CN103197187B - Verifying equipment for detector power supply and distribution test system - Google Patents
Verifying equipment for detector power supply and distribution test system Download PDFInfo
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- CN103197187B CN103197187B CN201310128836.5A CN201310128836A CN103197187B CN 103197187 B CN103197187 B CN 103197187B CN 201310128836 A CN201310128836 A CN 201310128836A CN 103197187 B CN103197187 B CN 103197187B
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Abstract
The invention discloses verifying equipment for a detector power supply and distribution test system. The verifying equipment comprises a landing device equivalent device and a patrolling device equivalent device. The verifying equipment can verify correctness and reliability of ground power supply and distribution equipment and correctness of an instruction path, and effectively avoids damage on satellites. Moreover, a key switch and a voltmeter are selected for carrying out a strobing test on a tested circuit, components are reduced, and therefore cost is saved and use is flexible and convenient. Verifying components and circuits of a landing device and a patrolling detector are respectively integrated into one machine case to be solidified with an interface of the ground power supply and distribution equipment, and therefore the verifying equipment has the advantages of being convenient to transport and high in stability, and can not be damaged easily.
Description
Technical field
The present invention relates to spacecraft-testing field, be specifically related to a kind of Authentication devices of detector power supply and distribution test system.
Background technology
It is China realizes landing detection first spacecraft at extratellurian celestial body that lander carries tour detection rover, after lander and inspection prober have been researched and developed, have and ground test is carried out to both, because lander and inspection prober rely on the solar wing carried to absorb solar electrical energy generation at moonscape, and the form that solar wing cannot be adopted during ground experiment to generate electricity is powered to lander and inspection prober, therefore, for tie surface test, have developed ground power supply and distribution equipment, this equipment is powered to lander or inspection prober by adopting the sun square formation simulator simulated solar wing, also be provided with multiple with lander with the interface of inspection prober in equipment, receive the analog signals of lander and inspection prober transmission, send controlled quentity controlled variable signal to lander and inspection prober simultaneously, realize the electricity function index to ground power supplying and distributing equipment, Non-follow control function, the detection of machine control function, because lander and rover involve great expense, equipment is meticulous, first with ground power supply and distribution equipment connection before, need the correctness of the computer software design first verifying ground power supply and distribution equipment and ground power supply and distribution test equipment and on-board equipment, the inspection of the harmony of solar cell array simulator interface, guarantee the correct of ground power supply and distribution equipment, reliably work, need the equivalent of the apparatus researching and developing lander and inspection prober thus, ground power supplying and distributing equipment is tested, by ground power supply and distribution equipment, electrical testing is added to lander and inspection prober again after success, guarantee that lander and inspection prober are not damaged.
Summary of the invention
In view of this, the invention provides a kind of Authentication devices of detector power supply and distribution test system, can verify the working regularity of ground power supplying and distributing equipment and correctness.
The Authentication devices of a kind of detector power supply and distribution test system of the present invention, comprises lander simulator and rover simulator, wherein:
Described lander simulator comprises cabinet, front panel, rear panel, power analog circuit, downstream analog amount circuit, up-on command mimic channel, is separated umbilical connector state simulation circuit, the power module being arranged on cabinet inside, heat radiator and electric fan, wherein, front panel and rear panel are embedded on former and later two openings of cabinet respectively, and cable switching plate is arranged on cabinet inside near rear panel; 220V ac plug rear panel being provided with two breakaway plugs, a pull-off plug and being connected with ground power supply and distribution equipment, wherein breakaway plug was used in the ground experiment stage, the attachment plug of satellite and ground power supply and distribution equipment, the cable of one of them breakaway plug for transferring in power analog circuit, all lines of another breakaway plug for transferring in downstream analog amount circuit and up mimic channel; Pull-off plug is used for the connection between Simulated Spacecraft and lander; 220V ac plug is used for powering from ground power supply and distribution equipment to power module; Cable from behind plate plug access after, then front panel and power module switching;
Described power module, according to the power supply characteristic in lander, converts the 220V alternating current fetched from 220V ac plug to 30V, 28V, 12V ,-12V and 5V direct current;
The electric energy that described power analog circuit produces for consuming sun square formation in lander, and show each sun square formation and whether be in normal operating conditions;
Described downstream analog amount circuit is used for testing and display lander battery voltage, satellite busbar voltage, 12V supply voltage ,-12V supply voltage, 5V supply voltage; Downstream analog amount circuit comprises 5 current-limiting resistances, one end of each current-limiting resistance is connected with the 28V power supply in power module, 30V power supply, 12V power supply ,-12V power supply, 5V power supply respectively, the other end is divided into two-way, one tunnel is connected with the test lead of ground power supply and distribution equipment, obtains voltage and current for detecting individual channel power supply; Another road is received on a key terminal of key switch, when place key switch is pressed, voltage table shows voltage;
Up-on command mimic channel for simulate and verify pass to lander from ground power supply and distribution equipment lander battery discharging switch open command, instruction power module cuts backup instruction, wired SMU adds cut-offing instruction circuit and simulation satellite and the rocket separation signal, wherein:
Described wired SMU adds cut-offing instruction circuit and comprises two diodes, two current-limiting resistances, two double-contact relays being embedded in the LED on front panel and being placed on cable switching plate; A current-limiting resistance and a Diode series composition leadage circuit, each leadage circuit in parallel in two ends of two line bags of relay, and diode cathode one terminated line bag positive pole one end; The minus earth of two line bags of relay, two line bag positive pole one end and a K switch controlled by ground power supply and distribution equipment respectively 1 and the K switch 2 of connecting between+28V power supply, the wired SMU power up signal of the closed simulation of K switch 1, the wired SMU power-off signal of the closed simulation of K switch 2; The positive pole of two groups of contacts of relay all connects+5V power supply, and the negative pole of contact is connected in series ground connection after a divider resistance and a LED;
Instruction power module is cut backup instruction circuit, simulation satellite and the rocket demultiplexing circuit and lander battery discharging switch disconnection mimic channel and is included a single contact relay, two diodes, a current-limiting resistance and LED: single contact relay is placed on cable switching plate, and LED etc. are arranged on front panel; Line bag one end and the switch controlled by ground power supply and distribution equipment of connecting between 28V power supply of single contact relay, relay line bag other end ground connection; The leadage circuit parallel connection that diode and current-limiting resistance are composed in series wraps two ends online, and the terminal of relay contact one end connects the 5V power supply of power module, and the other end is connected in series ground connection after a divider resistance and a LED; After the described instruction power module switch cut in backup instruction circuit, simulation satellite and the rocket demultiplexing circuit and lander battery discharging switch disconnection mimic channel closes, dummy instruction power module cuts backup instruction, simulation satellite and the rocket separation signal and lander battery discharging switch cut-off signal respectively;
Being separated umbilical connector state simulation circuit is arranged in pull-off plug, shows lander simulator and be connected with it or the state of disengaging in ground power supply and distribution equipment;
Rover simulator comprises the second cabinet, second face plate, second flank plate, the second power analog circuit, the second downstream analog amount circuit, the second up-on command mimic channel, the second source module being arranged on the second cabinet inside, the second heat radiator and an electric fan, wherein, second face plate and second flank plate are embedded on former and later two openings of the second cabinet respectively, and the second cable switching plate is arranged on the second cabinet inside near second flank plate; Second flank plate is provided with the second breakaway plug, a signal imitation plug, two power plug and a 220V ac plug be connected with ground power supply and distribution equipment, wherein the second breakaway plug was used in the ground experiment stage, the attachment plug of satellite and ground power supply and distribution equipment, all lines simultaneously also for transferring in up mimic channel, signal imitation plug is for downstream analog amount circuit of transferring; The cable of two power plug for transferring in the second power analog circuit, cable after the plug access of second flank plate, then is transferred to second face plate and second source module;
Described second source module, according to the power supply characteristic in rover, converts the 220V alternating current fetched from 220V ac plug to 30V, 28V, 12V ,-12V and 5V direct current;
The electric energy that described second power analog circuit produces for consuming sun square formation in rover, and show each sun square formation and whether be in normal operating conditions;
Second downstream analog amount circuit is used for testing and display rover battery voltage, satellite busbar voltage, 12V supply voltage ,-12V supply voltage; Second downstream analog amount circuit comprises 4 current-limiting resistances, one end of each current-limiting resistance is connected with the 28V power supply in second source module, 30V power supply, 12V power supply ,-12V power supply respectively, the other end is divided into two-way, one tunnel is connected with the test lead of ground power supply and distribution equipment, for detecting the voltage and current of individual channel power supply; Another road is received on a key terminal of the second key switch, when place key switch is pressed, the second voltage table shows voltage;
Second up-on command mimic channel for simulating and verify rover battery discharging switch open command from ground power supply and distribution equipment to rover, rover primary power source bus-tie circuit breaker state, two device charge and discharge switch states, central computer A electromechanical source state and the central computer B electromechanical source state uploaded from, wherein:
Rover battery discharging switch open command circuit, rover primary power source bus-tie circuit breaker state, two device charge and discharge switch states, central computer A electromechanical source state and central computer B electromechanical source state include a single contact relay, two diodes, current-limiting resistance and LED, single contact relay is placed on cable switching plate, and LED etc. are arranged on front panel; Line bag one end and the switch controlled by ground power supply and distribution equipment of connecting between 28V power supply of single contact relay, relay line bag other end ground connection; The leadage circuit parallel connection that diode and current-limiting resistance are composed in series wraps two ends online, and the terminal of relay contact one end connects the 5V power supply of power module, and the other end is connected in series ground connection after a divider resistance and a LED; Simulate rover battery discharging switch open command circuit, rover primary power source bus-tie circuit breaker state, two device charge and discharge switch states, central computer A electromechanical source state and central computer B electromechanical source state respectively after switch in described rover battery discharging switch open command circuit, rover primary power source bus-tie circuit breaker state, two device charge and discharge switch states, central computer A electromechanical source state and central computer B electromechanical source state is closed, and shown by LED;
Mock survey 7 groups of up-on command implementation status circuit comprise two device separation simulation circuit, rover battery discharging switch on and off circuit, rover primary power source bus-tie circuit breaker on-off circuit, two device charge and discharge switch on-off circuits, instruction power+28V on-off circuit, rover central computer A on-off circuit, rover central computer B on-off circuit, above-mentioned 7 circuit include two diodes, two current-limiting resistances, two double-contact relays being embedded in the LED on front panel and being placed on cable switching plate, a current-limiting resistance and a Diode series composition leadage circuit, the each leadage circuit in parallel in two ends of two line bags of relay, and diode cathode one terminated line bag positive pole one end, the minus earth of two line bags of relay, two line bag positive pole one end and a K switch controlled by ground power supply and distribution equipment respectively 1 and the K switch 2 of connecting between+28V power supply, the power up signal of K switch 1 closed simulation place circuit, K switch 2 closed simulation place contactor power-off signal, the positive pole of two groups of contacts of relay all connects+5V power supply, and the negative pole of contact is connected in series ground connection after a divider resistance and a LED.
Described lander simulator also comprises the cable switching plate be arranged near rear panel side in described cabinet, for after the wire cable layout accessed from described plug, then front panel and power module switching.
Power analog circuit in described lander simulator comprises 12 power resistors, 12 LED, a voltage table and electric fans, and the key switch be embedded on front panel, wherein 12 power resistors are placed on above heat radiator, and electric fan is arranged on heat radiator bottom; Voltage table and all LED are embedded on front panel; A power resistor and a LED are cascaded; The front end of each power resistor side is connected with 1 square formation in the sun emulation simulator on the lander that rear panel accesses by cable switching plate, the rear end ground connection of corresponding LED, form 12 power flow thus, whether LED has power to input for showing place path; The rear end of the LED side of every bar power flow is connected with a key terminal of key switch input end respectively, and the terminal of key switch output terminal is in parallel with one end of voltage table, and the other end of voltage table is connected to ground.
Described rover simulator also comprises the second cable switching plate be arranged near second flank plate side in described second cabinet, for after the wire cable layout accessed from described plug, then to second face plate and the switching of second source module.
The second key switch that described second power analog circuit comprises power resistor, LED, the second voltage table and is embedded on second face plate, all power resistors are placed on the second heat radiator side, and the second heat radiator bottom arranges an electric fan; Second voltage table and all LED are embedded on front panel; A power resistor and a LED are cascaded; The front end of each power resistor side is connected with 1 square formation in the sun emulation simulator in the rover that second flank plate accesses by the second cable switching plate, the rear end ground connection of corresponding LED, form 4 power flow thus, whether LED has power to input for showing place path; The rear end of the LED side of every bar power flow is connected with a key terminal of the second key switch input end respectively, and the terminal of the second key switch output terminal is in parallel with one end of the second voltage table, and the other end of the second voltage table is connected to ground.
The Authentication devices of a kind of detector power supply and distribution test system of the present invention has following beneficial effect:
1) Authentication devices provided by the invention, can verify the correctness of the correctness of ground power supply and distribution equipment, reliability and instruction path, effectively avoid working the mischief to satellite;
2) select key switch and voltage table to carry out gating test to tested circuit, save device, save cost thus, and flexible and convenient to use;
3) verifying parts of lander and inspection prober and circuit are integrated in a cabinet respectively, will solidify with ground power supply and distribution equipment interface, Authentication devices is had be convenient to the feature of carrying, not fragile and stability is high.
Accompanying drawing explanation
Fig. 1 is the structural representation of lander simulator of the present invention.
Fig. 2 is the front panel schematic diagram of lander simulator of the present invention.
Fig. 3 is the rear panel schematic diagram of lander simulator of the present invention.
Fig. 4 is the schematic diagram of the power analog circuit of lander simulator of the present invention.
Fig. 5 is the schematic diagram that wired SMU of lander simulator of the present invention adds power-down circuit.
Fig. 6 is the schematic diagram of the satellite and the rocket demultiplexing circuit of lander simulator of the present invention.
Fig. 7 is the schematic diagram of the satellite busbar voltage test circuit of lander simulator of the present invention.
Fig. 8 is the structural representation of rover simulator of the present invention.
Fig. 9 is the rear panel schematic diagram of rover simulator of the present invention.
Figure 10 is the front panel schematic diagram of rover simulator of the present invention.
Embodiment
To develop simultaneously embodiment below in conjunction with accompanying drawing, describe the present invention.
The invention provides a kind of Authentication devices of detector power supply and distribution test system, comprise lander simulator and rover simulator, wherein:
Lander simulator comprises cabinet, front panel, rear panel, cable switching plate, power analog circuit, downstream analog amount circuit, up-on command mimic channel, is separated umbilical connector state simulation circuit, the power module being arranged on cabinet inside, heat radiator and electric fan, and the key switch be embedded on front panel, wherein, front panel and rear panel are embedded on former and later two openings of cabinet respectively, and cable switching plate is arranged on cabinet inside near rear panel; 220V ac plug rear panel being provided with two breakaway plugs, a pull-off plug and being connected with ground power supply and distribution equipment, wherein breakaway plug was used in the ground experiment stage, the attachment plug of satellite and ground power supply and distribution equipment, the cable of one of them breakaway plug for transferring in power analog circuit, all lines of another breakaway plug for transferring in downstream analog amount circuit and up mimic channel; Pull-off plug is used for the connection between Simulated Spacecraft and lander; 220V ac plug is used for powering from ground power supply and distribution equipment to power module; Cable from behind plate plug access after, after the layout again of cable switching plate, by cable again front panel and power module switching;
Described power module, according to the power supply characteristic in lander, converts the 220V alternating current fetched from 220V ac plug to 30V, 28V, 12V ,-12V and 5V direct current;
Power analog circuit comprises power resistor, LED, voltage table, all power resistors are placed on heat radiator side, and electric fan is arranged on heat radiator bottom; Voltage table and all LED are embedded on front panel; A power resistor and a LED are cascaded; The front end of each power resistor side is connected with 1 square formation in the sun emulation simulator on the lander that rear panel accesses by cable switching plate, the rear end ground connection of corresponding LED, form 12 power flow thus, whether LED has power to input for showing place path; The rear end of the LED side of every bar power flow is connected with a key terminal of key switch input end respectively, and the terminal of key switch output terminal is in parallel with one end of voltage table, and the other end of voltage table is connected to ground.
Downstream analog amount circuit is used for testing and display lander battery voltage, satellite busbar voltage, 12V supply voltage ,-12V supply voltage, 5V supply voltage; Downstream analog amount circuit comprises 5 current-limiting resistances, one end of each current-limiting resistance is connected with the 28V power supply in power module, 30V power supply, 12V power supply ,-12V power supply, 5V power supply respectively, the other end is divided into two-way, one tunnel is connected with the test lead of ground power supply and distribution equipment, obtains voltage and current for detecting individual channel power supply; Another road is received on a key terminal of key switch, when place key switch is pressed, voltage table shows voltage.
Up-on command mimic channel for simulating and verify that lander battery discharging switch open command, the instruction power module passed to lander from ground power supply and distribution equipment cuts backup instruction, wired SMU (Inertial Measurement Unit) adds cut-offing instruction circuit and simulation satellite and the rocket separation signal, wherein:
Simulate and verify that wired SMU adds cut-offing instruction circuit and comprises two diodes, two current-limiting resistances, two double-contact relays being embedded in the LED on front panel and being placed on cable switching plate; A current-limiting resistance and a Diode series composition leadage circuit, each leadage circuit in parallel in two ends of two line bags of relay, and diode cathode one terminated line bag positive pole one end; The minus earth of two line bags of relay, two line bag positive pole one end and a K switch controlled by ground power supply and distribution equipment respectively 1 and the K switch 2 of connecting between+28V power supply, the wired SMU power up signal of the closed simulation of K switch 1, the wired SMU power-off signal of the closed simulation of K switch 2; The positive pole of two groups of contacts of relay all connects+5V power supply, and the negative pole of contact is connected in series ground connection after a divider resistance and a LED.
Instruction power module is cut backup instruction circuit, simulation satellite and the rocket demultiplexing circuit and lander battery discharging switch disconnection mimic channel and is included a single contact relay, two diodes, current-limiting resistance and LED, single contact relay is placed on cable switching plate, and LED etc. are arranged on front panel; Line bag one end and the switch controlled by ground power supply and distribution equipment of connecting between 28V power supply of single contact relay, relay line bag other end ground connection; The leadage circuit parallel connection that diode and current-limiting resistance are composed in series wraps two ends online, and the terminal of relay contact one end connects the 5V power supply of power module, and the other end is connected in series ground connection after a divider resistance and a LED; After the described instruction power module switch cut in backup instruction circuit, simulation satellite and the rocket demultiplexing circuit and lander battery discharging switch disconnection mimic channel closes, dummy instruction power module cuts backup instruction, simulation satellite and the rocket separation signal and lander battery discharging switch cut-off signal respectively.
Being separated umbilical connector state simulation circuit is arranged in pull-off plug, shows simulator and be connected with it or the state of disengaging in ground power supply and distribution equipment.
Rover simulator comprises the second cabinet, second face plate, second flank plate, second cable switching plate, second power analog circuit, second downstream analog amount circuit, second up-on command mimic channel, second is separated umbilical connector state simulation circuit, be arranged on the second source module of the second cabinet inside, second heat radiator and an electric fan, and the second key switch be embedded on second face plate, wherein, before second face plate and second flank plate are embedded in the second cabinet respectively, on latter two opening, second cable switching plate is arranged on the second cabinet inside near second flank plate, second flank plate is provided with two power plug, second breakaway plug, a 220V ac plug be connected with ground power supply and distribution equipment, wherein the second breakaway plug was used in the ground experiment stage, the attachment plug of satellite and ground power supply and distribution equipment, all lines of the second breakaway plug for transferring in downstream analog amount circuit and up mimic channel, the cable of two power plug for transferring in the second power analog circuit, cable, after the plug access of second flank plate, after the layout again of the second cable switching plate, is transferred to second face plate and second source module by cable again,
Described second source module, according to the power supply characteristic in rover, converts the 220V alternating current fetched from 220V ac plug to 30V, 28V, 12V ,-12V and 5V direct current;
Second power analog circuit comprises power resistor, LED, the second voltage table, all power resistors are placed on the second heat radiator side, and the second heat radiator bottom arranges an electric fan; Second voltage table and all LED are embedded on front panel; A power resistor and a LED are cascaded; The front end of each power resistor side is connected with 1 square formation in the sun emulation simulator in the rover that second flank plate accesses by the second cable switching plate, the rear end ground connection of corresponding LED, form 4 power flow thus, whether LED has power to input for showing place path; The rear end of the LED side of every bar power flow is connected with a key terminal of the second key switch input end respectively, and the terminal of the second key switch output terminal is in parallel with one end of the second voltage table, and the other end of the second voltage table is connected to ground;
Second downstream analog amount circuit is used for testing and display rover battery voltage, satellite busbar voltage, 12V supply voltage ,-12V supply voltage; Second downstream analog amount circuit comprises 4 current-limiting resistances, one end of each current-limiting resistance is connected with the 28V power supply in second source module, 30V power supply, 12V power supply ,-12V power supply respectively, the other end is divided into two-way, one tunnel is connected with the test lead of ground power supply and distribution equipment, obtains voltage and current for detecting individual channel power supply; Another road is received on a key terminal of the second key switch, when place key switch is pressed, the second voltage table shows voltage;
Second up-on command mimic channel for simulating and verify rover battery discharging switch open command from ground power supply and distribution equipment to rover, rover primary power source bus-tie circuit breaker state, two device charge and discharge switch states, central computer A electromechanical source state and the central computer B electromechanical source state uploaded from, wherein:
Rover battery discharging switch open command circuit, rover primary power source bus-tie circuit breaker state, two device charge and discharge switch states, central computer A electromechanical source state and central computer B electromechanical source state include a single contact relay, two diodes, current-limiting resistance and LED, single contact relay is placed on cable switching plate, and LED etc. are arranged on front panel; Line bag one end and the switch controlled by ground power supply and distribution equipment of connecting between 28V power supply of single contact relay, relay line bag other end ground connection; The leadage circuit parallel connection that diode and current-limiting resistance are composed in series wraps two ends online, and the terminal of relay contact one end connects the 5V power supply of power module, and the other end is connected in series ground connection after a divider resistance and a LED; Simulate rover battery discharging switch open command circuit, rover primary power source bus-tie circuit breaker state, two device charge and discharge switch states, central computer A electromechanical source state and central computer B electromechanical source state respectively after switch in described rover battery discharging switch open command circuit, rover primary power source bus-tie circuit breaker state, two device charge and discharge switch states, central computer A electromechanical source state and central computer B electromechanical source state is closed, and shown by LED;
Mock survey 7 groups of up-on command implementation status circuit comprise two device separation simulation circuit, rover battery discharging switch on and off circuit, rover primary power source bus-tie circuit breaker on-off circuit, two device charge and discharge switch on-off circuits, instruction power+28V on-off circuit, rover central computer A on-off circuit, rover central computer B on-off circuit, above-mentioned 7 circuit include two diodes, two current-limiting resistances, two double-contact relays being embedded in the LED on front panel and being placed on cable switching plate, a current-limiting resistance and a Diode series composition leadage circuit, the each leadage circuit in parallel in two ends of two line bags of relay, and diode cathode one terminated line bag positive pole one end, the minus earth of two line bags of relay, two line bag positive pole one end and a K switch controlled by ground power supply and distribution equipment respectively 1 and the K switch 2 of connecting between+28V power supply, the power up signal of K switch 1 closed simulation place circuit, K switch 2 closed simulation place contactor power-off signal, the positive pole of two groups of contacts of relay all connects+5V power supply, and the negative pole of contact is connected in series ground connection after a divider resistance and a LED,
Being separated umbilical connector state simulation circuit is arranged in pull-off plug, shows simulator and be connected with it or the state of disengaging in ground power supply and distribution equipment.
In sum, these are only preferred embodiment of the present invention, be not intended to limit protection scope of the present invention.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (5)
1. an Authentication devices for detector power supply and distribution test system, is characterized in that, comprises lander simulator and rover simulator, wherein:
Described lander simulator comprises cabinet, front panel, rear panel, power analog circuit, downstream analog amount circuit, up-on command mimic channel, is separated umbilical connector state simulation circuit, the power module being arranged on cabinet inside, heat radiator and electric fan, wherein, front panel and rear panel are embedded on former and later two openings of cabinet respectively, and cable switching plate is arranged on cabinet inside near rear panel; 220V ac plug rear panel being provided with two breakaway plugs, a pull-off plug and being connected with ground power supply and distribution equipment, wherein breakaway plug was used in the ground experiment stage, the attachment plug of satellite and ground power supply and distribution equipment, the cable of one of them breakaway plug for transferring in power analog circuit, all lines of another breakaway plug for transferring in downstream analog amount circuit and up mimic channel; Pull-off plug is used for the connection between Simulated Spacecraft and lander; 220V ac plug is used for powering from ground power supply and distribution equipment to power module; Cable from behind plate plug access after, then front panel and power module switching;
Described power module, according to the power supply characteristic in lander, converts the 220V alternating current fetched from 220V ac plug to 30V, 28V, 12V ,-12V and 5V direct current;
The electric energy that described power analog circuit produces for consuming sun square formation in lander, and show each sun square formation and whether be in normal operating conditions;
Described downstream analog amount circuit is used for testing and display lander battery voltage, satellite busbar voltage, 12V supply voltage ,-12V supply voltage, 5V supply voltage; Downstream analog amount circuit comprises 5 current-limiting resistances, one end of each current-limiting resistance is connected with the 28V power supply in power module, 30V power supply, 12V power supply ,-12V power supply, 5V power supply respectively, the other end is divided into two-way, one tunnel is connected with the test lead of ground power supply and distribution equipment, obtains voltage and current for detecting individual channel power supply; Another road is received on a key terminal of key switch, when place key switch is pressed, voltage table shows voltage;
Up-on command mimic channel for simulate and verify pass to lander from ground power supply and distribution equipment lander battery discharging switch open command, instruction power module cuts backup instruction, wired SMU adds cut-offing instruction circuit and simulation satellite and the rocket separation signal, wherein:
Described wired SMU adds cut-offing instruction circuit and comprises two diodes, two current-limiting resistances, two double-contact relays being embedded in the LED on front panel and being placed on cable switching plate; A current-limiting resistance and a Diode series composition leadage circuit, each leadage circuit in parallel in two ends of two line bags of relay, and diode cathode one terminated line bag positive pole one end; The minus earth of two line bags of relay, two line bag positive pole one end and a K switch controlled by ground power supply and distribution equipment respectively 1 and the K switch 2 of connecting between+28V power supply, the wired SMU power up signal of the closed simulation of K switch 1, the wired SMU power-off signal of the closed simulation of K switch 2; The positive pole of two groups of contacts of relay all connects+5V power supply, and the negative pole of contact is connected in series ground connection after a divider resistance and a LED;
Instruction power module is cut backup instruction circuit, simulation satellite and the rocket demultiplexing circuit and lander battery discharging switch disconnection mimic channel and is included a single contact relay, two diodes, a current-limiting resistance and LED: single contact relay is placed on cable switching plate, and LED is arranged on front panel; Line bag one end and the switch controlled by ground power supply and distribution equipment of connecting between 28V power supply of single contact relay, relay line bag other end ground connection; The leadage circuit parallel connection that diode and current-limiting resistance are composed in series wraps two ends online, and the terminal of relay contact one end connects the 5V power supply of power module, and the other end is connected in series ground connection after a divider resistance and a LED; After the described instruction power module switch cut in backup instruction circuit, simulation satellite and the rocket demultiplexing circuit and lander battery discharging switch disconnection mimic channel closes, dummy instruction power module cuts backup instruction, simulation satellite and the rocket separation signal and lander battery discharging switch cut-off signal respectively;
Being separated umbilical connector state simulation circuit is arranged in pull-off plug, shows lander simulator and be connected with it or the state of disengaging in ground power supply and distribution equipment;
Rover simulator comprises the second cabinet, second face plate, second flank plate, the second power analog circuit, the second downstream analog amount circuit, the second up-on command mimic channel, the second source module being arranged on the second cabinet inside, the second heat radiator and an electric fan, wherein, second face plate and second flank plate are embedded on former and later two openings of the second cabinet respectively, and the second cable switching plate is arranged on the second cabinet inside near second flank plate; Second flank plate is provided with the second breakaway plug, a signal imitation plug, two power plug and a 220V ac plug be connected with ground power supply and distribution equipment, wherein the second breakaway plug was used in the ground experiment stage, the attachment plug of satellite and ground power supply and distribution equipment, all lines simultaneously also for transferring in up mimic channel, signal imitation plug is for downstream analog amount circuit of transferring; The cable of two power plug for transferring in the second power analog circuit, cable after the plug access of second flank plate, then is transferred to second face plate and second source module;
Described second source module, according to the power supply characteristic in rover, converts the 220V alternating current fetched from 220V ac plug to 30V, 28V, 12V ,-12V and 5V direct current;
The electric energy that described second power analog circuit produces for consuming sun square formation in rover, and show each sun square formation and whether be in normal operating conditions;
Second downstream analog amount circuit is used for testing and display rover battery voltage, satellite busbar voltage, 12V supply voltage ,-12V supply voltage; Second downstream analog amount circuit comprises 4 current-limiting resistances, one end of each current-limiting resistance is connected with the 28V power supply in second source module, 30V power supply, 12V power supply ,-12V power supply respectively, the other end is divided into two-way, one tunnel is connected with the test lead of ground power supply and distribution equipment, for detecting the voltage and current of individual channel power supply; Another road is received on a key terminal of the second key switch, when place key switch is pressed, the second voltage table shows voltage;
Second up-on command mimic channel for simulating and verify rover battery discharging switch open command from ground power supply and distribution equipment to rover, rover primary power source bus-tie circuit breaker state, two device charge and discharge switch states, central computer A electromechanical source state and the central computer B electromechanical source state uploaded from, wherein:
Rover battery discharging switch open command circuit, rover primary power source bus-tie circuit breaker state, two device charge and discharge switch states, central computer A electromechanical source state and central computer B electromechanical source state include a single contact relay, two diodes, current-limiting resistance and LED, single contact relay is placed on cable switching plate, and LED is arranged on front panel; Line bag one end and the switch controlled by ground power supply and distribution equipment of connecting between 28V power supply of single contact relay, relay line bag other end ground connection; The leadage circuit parallel connection that diode and current-limiting resistance are composed in series wraps two ends online, and the terminal of relay contact one end connects the 5V power supply of power module, and the other end is connected in series ground connection after a divider resistance and a LED; Simulate rover battery discharging switch open command circuit, rover primary power source bus-tie circuit breaker state, two device charge and discharge switch states, central computer A electromechanical source state and central computer B electromechanical source state respectively after switch in described rover battery discharging switch open command circuit, rover primary power source bus-tie circuit breaker state, two device charge and discharge switch states, central computer A electromechanical source state and central computer B electromechanical source state is closed, and shown by LED;
Mock survey 7 groups of up-on command implementation status circuit comprise two device separation simulation circuit, rover battery discharging switch on and off circuit, rover primary power source bus-tie circuit breaker on-off circuit, two device charge and discharge switch on-off circuits, instruction power+28V on-off circuit, rover central computer A on-off circuit, rover central computer B on-off circuit, two device separation simulation circuit, rover battery discharging switch on and off circuit, rover primary power source bus-tie circuit breaker on-off circuit, two device charge and discharge switch on-off circuits, instruction power+28V on-off circuit, rover central computer A on-off circuit and rover central computer B on-off circuit include two diodes, two current-limiting resistances, two double-contact relays being embedded in the LED on front panel and being placed on cable switching plate, a current-limiting resistance and a Diode series composition leadage circuit, the each leadage circuit in parallel in two ends of two line bags of relay, and diode cathode one terminated line bag positive pole one end, the minus earth of two line bags of relay, two line bag positive pole one end and a K switch controlled by ground power supply and distribution equipment respectively 1 and the K switch 2 of connecting between+28V power supply, the power up signal of K switch 1 closed simulation place circuit, K switch 2 closed simulation place contactor power-off signal, the positive pole of two groups of contacts of relay all connects+5V power supply, and the negative pole of contact is connected in series ground connection after a divider resistance and a LED.
2. the Authentication devices of a kind of detector power supply and distribution test system as claimed in claim 1, it is characterized in that, described lander simulator also comprises the cable switching plate be arranged near rear panel side in described cabinet, for to after the wire cable layout accessed from described plug, then front panel and power module switching.
3. the Authentication devices of a kind of detector power supply and distribution test system as claimed in claim 1, it is characterized in that, power analog circuit in described lander simulator comprises 12 power resistors, 12 LED, a voltage table and electric fans, and the key switch be embedded on front panel, wherein 12 power resistors are placed on above heat radiator, and electric fan is arranged on heat radiator bottom; Voltage table and all LED are embedded on front panel; A power resistor and a LED are cascaded; The front end of each power resistor side is connected with 1 square formation in the sun emulation simulator on the lander that rear panel accesses by cable switching plate, the rear end ground connection of corresponding LED, form 12 power flow thus, whether LED has power to input for showing place path; The rear end of the LED side of every bar power flow is connected with a key terminal of key switch input end respectively, and the terminal of key switch output terminal is in parallel with one end of voltage table, and the other end of voltage table is connected to ground.
4. the Authentication devices of a kind of detector power supply and distribution test system as claimed in claim 1, it is characterized in that, described rover simulator also comprises the second cable switching plate be arranged near second flank plate side in described second cabinet, for to after the wire cable layout accessed from described plug, then to second face plate and the switching of second source module.
5. the Authentication devices of a kind of detector power supply and distribution test system as claimed in claim 1, it is characterized in that, the second key switch that described second power analog circuit comprises power resistor, LED, the second voltage table and is embedded on second face plate, all power resistors are placed on the second heat radiator side, and the second heat radiator bottom arranges an electric fan; Second voltage table and all LED are embedded on front panel; A power resistor and a LED are cascaded; The front end of each power resistor side is connected with 1 square formation in the sun emulation simulator in the rover that second flank plate accesses by the second cable switching plate, the rear end ground connection of corresponding LED, form 4 power flow thus, whether LED has power to input for showing place path; The rear end of the LED side of every bar power flow is connected with a key terminal of the second key switch input end respectively, and the terminal of the second key switch output terminal is in parallel with one end of the second voltage table, and the other end of the second voltage table is connected to ground.
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| CN104280710B (en) * | 2014-09-26 | 2017-05-10 | 航天东方红卫星有限公司 | General portable satellite power supply and distribution system equivalent device |
| CN104503421A (en) * | 2014-10-30 | 2015-04-08 | 航天东方红卫星有限公司 | Test system used for satellite power supply and distribution system |
| CN104477414B (en) * | 2014-10-31 | 2017-02-15 | 北京兴华机械厂 | Single-needle separable power supply device |
| CN106441392A (en) * | 2016-10-18 | 2017-02-22 | 周末 | Satellite detector |
| CN106526381A (en) * | 2016-11-23 | 2017-03-22 | 上海卫星工程研究所 | Satellite power supply and distribution response characteristic simulation device |
| CN107843770B (en) * | 2017-10-08 | 2019-11-26 | 国网江西省电力有限公司电力科学研究院 | A kind of distribution line position of the switch setting method based on impedance variations rule |
| CN109742843B (en) * | 2018-12-27 | 2021-02-09 | 中国空间技术研究院 | Power supply and distribution reconfigurable control system and method for batched flight verification |
| CN109857138B (en) * | 2019-01-28 | 2021-10-01 | 北京卫星环境工程研究所 | Rapid installation and adjustment method based on spacecraft non-reference structure multi-coupling dimension chain mechanism |
| 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 |
| CN112462273B (en) * | 2020-10-23 | 2023-03-28 | 北京空间飞行器总体设计部 | Flight event driven upper-level satellite assembly power supply capability verification system and method |
| CN117092959B (en) * | 2023-10-18 | 2024-01-30 | 北京星河动力装备科技有限公司 | Carrier rocket time sequence path monitoring circuit and method and carrier rocket |
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| CN201464628U (en) * | 2009-07-23 | 2010-05-12 | 航天东方红卫星有限公司 | Ground power supply and distribution test system supporting constellation test |
| CN101620261B (en) * | 2009-07-23 | 2011-09-21 | 航天东方红卫星有限公司 | Equivalent device for general satellite power-distribution system |
| CN101877555B (en) * | 2009-11-13 | 2012-03-21 | 航天东方红卫星有限公司 | Method for constructing solar cell array simulation system used for multi-satellite parallel test |
| CN202230154U (en) * | 2011-09-15 | 2012-05-23 | 航天东方红卫星有限公司 | Miniature satellite ground power supply and distribution test device based on USB bus |
| CN102539185B (en) * | 2011-12-27 | 2014-07-16 | 北京卫星环境工程研究所 | Selenographic gravity simulation system for ground traveling tests of exploration rover |
| CN102981426B (en) * | 2012-12-10 | 2015-04-15 | 上海空间电源研究所 | Sleep control system and control method for detector in deep-space detection field |
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