is first shut off whole examinations Verification certificate member, it is rear to be closed two connected relays of health DC/DC module, so that the DC/DC module gives two groups of test units simultaneously Power supply, is fully loaded with operating mode into single machine, enters step (7)；

(6) relay switch is switched by sending telecommand according to test mission demand, so that two groups of test units alternately add Electricity work, the two DC/DC module outputs of diode pair for intersecting the power output end in recombination module carry out stream adjustment；

At the end of test unit task execution, ground sends telecommand and gives power supply and distribution unit, and power supply and distribution unit is by one group of DC/ DC module is outputted to the power supply of off-position test unit interface, restores two-shipper normal power supply mode, goes to step (4)；

If there is single DC/DC module output voltage abnormal at this time, power supply and distribution unit monitors that the failure disconnects the DC/DC module Output relay, into single machine fail powering mode, go to step (5)；

(7) in the case where single machine is fully loaded with operating mode, single DC/DC module is supplied by two test unit interfaces to two groups of test units Electricity, power supply and distribution unit is according to preset test unit priority, successively by test unit switch control and instruction interface circuit It sends the instruction of test unit remote-controlled start-up to be powered on test unit, until health status DC/DC module output power reaches its volume Surely the upper limit is exported；

If the DC/DC module worked normally under the mode breaks down, corresponding test unit is automatically closed in power supply and distribution unit, is broken The output relay for opening the DC/DC module goes to step (8) into two-shipper failure powering mode；

If failure DC/DC module completes fault recovery by restarting, resetting, output voltage is normal, then power supply and distribution unit is sent Command pulse disconnects arbitrarily a output control relay of DC/DC module of work at present, is switched to single machine failure powering mode, turns Step (5)；

(8) in the case where two-shipper fails operating mode, for total Test unit all in power-down mode, the intersection of power supply and distribution unit recombinates mould Two DC/DC modules in block break down, and power supply and distribution unit sends telecommand, close relay K1, intersect recombination mould Two DC/DC modules in block power off, and rear FPGA re-closes relay K1 to recombination module transmission telecommand is intersected, weight Intersection recombination module is opened, monitors whether two DC/DC modules export normally, is confirmed whether to repair and complete；

If two DC/DC modules repair completions simultaneously, give power supply and distribution unit by ground transmission telecommand, from FPGA module to Test unit power supply and distribution intersects recombination module and sends instruction, closes relay K2, K5 or K3, K4, returns to two-shipper normal power supply mould Formula is transferred to step (4)；

If single DC/DC module failure restores to complete, telecommand is sent by ground and gives power supply and distribution unit, from FPGA module to Intersect recombination module and send instruction, closes the connected any relay of the DC/DC module repaired and completed, be transferred to step (5)；

If can not still be repaired by adding power-off to attempt two DC/DC modules in intersection recombination module three times intersection recombination module It completes, then termination test task, closes relay K1, wait and further repairing.