CN101950002B - Comprehensive test method of small satellite power subsystem - Google Patents
Comprehensive test method of small satellite power subsystem Download PDFInfo
- Publication number
- CN101950002B CN101950002B CN 201010253639 CN201010253639A CN101950002B CN 101950002 B CN101950002 B CN 101950002B CN 201010253639 CN201010253639 CN 201010253639 CN 201010253639 A CN201010253639 A CN 201010253639A CN 101950002 B CN101950002 B CN 101950002B
- Authority
- CN
- China
- Prior art keywords
- test
- charging
- current
- ground
- battle array
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention discloses a comprehensive test method of a small satellite power subsystem. In the method, a solar cell array is replaced by a solar matrix simulator; a ground wired test and control platform of a satellite comprehensive test system is used to transmit wired instructions and collect important parameters; and ground test and control equipment, a remote measurement and control front end and a test computer are used to transmit remote control instructions and collect remote test data. After the satellite is electrified, the on operation time, off operation time and remote control command transmission time of the solar matrix simulator are reasonably controlled, the working state of a power subsystem is set, various parameters and states are monitored and interpreted, and thus, various test items are accomplished. In addition, a method of injecting normal or fault data blocks and program blocks is adopted to test the up injection function, reliability and fault tolerance are tested. The method has high test coverage, clear and definite flow, simple and reliable operation and convenient construction.
Description
Technical field
The present invention relates to a kind of integrated test facility that adopts charging battle array and the power supply gust full adjusting bus moonlet power subsystem of distinguishing to some extent.
Background technology
It is generally acknowledged that quality is that the satellite of 500～1000Kg belongs to moonlet.Power subsystem is as the TRT of moonlet; It is the source of the energy of whole satellite; Mainly form by power-supply controller of electric, battery pack, solar battery array etc.; Concentrate to realize the control function of satellite power supply subsystem through power-supply controller of electric, comprise busbar voltage adjustings, solar battery array output power flow-dividing control, battery pack discharge and recharge control and with the interface of other subsystem.The performance of power subsystem and functional characteristic directly affect the duty and the whole star life-span of other system.
After satellite comprehensive testing is meant that examination and the joint-trial of each subsystem through device level, subsystem level is qualified; General assembly is on satellite body; Supply under the distribution condition unified, the correctness and the compatibility of each subsystem electrical property of check satellite detect satellite and whether reach desired electrical performance indexes.In the satellite development process, need carry out complete, effective, reliable integration test to the satellite power supply subsystem, comprise many-sided contents such as function of supplying power, charging and shunting function, discharging function, instruction control, data acquisition, last pouring functions inspection.
On Dec 1st, 2002, the Chinese cosmonautics of public publication can the energy academic nd Annual Meeting in space be concentrated; The recapitulative integration test notion of introducing the space power system subsystem of paper of one piece " integration test technology of space power system system " by name; Enumerated the partial test project of space power system subsystem integration test; But the content measurement that does not have refinement especially lacks feasible test operating procedure, does not possess operability.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiency of prior art, the moonlet power subsystem that a kind of test event is perfect, clear process is clear and definite, easy and simple to handle integrated test facility is provided.
Technical solution of the present invention is: a kind of integrated test facility of moonlet power subsystem, and step is following:
(1) adopts sun square formation simulator to substitute solar battery array, and insert power subsystem with wired mode through umbilical connector; The wired monitoring and control unit in ground is connected with power subsystem with wired mode through umbilical connector; Test computer to the satellite transmission telecommand, receives satellite telemetry parameters with wired or wireless mode through remote measuring and controlling front end, ground observing and controlling equipment;
(2) the wired monitoring and control unit in ground sends and line is arranged " battery is logical " connects that battery switch makes satellite be in powering state on star, and the ground test computing machine sends " power supply slave computer A machine, A bus " telecommand power supply slave computer A machine A bus is set;
(3) sun square formation simulator moves back electricity, and the test of power subsystem discharging function is carried out in the battery pack discharge; The ground test computing machine sends " the charging battle array is broken off and connected " telecommand, and charging battle array on off test is accomplished in inspection and the corresponding telemetry parameter of charging battle array on off operating mode; The ground test computing machine sends " switching of V/T curve " telecommand, and inspection telemetry parameter " V/T curve state " is accomplished V/T curve switch test; The ground test computing machine sends " ampere-hour meter is broken off and connected " telecommand, and inspection telemetry parameter " ampere-hour meter on off operating mode " is accomplished the ampere-hour meter on off test;
(4) sun square formation simulator rises electricity, carries out the test of power subsystem V/T curve charge function; Different sun square formation simulator supply currents is set in charging process, and the test of hardware current-limiting function is carried out in inspection and the corresponding telemetry parameter of charging battle array current limliting on off operating mode; Wait for charging termination, accomplish the test of V/T curve charging function controlled, the test of two-stage charging control function;
(5) sun square formation simulator moves back electricity, makes the battery discharging electric weight greater than 2Ah, accomplishes the discharging function test under the battery pack ampere-hour meter control;
(6) the ground test computing machine sends " B bus " telecommand power supply slave computer bus state is set is the B bus; The ground test computing machine sends " software is current limiting enabled " telecommand, accomplishes the current limiting enabled instruction testing of software;
(7) sun square formation simulator rises electricity, and different sun square formation simulator supply currents is set, and the test of software current-limiting function is accomplished in inspection and the corresponding telemetry parameter of charging battle array current limliting on off operating mode;
(8) sun square formation simulator moves back electricity, and the ground test computing machine sends " hardware is current limiting enabled " telecommand, accomplishes the current limiting enabled instruction testing of hardware; The ground test computing machine sends " software is current limiting enabled " telecommand, and the current limiting enabled state of software of getting back to is set;
(9) sun square formation simulator rises electricity, and the ground test computing machine sends " charging battle array current limliting is broken off and connected " telecommand, and charging battle array current limliting break-make instruction testing is accomplished in inspection and the corresponding telemetry parameter of charging battle array current limliting on off operating mode; Wait for charging termination, accomplish the test of ampere-hour meter charge function;
(10) sun square formation simulator moves back electricity, makes the battery discharging electric weight greater than 2Ah, and sun square formation simulator rises electricity, and the ground test computing machine sends " charging termination " telecommand, and telemetry parameter " charging current " becomes 2.5A, accomplishes the charging termination functional test;
(11) sun square formation simulator moves back electricity, and the ground test computing machine injects normal or fault data piece, carries out pouring functions test on the data;
(12) the ground test computing machine injects normal or malfunction routine piece, carries out pouring functions test on the program;
(13) the ground test computing machine sends " power supply slave computer B machine, A bus " telecommand power supply slave computer B machine A bus is set, and repeating step (3) is to step (12);
(14) test finishes, and the ground test computing machine sends " power supply slave computer A machine, A bus " telecommand power supply slave computer A machine A bus is set; The wired monitoring and control unit in ground sends to be had line " battery is disconnected " breaks off that battery switch makes satellite be in off-position on the star.
The present invention's advantage compared with prior art is:
1, test event is perfect, and test coverage is good.The inventive method is to the technical characterstic and the design concept of moonlet power subsystem; Having analyzed needs the examination test contents; Worked out perfect test event; Comprise discharging function test, the test of V/T curve charging function controlled, the test of two-stage charging control function, the test of ampere-hour meter charge function, the test of software current-limiting function, the test of hardware current-limiting function, charging battle array on off test, V/T curve switch test, ampere-hour meter on off test, the current limiting enabled switch test of software and hardware, charging battle array current limliting break-make instruction testing, the test of remote control charging termination, the test of slave computer master backup handoff functionality, bus switch test, go up the pouring functions inspection, covered the various aspects of moonlet power subsystem integration test;
2, the testing process clear and definite is detailed.The inventive method is according to test event, according to the principle of substep order, standard operation step; Worked out clear and definite and detailed testing process; Each step of flow process has all provided content of operation and relevant parameters changes judgment criterion, and logic is good, has extremely strong operability;
3, operation is simple and reliable.The inventive method utilizes sun square formation simulator to substitute real solar battery array, utilizes ground observing and controlling equipment, remote measuring and controlling front end, test computer and wired monitoring and control unit of floor synthetic test macro to instruct and sends and parameter testing.Rise electricity and the operation opportunity of moving back electricity, ground checkout equipment instruction transmission opportunity through reasonable control sun square formation simulator; Clearly test successful parameter Rule of judgment; Only need simply instruct transmit operation and parameter to judge and just can accomplish test; Simple and convenient, and can effectively guarantee the safe reliability of testing.
Description of drawings
Fig. 1 is the theory of constitution and the test system structure block diagram of moonlet power subsystem;
Fig. 2 is the FB(flow block) of method of testing of the present invention.
Embodiment
As shown in Figure 1, be the theory of constitution and the test system structure block diagram of moonlet power subsystem.The full adjusting dc bus system that the moonlet power subsystem is distinguished for charging battle array and power supply battle array to some extent mainly is made up of power-supply controller of electric, battery pack, solar battery array etc.Power-supply controller of electric comprises shunting regulating circuit, charge adjustment circuit, charging/shunt controller, discharge regulator and power supply slave computer.
Among Fig. 1, solar battery array 1 only is used to the satellite power supply with solar battery array 2, can not be battery charging, is called power supply battle array 1 and power supply battle array 2; Solar battery array 3～solar battery array 8 can be supplied power for satellite, can be battery charging again, is called charging battle array 3～charging battle array 8.Charge adjustment circuit 1～charge adjustment circuit 6 is successively to inductive charging battle array 3～charging battle array 8.Concentrate the control function that realizes the satellite power supply subsystem through power-supply controller of electric, comprise that busbar voltage adjusting, solar battery array output power flow-dividing control and battery pack discharge and recharge control, are stabilized in the scope of 28.5 ± 1V busbar voltage.Power supply slave computer (comprising the A machine and the B machine of cold standby each other) is realized and the interface of Star Service subsystem through CAN bus A or B, receives the guidance command that the Star Service subsystem is sent, and sends telemetry to the Star Service subsystem.
Charging/shunt controller inside has charging battle array break-make pilot relay; Corresponding charging battle array on-off switch in charge adjustment circuit 1～charge adjustment circuit 6 is controlled; The telecommand of sending according to the power supply slave computer " charging battle array 3 is broken off ", " charging battle array 3 is connected ", " charging battle array 4 is broken off ", " charging battle array 4 is connected ", " charging battle array 5 is broken off ", " charging battle array 5 is connected " " charging battle array 6 is broken off ", " charging battle array 6 is connected " " charging Zhen 7 Duan Kais ", " Chong Dian Zhen 7 Jie Tongs ", " Chong Dian Zhen 8 Duan Kais ", " Chong Dian Zhen 8 Jie Tongs " are carried out break-make control to the charge adjustment circuit of phase inductive charging battle array.The power supply slave computer detects the executing state of instruction, and corresponding telemetry parameter " charging battle array 3 on off operating modes ", " charging battle array 4 on off operating modes ", " charging battle array 5 on off operating modes ", " charging battle array 6 on off operating modes ", " charging battle array 7 on off operating modes ", " charging battle array 8 on off operating modes " is set for breaking off or connecting.
In addition; Charge adjustment circuit 4～charge adjustment circuit 6 is successively to inductive charging battle array 6～charging battle array 8; Be the limit charging current size; Charge adjustment circuit 4～charge adjustment circuit 6 inside have charging current limiter break-make control metal-oxide-semiconductor electronic switch, and the charge adjustment circuit of phase inductive charging battle array is carried out break-make control.That is to say; Charging battle array 6～charging battle array 8 current limliting on-off functions both can be controlled through charge adjustment circuit by charging/shunt controller automatically; Can control by telecommand " charging battle array 6 current limlitings are disconnected ", " charging battle array 6 current limlitings are logical ", " charging battle array 7 current limlitings are disconnected ", " charging battle array 7 current limlitings are logical ", " charging battle array 8 current limlitings are disconnected ", " charging battle array 8 current limlitings are logical " that charging/shunt controller sends according to the power supply slave computer again; The power supply slave computer detects the instruction executing state, and corresponding telemetry parameter " charging battle array 6 current limliting on off operating modes ", " charging battle array 7 current limliting on off operating modes ", " charging battle array 8 current limliting on off operating modes " is set for breaking off or connecting.
The power supply slave computer is one of functional module of power-supply controller of electric, adopts A, the configuration of B machine two-shipper cold standby, and A, B machine all can be selected CAN bus A, B and Star Service compunication.Its major function is: accomplish the supervision and the control of power subsystem duty; Adopt ampere-hour meter and control method, independently accomplish the charge and discharge capacity accumulation of battery pack and calculate, and realize the charging termination control of battery pack; The autonomous software Current limited Control of accomplishing the battery charging electric current; Gather, handle the engineering parameter (comprising busbar voltage, load current, solar battery array electric current, charging current, discharge current, accumulator battery voltage, charging battle array 6～charging battle array 8 current limliting on off operating modes, charging battle array 3～charging battle array 8 on off operating modes etc.) of primary power source; Accomplish the response operation of CAN bus communication network protocol specifies; Receive indirect instruction and the data that the Star Service main frame transmits through CAN bus communication network, and carry out on request.
The power supply slave computer can also be carried out the notes program according to different pieces of information piece " program injection ", the telecommand " injecting program startup " that send on ground except can carrying out original program curing.When inject be normal procedure the time, it is injecting program that telemetry parameter " program user mode " is set; When inject be the fault program time, power supply slave computer watchdog reset, the power supply slave computer is carried out original program curing, and numerical value+1 of telemetry parameter " warm start counter " is set.
The controlled variable setting of different pieces of information piece " data injections " the telecommand modification power subsystem that the power supply slave computer sends according to ground (comprise accumulator electric-quantity, charge and discharge ratio, battery tension alarm threshold, software current limliting thresholding etc.).The power supply slave computer software is judged parameters such as battery tension, battery tension alarm thresholds, when surpassing normal allowed band, telemetry parameter " power safety status word " is set is corresponding ERST.
Software Current limited Control and hardware current-limiting function be cold standby each other, and the power supply slave computer is through " the hardware current-limiting function enables " and " the software current-limiting function enables " Instruction Selection Current limited Control mode, and telemetry parameter " Current limited Control state " is set is hardware or software.The hardware Current limited Control mainly independently detects comparison by charging/shunt controller through its internal hardware electronic circuit, and controls the opening and closing that the metal-oxide-semiconductor electronic switch is controlled the charging battle array through the charging current limiter break-make, guarantees that charging current is in certain scope.The software Current limited Control is mainly by the autonomous detection computations of power supply slave computer, and controls the opening and closing of charging battle array through charging current limiter break-make control electronic switch, guarantees that charging current is in certain scope.When the power supply slave computer resets with cutter, close the software Current limited Control automatically, open the hardware current-limiting function.The software Current limited Control is provided with the software current limliting upper limit and two thresholdings of software current limliting lower limit, and allows to revise this two threshold values through annotating on the data.
The logic of software Current limited Control is following:
(1) the power supply slave computer is periodically monitored telemetry parameter " charging current " through sampling resistor, when charging current greater than the software current limliting in limited time, send " charging battle array 8 current limlitings are disconnected " instruction automatically, turn-off charging battle array 8, continue monitoring telemetry parameter " charging current "; If after slave computer circle collection parameter next time, charging current still greater than prescribing a time limit on the software current limliting, is sent " charging battle array 7 current limlitings are broken " instruction automatically, turn-offs charging battle array 7, continuation monitoring telemetry parameter " charging current "; If after slave computer circle collection parameter next time, charging current still greater than prescribing a time limit on the software current limliting, is sent " charging battle array 6 current limlitings are broken " instruction automatically, turn-offs charging battle array 6.
(2) slave computer is periodically monitored telemetry parameter " charging current " through sampling resistor, when charging current less than the software current limliting under in limited time, send " charging battle array 6 current limlitings are logical " instruction automatically, connect charging battle array 6, continue monitoring telemetry parameter " charging current "; If after slave computer circle collection parameter next time, charging current still less than prescribing a time limit under the software current limliting, is sent " charging battle array 7 current limlitings are led to " instruction automatically, connects charging battle array 7, continuation monitoring telemetry parameter " charging current "; If after slave computer circle collection parameter next time, charging current still less than prescribing a time limit under the software current limliting, is sent " charging battle array 8 current limlitings are led to " instruction automatically, connects charging battle array 8.
Hardware current limliting and software Current limited Control logic are basic identical, and difference is: the software current limliting upper limit and software current limliting lower limit allow to annotate on the data and revise, and hardware current limliting upper and lower bound is the circuit fixed level, can not revise; Software Current limited Control function is realized that by the power supply slave computer hardware Current limited Control function is realized through the hardware electronic circuit by charging/shunt controller.
V/T curve hardware controls and the mutually redundant control model of slave computer ampere-hour meter software are adopted in power subsystem charging control.Behind V/T curve and ampere-hour meter control charging termination, get into the trickle charge state, it is trickle that telemetry parameter " trickle state " is set.The trickle charge state is divided into 2 stages, at first is the two-stage charged state; The two-stage charging transfers low current charge to after 30 minutes automatically.The two-stage charging current is about 2.5A, and the low current charge electric current is about 0.5A.
The control principle of V/T curve is: the charge volume of battery pack is the function of voltage that battery pack reaches; Therefore; The charging voltage that battery pack reached can be used as the sign whether battery pack is full of, and the end of charge voltage of battery pack is relevant with the temperature of battery pack.Therefore, stopping controlling features with voltage as battery charging is the curve of a voltage relative temperature, i.e. the V/T curve.Charging/shunt controller hardware electronic circuit detects comparison accumulator battery voltage and V/T curve end of charge voltage automatically; For a certain specific battery pack temperature, when the accumulator battery voltage charging arrived V/T curve end of charge voltage, the hardware electronic circuit was adjusted charging current automatically; It is constant to keep this voltage; And V/T termination level signal is changed to termination level, and promptly becoming 1 by 0, telemetry parameter this moment " V/T termination level " is for stopping.The power supply slave computer was selected to use which bar V/T curve according to the telecommand " V/T Curve selection master " that receives, " the V/T Curve selection is equipped with ", and telemetry parameter " V/T curve state " is set is main or be equipped with.
The content of ampere-hour meter control comprises: power supply slave computer continuous acquisition charge capacity and discharge electricity amount, and compare calculating by the requirement of correlation computations formula, obtain the current electric quantity of battery pack; After battery pack current electric quantity accumulative total reached Full Charge Capacity, the power supply slave computer sent " charging termination " instruction automatically, gets into the trickle charge state.Relative electric energy control is adopted in ampere-hour meter charging control, and promptly how many electric weight accumulator emits, and solar battery array just replenishes corresponding electric weight.
For avoiding resetting or switching etc. causes losing of accumulator electric-quantity parameter that ampere-hour meter control adding up because of slave computer, thereby the situation that influence the ampere-hour meter control function takes place, and every program restarts when moving; All at first adopt V/T curve controlled accumulator once to charge; Software is monitored V/T termination level signal always, after confirming that this signal becomes 1 by 0, thinks that the initial state of accumulator is clear and definite; Be in the Full Charge Capacity state, just can carry out ampere-hour meter charging control.The power supply slave computer is opened according to the telecommand " ampere-hour meter disconnection ", " the ampere-hour meter connection " that receive or is stopped the ampere-hour meter control function, and telemetry parameter " ampere-hour meter on off operating mode " is set for breaking off or connecting.
Also do not get into the two-stage during charged state in the battery charging process, charging/shunt controller can receive the telecommand " charging termination " that the power supply slave computer sends, and the battery charging electric current is set to about 2.5A.
As shown in Figure 1, when adopting the inventive method to carry out the integration test of satellite power supply subsystem, adopt sun square formation simulator (like the E4350B-J02 of Agilent company) to substitute solar battery array.Sun square formation simulator is connected with power subsystem with wired mode through umbilical connector, is used for simulated solar battery battle array.The wired monitoring and control unit in ground is connected with power subsystem with wired mode through umbilical connector, sends to power subsystem that accumulator leads to, accumulator breaks has line, collecting part important parameter (busbar voltage, load current etc.).Test computer is connected with the remote measuring and controlling front end through network interface, and the remote measuring and controlling front end passes through the another one network interface and is connected with ground observing and controlling equipment, and ground observing and controlling equipment is connected with measuring and controlling equipment on the satellite through the observing and controlling interface.Test computer sends telecommand to the remote measuring and controlling front end; The remote measuring and controlling front end sends to ground observing and controlling equipment after receiving telecommand and processing; Ground observing and controlling equipment receives the telecommand data that the remote measuring and controlling front end sends, and after further handling, sends to satellite.Ground observing and controlling equipment receives the descending telemetry of satellite, sends to the remote measuring and controlling front end after the processing, and the remote measuring and controlling front end receives the telemetry that ground observing and controlling equipment sends, and after further handling, sends to test computer.
As shown in Figure 2, be the integration test process flow diagram of moonlet power subsystem of the present invention.Test event comprises the discharging function test; The test of V/T curve charging function controlled; The test of two-stage charging control function; The test of ampere-hour meter charge function; The test of software current-limiting function; The test of hardware current-limiting function; Charging battle array on off test; V/T curve switch test; The ampere-hour meter on off test; The current limiting enabled switch test of software and hardware; Charging battle array current limliting break-make instruction testing; The test of remote control charging termination; The test of slave computer master backup handoff functionality; The bus switch test; Last pouring functions inspection.Step is following:
(1) carries out satellite and power up functional test; The wired monitoring and control unit in ground sends to be had line " battery is logical " connects that battery switch makes satellite be in powering state on star; Judge that powering up conditions for successful is: the parameter " busbar voltage " that the wired monitoring and control unit in ground collects is consistent with telemetry parameter " busbar voltage " and " load current " that " load current " and ground test computer acquisition are arrived, and in the design load scope.
After satellite powers up; Carry out power supply slave computer A machine, the test of A bus command; Test computer sends telecommand " power supply slave computer A machine ", " power supply slave computer A bus ", and judge that the test conditions for successful is: telemetry parameter " slave computer and bus state " is A machine A bus.
(2) sun square formation simulator moves back electricity, and power subsystem initial discharge functional test is carried out in the battery pack discharge; Judge that the test conditions for successful is: telemetry parameter " busbar voltage " is 28.5 ± 1V, and " accumulator battery voltage " is 22.5 ± 2.5V, and " solar battery array electric current " is 0A; " discharge current "＞0A; " charging current " is 0A, and " charging control mode " is the control of V/T curve, and " V/T termination level " be not for stopping; " trickle state " is non-trickle, and " Current limited Control state " is hardware.
After the discharging function test is accomplished; A gust on off test charges; This moment, the ground test computing machine sent telecommand " charging battle array 3 is broken off ", " charging battle array 3 is connected ", judged that the test conditions for successful is: telemetry parameter " charging battle array 3 on off operating modes " is followed successively by disconnection, connects; In this order, accomplish the on off test of charging battle array 4～charging battle array 8 successively.
After charging battle array on off test is accomplished; Carry out V/T curve switch test; The ground test computing machine sends telecommand " V/T Curve selection master ", " the V/T Curve selection is equipped with ", and judge that the test conditions for successful is: telemetry parameter " V/T curve state " is followed successively by active and standby.
After V/T curve switch test is accomplished; Carry out the ampere-hour meter on off test; The ground test computing machine sends telecommand " ampere-hour meter disconnection ", " ampere-hour meter connection ", and judge that the test conditions for successful is: telemetry parameter " ampere-hour meter on off operating mode " is followed successively by disconnection, connects.
(3) sun square formation simulator supply current is set greater than hardware current limliting lower limit and less than the hardware current limliting upper limit; Sun square formation simulator rises electricity, carries out the test of power subsystem V/T curve charge function, and judge that the test conditions for successful is: telemetry parameter " busbar voltage " is 28.5 ± 1V; " accumulator battery voltage " is 22.5 ± 2.5V; " solar battery array electric current "＞0A, " discharge current " are 0A, " charging current "＞2.5A.
In charging process, carry out the test of hardware current-limiting function, judge that the test conditions for successful is: sun square formation simulator supply current is set greater than the hardware current limliting upper limit, telemetry parameter " charging battle array 8 current limliting on off operating modes " is for breaking off; Sun square formation simulator supply current is set less than hardware current limliting lower limit, telemetry parameter " charging battle array 8 current limliting on off operating modes ", " charging battle array 7 current limliting on off operating modes ", " charging battle array 6 current limliting on off operating modes " are connection.
After the test of hardware current-limiting function is accomplished, carry out V/T curve charging function controlled test and the test of two-stage charging control function, judge that the test conditions for successful is: after charging continues a period of time; Telemetry parameter " V/T termination level " is for stopping; " trickle state " becomes " trickle ", and battery pack " current electric quantity " is a Full Charge Capacity, and " discharge electricity amount " and " charge capacity " is 0; " charging control mode " is the ampere-hour meter control; " charging current " becomes the about 2.5A of two-stage charging current value automatically, and telemetry parameter after 30 minutes " charging current " becomes about 0.5A, and charging finishes.
(4) sun square formation simulator is moved back electricity, battery pack gets into discharge condition, carries out the discharging function test under the battery pack ampere-hour meter control; Judge that the test conditions for successful is: telemetry parameter " V/T termination level " is termination, and battery pack " charging current " is 0A, " discharge current "＞0A; " current electric quantity " constantly reduces; " discharge electricity amount " constantly increases, and discharge sustain is after a period of time, and telemetry parameter " discharge electricity amount " is greater than 2Ah.
(5) carry out power supply slave computer B bus test, the ground test computing machine sends telecommand " power supply slave computer B bus ", and judge that the test conditions for successful is: the bus state in " slave computer and bus state " is the B bus.
Power supply slave computer B bus test carries out the current limiting enabled instruction testing of software after accomplishing, and the ground test computing machine sends telecommand " software is current limiting enabled ", and judge that the test conditions for successful is: telemetry parameter " Current limited Control state " is a software.
(6) carry out the test of software current-limiting function; Judge that the test conditions for successful is: sun square formation simulator is risen; Sun square formation simulator supply current is set greater than the software current limliting upper limit; Then telemetry parameter " charging battle array 8 current limliting on off operating modes " for breaking off, is provided with sun square formation simulator supply current less than software current limliting lower limit, and telemetry parameter this moment " charging battle array 8 current limliting on off operating modes ", " charging battle array 7 current limliting on off operating modes ", " charging battle array 6 current limliting on off operating modes " are connection.
(7) sun square formation simulator moves back electricity, telemetry parameter " discharge current "＞0A; Carry out the current limiting enabled instruction testing of hardware; And the current limiting enabled state of software is got back in setting; The ground test computing machine sends telecommand " hardware is current limiting enabled " " software is current limiting enabled ", and judge that the test conditions for successful is: telemetry parameter " Current limited Control state " is followed successively by hardware, software;
(8) sun square formation simulator rises electricity, telemetry parameter battery pack " charging current "＞0, and " charge capacity " beginning constantly adds up; A gust current limliting on off test charges; Judge that the test conditions for successful is: sun square formation simulator supply current is set less than the software current limliting upper limit and greater than software current limliting lower limit, telemetry parameter this moment " charging battle array 8 current limliting on off operating modes ", " charging battle array 7 current limliting on off operating modes ", " charging battle array 6 current limliting on off operating modes " are connection; The ground test computing machine sends telecommand " charging battle array 6 current limlitings are disconnected ", " charging battle array 6 current limlitings are logical ", and telemetry parameter " charging battle array 6 current limliting on off operating modes " is followed successively by disconnection, connects; Send telecommand " charging battle array 7 current limlitings are disconnected ", " charging battle array 7 current limlitings are logical ", telemetry parameter " charging battle array 7 current limliting on off operating modes " is followed successively by disconnection, connects; Send telecommand " charging battle array 8 current limlitings are disconnected ", " charging battle array 8 current limlitings are logical ", telemetry parameter " charging battle array 8 current limliting on off operating modes " is followed successively by disconnection, connects.
After charging battle array current limliting on off test is accomplished; Carry out the test of ampere-hour meter charging control function, judge that the test conditions for successful is: after charging continued a period of time, telemetry parameter " trickle state " became " trickle "; Battery pack " current electric quantity " is a Full Charge Capacity; " discharge electricity amount " and " charge capacity " is 0, and " charging current " becomes the about 2.5A of two-stage charging current value automatically, and telemetry parameter after 30 minutes " charging current " becomes about 0.5A.
(9) sun square formation simulator is moved back electricity, battery pack gets into discharge condition, telemetry parameter " discharge current "＞0A, and " charging current " is 0A, battery pack " current electric quantity " constantly reduces, and waits for that telemetry parameter " discharge electricity amount " is greater than 2Ah; Sun square formation simulator rises; Telemetry parameter battery pack " charging current " is greater than 2.5A; Carry out the charging termination functional test, ground checkout equipment sends telecommand " charging termination ", and judge that the test conditions for successful is: telemetry parameter battery pack " charging current " is about 2.5A.
(10) sun square formation simulator moves back; Battery pack gets into discharge condition, and telemetry parameter " charging current " is 0A, " discharge current "＞0A; Carry out the test of data function of injecting; Ground test the computer sends the data piece " data injection " is changed accumulator electric-quantity, is charged and discharged than setting, the setting of battery tension alarm threshold, judges that the test conditions for successful is: telemetry relevant parameter and injection data consistent; When the data of injecting surpass normal allowed band, observe telemetry parameter " power safety status word " and change into corresponding ERST.
(11) after the test of data function of injecting is accomplished; Carry out the test of program function of injecting; Ground test the computer sends the data piece " program injection ", instruction " injecting program startup "; Judge that the test conditions for successful is: when inject be normal procedure the time telemetry parameter " program user mode " be injecting program, the power subsystem telemetry parameter is correct; When inject be the fault program time power supply slave computer watchdog reset, numerical value+1 of telemetry parameter " warm start counter ".
(12) the mechanical, electrical source of power supply slave computer B slave computer A bus command test; The ground test computing machine sends telecommand " power supply slave computer B machine ", " power supply slave computer A bus ", and judge that the test conditions for successful is: telemetry parameter " slave computer and bus state " is B machine A bus.
Repeating step (2) is accomplished the test of power supply slave computer B machine to step (11).
(13) the ground test computing machine sends telecommand " power supply slave computer A machine ", " power supply slave computer A bus ", and telemetry parameter " slave computer and bus state " is an A machine A bus.Carry out the test of satellite power down function; The wired monitoring and control unit transmission in ground has line " battery is disconnected " to break off battery switch on the star; Make satellite be in off-position; Judge that the test conditions for successful is: parameter " busbar voltage " and " load current " that the wired monitoring and control unit in ground collects are 0, and satellite telemetering data disappears.
The content of not doing to describe in detail in the instructions of the present invention belongs to those skilled in the art's known technology.
Claims (2)
1. the integrated test facility of a moonlet power subsystem is characterized in that step is following:
(1) adopts sun square formation simulator to substitute solar battery array, and insert power subsystem with wired mode through umbilical connector; The wired monitoring and control unit in ground is connected with power subsystem with wired mode through umbilical connector; Test computer to the satellite transmission telecommand, receives satellite telemetry parameters with wired or wireless mode through remote measuring and controlling front end, ground observing and controlling equipment;
(2) the wired monitoring and control unit in ground sends and line is arranged " battery is logical " connects that battery switch makes satellite be in powering state on star, and the ground test computing machine sends " power supply slave computer A machine, A bus " telecommand power supply slave computer A machine A bus is set;
(3) sun square formation simulator moves back electricity, and the test of power subsystem discharging function is carried out in the battery pack discharge; The ground test computing machine sends " the charging battle array is broken off and connected " telecommand, and charging battle array on off test is accomplished in inspection and the corresponding telemetry parameter of charging battle array on off operating mode; The ground test computing machine sends " switching of V/T curve " telecommand, and inspection telemetry parameter " V/T curve state " is accomplished V/T curve switch test; The ground test computing machine sends " ampere-hour meter is broken off and connected " telecommand, and inspection telemetry parameter " ampere-hour meter on off operating mode " is accomplished the ampere-hour meter on off test;
(4) sun square formation simulator rises electricity, carries out the test of power subsystem V/T curve charge function; Different sun square formation simulator supply currents is set in charging process, and the test of hardware current-limiting function is carried out in inspection and the corresponding telemetry parameter of charging battle array current limliting on off operating mode; Wait for charging termination, accomplish the test of V/T curve charging function controlled, the test of two-stage charging control function;
(5) sun square formation simulator moves back electricity, makes the battery discharging electric weight greater than 2Ah, accomplishes the discharging function test under the battery pack ampere-hour meter control;
(6) the ground test computing machine sends " B bus " telecommand power supply slave computer bus state is set is the B bus; The ground test computing machine sends " software is current limiting enabled " telecommand, accomplishes the current limiting enabled instruction testing of software;
(7) sun square formation simulator rises electricity, and different sun square formation simulator supply currents is set, and the test of software current-limiting function is accomplished in inspection and the corresponding telemetry parameter of charging battle array current limliting on off operating mode;
(8) sun square formation simulator moves back electricity, and the ground test computing machine sends " hardware is current limiting enabled " telecommand, accomplishes the current limiting enabled instruction testing of hardware; The ground test computing machine sends " software is current limiting enabled " telecommand, and the current limiting enabled state of software of getting back to is set;
(9) sun square formation simulator rises electricity, and the ground test computing machine sends " charging battle array current limliting is broken off and connected " telecommand, and charging battle array current limliting break-make instruction testing is accomplished in inspection and the corresponding telemetry parameter of charging battle array current limliting on off operating mode; Wait for charging termination, accomplish the test of ampere-hour meter charge function;
(10) sun square formation simulator moves back electricity, makes the battery discharging electric weight greater than 2Ah, and sun square formation simulator rises electricity, and the ground test computing machine sends " charging termination " telecommand, and telemetry parameter " charging current " becomes 2.5A, accomplishes the charging termination functional test;
(11) sun square formation simulator moves back electricity, and the ground test computing machine injects normal or fault data piece, carries out pouring functions test on the data;
(12) the ground test computing machine injects normal or malfunction routine piece, carries out pouring functions test on the program;
(13) the ground test computing machine sends " power supply slave computer B machine, A bus " telecommand power supply slave computer B machine A bus is set, and repeating step (3) is to step (12);
(14) test finishes, and the ground test computing machine sends " power supply slave computer A machine, A bus " telecommand power supply slave computer A machine A bus is set; The wired monitoring and control unit in ground sends to be had line " battery is disconnected " breaks off that battery switch makes satellite be in off-position on the star.
2. the integrated test facility of a kind of moonlet power subsystem according to claim 1 is characterized in that: described sun square formation simulator is the E4350B-J02 of Agilent company.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010253639 CN101950002B (en) | 2010-08-13 | 2010-08-13 | Comprehensive test method of small satellite power subsystem |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010253639 CN101950002B (en) | 2010-08-13 | 2010-08-13 | Comprehensive test method of small satellite power subsystem |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101950002A CN101950002A (en) | 2011-01-19 |
| CN101950002B true CN101950002B (en) | 2012-05-23 |
Family
ID=43453569
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010253639 Active CN101950002B (en) | 2010-08-13 | 2010-08-13 | Comprehensive test method of small satellite power subsystem |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101950002B (en) |
Families Citing this family (40)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102289535B (en) * | 2011-06-07 | 2013-03-20 | 北京航空航天大学 | Spacecraft power system energy analysis simulation platform |
| CN102707714A (en) * | 2012-06-18 | 2012-10-03 | 上海卫星工程研究所 | General test equipment applied to satellite-borne power distribution type single machine |
| CN102931706B (en) * | 2012-10-31 | 2015-02-11 | 航天东方红卫星有限公司 | Space-borne software current limit controlling method for two-stage current charge of storage batteries |
| CN103235270B (en) * | 2013-04-15 | 2015-02-18 | 北京空间飞行器总体设计部 | Reliability testing device for star power system of lunar probe |
| CN103336249B (en) * | 2013-06-18 | 2015-06-10 | 北京空间飞行器总体设计部 | Self-management emulation proof system of power system of navigational satellite |
| CN103913672B (en) * | 2014-03-20 | 2017-01-04 | 中国空间技术研究院 | A kind of satellite low frequency interface automatization test system |
| CN104267690A (en) * | 2014-09-22 | 2015-01-07 | 深圳市航天新源科技有限公司 | Inner bus system of satellite power supply controller |
| CN104297699B (en) * | 2014-09-26 | 2017-03-15 | 航天东方红卫星有限公司 | A kind of satellite power supply health status tracking and detection method based on intelligent interpretation |
| CN104462188B (en) * | 2014-10-23 | 2017-09-12 | 北京空间飞行器总体设计部 | A kind of method of testing and system of the planning of spacecraft intelligent task |
| CN105827100A (en) * | 2016-04-21 | 2016-08-03 | 哈尔滨工业大学 | Satellite power source sequential shunt regulator with abnormal injection function |
| CN106547003B (en) * | 2016-09-22 | 2019-03-22 | 北京空间飞行器总体设计部 | A kind of timesharing multipurpose telemetry system based on return mission requirements |
| CN106503317B (en) * | 2016-10-12 | 2022-08-05 | 深圳航天东方红卫星有限公司 | Energy supply test system based on V-I curve simulation technology |
| CN106569147B (en) * | 2016-10-31 | 2019-01-15 | 航天东方红卫星有限公司 | A kind of small satellite power subsystem test method based on lithium-ions battery group |
| CN106771704B (en) * | 2016-11-15 | 2019-04-30 | 航天东方红卫星有限公司 | A kind of agility satellite power system power supply balanced capacity closed loop test method |
| CN108089074A (en) * | 2016-11-23 | 2018-05-29 | 北京空间技术研制试验中心 | Spacecraft power supply buses voltage overshoot detection device |
| CN106772116B (en) * | 2016-11-28 | 2019-02-15 | 北京卫星制造厂 | A kind of Auto-Test System for aerospace satellite secondary power supply |
| CN107425560B (en) * | 2017-05-17 | 2018-11-23 | 上海卫星工程研究所 | Low orbit satellite lithium-ions battery group charge and discharge safety control method |
| CN109146213B (en) * | 2017-06-16 | 2022-04-12 | 北京航空航天大学 | Spacecraft power system health management verification and evaluation environment system |
| CN107621786A (en) * | 2017-08-16 | 2018-01-23 | 中国电子科技集团公司第十八研究所 | A kind of space power system control device worst case analysis method |
| CN107798164A (en) * | 2017-09-12 | 2018-03-13 | 北京空间飞行器总体设计部 | A kind of high rail satellite power supply control device accelerated life test system and method |
| CN107991621A (en) * | 2017-11-24 | 2018-05-04 | 上海微小卫星工程中心 | It is a kind of can analog satellite accumulator cell charging and discharging curve test device and method |
| CN108279388A (en) * | 2018-02-05 | 2018-07-13 | 哈尔滨工业大学 | A kind of injection of Switching Power Supply fault simulation and testability analysis device and method |
| CN108549355B (en) * | 2018-03-16 | 2019-11-19 | 西北工业大学 | A kind of cube star generalization ground fast testing system |
| CN109038512B (en) * | 2018-08-08 | 2019-11-05 | 上海空间电源研究所 | The anti-wired instruction cycle BIT in outside is reported by mistake therefore circuit and control method |
| CN111220923A (en) * | 2018-11-26 | 2020-06-02 | 深圳市泰斯电子有限公司 | Battery or battery protection board detection method based on big data management |
| CN109606752B (en) * | 2018-12-12 | 2021-12-21 | 上海空间电源研究所 | Method and system for testing illumination path of low-orbit spacecraft |
| CN109814530B (en) * | 2019-01-28 | 2021-02-05 | 中国空间技术研究院 | Automatic performance test system for satellite power supply controller |
| CN110824269B (en) * | 2019-09-26 | 2022-08-12 | 中国空间技术研究院 | Power supply and distribution joint test verification system and method based on comprehensive electronic system |
| CN110749790A (en) * | 2019-10-21 | 2020-02-04 | 中国科学院微小卫星创新研究院 | Comprehensive test fault positioning method |
| CN110824369A (en) * | 2019-10-23 | 2020-02-21 | 中国空间技术研究院 | Satellite discharge depth overrun diagnosis and recovery test method |
| CN111025175B (en) * | 2019-11-06 | 2022-06-03 | 中国空间技术研究院 | Automatic joint test method for primary power subsystem of high-orbit communication satellite |
| CN110927595B (en) * | 2019-12-17 | 2021-01-01 | 北京空间飞行器总体设计部 | Ampere-hour meter electric quantity calculation method of spacecraft storage battery |
| CN112731156B (en) * | 2020-12-10 | 2023-07-25 | 中国西安卫星测控中心 | Method and device for removing abnormal parameters of satellite storage battery current data |
| CN112947358B (en) * | 2021-01-25 | 2022-09-23 | 航天科工空间工程发展有限公司 | Vehicle-mounted comprehensive test system and method for testing mobile launching satellite |
| CN112953381B (en) * | 2021-02-04 | 2021-12-14 | 中国科学院微小卫星创新研究院 | Ground test method for solar cell array driving device |
| CN112803574A (en) * | 2021-03-23 | 2021-05-14 | 中国人民解放军国防科技大学 | Multi-stage security protection method and system for small satellite power supply |
| CN113346939B (en) * | 2021-05-31 | 2023-03-21 | 长光卫星技术股份有限公司 | Satellite instruction uploading system with narrow-band communication and information forwarding functions |
| CN114039686B (en) * | 2022-01-10 | 2022-03-25 | 成都国星宇航科技有限公司 | Automatic semi-physical satellite energy testing system and method |
| CN115314138B (en) * | 2022-09-29 | 2023-03-24 | 北京航天驭星科技有限公司 | Satellite remote control command issuing method and related equipment |
| CN116263595B (en) * | 2022-11-16 | 2024-05-10 | 长光卫星技术股份有限公司 | Universal automatic test platform for satellite single machine environment test and control method thereof |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6175241B1 (en) * | 1999-02-19 | 2001-01-16 | Micron Technology, Inc. | Test carrier with decoupling capacitors for testing semiconductor components |
| US6968302B1 (en) * | 1999-08-11 | 2005-11-22 | Agilent Technologies, Inc. | System and method for remote analysis and control of test and measurement devices |
| US6889147B2 (en) * | 2002-09-17 | 2005-05-03 | Hydrogenics Corporation | System, computer program product and method for controlling a fuel cell testing device |
| CN100432691C (en) * | 2005-01-21 | 2008-11-12 | 新源动力股份有限公司 | Automatic detection platform for performance of air compressor for fuel cell system |
| CN1858613B (en) * | 2005-05-08 | 2010-08-11 | 王宏栋 | Detecting method and device for lithium ion cell material |
| CN2909282Y (en) * | 2005-10-26 | 2007-06-06 | 中国北方车辆研究所 | Testing box for safety property of power battery of electric motor car |
-
2010
- 2010-08-13 CN CN 201010253639 patent/CN101950002B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN101950002A (en) | 2011-01-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101950002B (en) | Comprehensive test method of small satellite power subsystem | |
| CN104158259B (en) | Based on the vehicle-mounted charge/discharge control method of V2G technology | |
| CN102801208B (en) | Multi-path power supply intelligent scheduling manager and control method thereof | |
| CN104300669B (en) | Nuclear power station dc source mixed power supply system | |
| CN111452665B (en) | Intelligent charging and battery replacing cabinet for electric bicycle | |
| CN109586361B (en) | Lithium battery energy storage power supply system | |
| CN205565901U (en) | Transformer substation storage cell organizes intelligent management system | |
| CN109449944B (en) | Bidirectional direct-current power supply control system and method for transformer substation | |
| CN104810886A (en) | Intelligent storage battery pack and connecting circuit thereof | |
| CN105743190A (en) | Intelligent power source adaption system | |
| CN112816896A (en) | Dual-power direct-current system battery pack remote nuclear capacity control system and control method | |
| CN203434637U (en) | Energy storage system | |
| CN205015400U (en) | Storage battery internal resistance measuring device | |
| CN202721445U (en) | Intelligent reactive power compensation integrated module | |
| CN103812210A (en) | Intelligent monitoring system for alternating current-direct current uninterruptible power supply system | |
| CN201359640Y (en) | Intelligent power supply surface observation and report machine | |
| CN202330669U (en) | Intelligent on-line monitoring system for lithium battery | |
| CN102931706B (en) | Space-borne software current limit controlling method for two-stage current charge of storage batteries | |
| CN108695566B (en) | Synchronous control system architecture for improving energy-saving efficiency | |
| CN215813253U (en) | Remote control system for checking capacity of communication power supply storage battery | |
| CN214154122U (en) | Ground redundant power supply system for carrier rocket | |
| CN204761067U (en) | Communication energy storage power supply system | |
| CN208078632U (en) | A kind of intelligent substation tranformer protection system | |
| CN113030747A (en) | Station storage battery pack checking discharge test system | |
| CN107968404B (en) | Power management system and method for overhead line data acquisition terminal |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |