CN117368619A - Spacecraft electrical system function detection device - Google Patents
Spacecraft electrical system function detection device Download PDFInfo
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- CN117368619A CN117368619A CN202311604200.3A CN202311604200A CN117368619A CN 117368619 A CN117368619 A CN 117368619A CN 202311604200 A CN202311604200 A CN 202311604200A CN 117368619 A CN117368619 A CN 117368619A
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- 238000001514 detection method Methods 0.000 title claims abstract description 49
- 238000005259 measurement Methods 0.000 claims abstract description 24
- 238000009413 insulation Methods 0.000 claims abstract description 7
- 230000003993 interaction Effects 0.000 claims abstract description 4
- 238000012360 testing method Methods 0.000 claims description 22
- 238000013461 design Methods 0.000 claims description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 239000003086 colorant Substances 0.000 claims description 2
- 238000011056 performance test Methods 0.000 claims 1
- 229910000679 solder Inorganic materials 0.000 claims 1
- 230000005284 excitation Effects 0.000 description 15
- 238000010586 diagram Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000005476 soldering Methods 0.000 description 2
- 238000003860 storage Methods 0.000 description 2
- 238000012356 Product development Methods 0.000 description 1
- 238000010923 batch production Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000004069 differentiation Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R15/00—Details of measuring arrangements of the types provided for in groups G01R17/00 - G01R29/00, G01R33/00 - G01R33/26 or G01R35/00
- G01R15/12—Circuits for multi-testers, i.e. multimeters, e.g. for measuring voltage, current, or impedance at will
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measurement Of Resistance Or Impedance (AREA)
Abstract
The invention discloses a spacecraft electrical system function detection device, which comprises a power supply module, a control module, a measurement module, a universal switching module, an operation panel and a box body, wherein the power supply module is connected with the control module; the power module, the control module and the measurement module are fixed in the box body, are connected through the operation panel, and lead out a man-machine interaction port on the operation panel; the opening of the box body is provided with the operation panel. The invention can output two different voltages of 6 paths simultaneously, can output current of 6 paths of 0-10A, realizes measurement of 15 paths of voltage and resistance, 30 paths of conduction and insulation, realizes universal detection of equipment of various types and improves detection efficiency.
Description
Technical Field
The invention relates to the technical field of test equipment, in particular to a spacecraft electrical system function detection device.
Background
The spacecraft electrical system mainly comprises a cable network, an electrical control box, power equipment and the like, and has the main functions of: the ground power supply and the power supply on the spacecraft are correctly converted in the launching process of the spacecraft; power supply and distribution of equipment on the bullet and internal signal transmission of each subsystem in the flight process of the spacecraft; a test interface is provided for ground testing. In the process of product development and batch production, the performance of an electrical system is detected, the working accuracy of the electrical system is ensured, and the performance detection of the electrical system comprises detection items such as conductivity, insulativity, line resistance, control function and the like. The control function detection is simply called function detection, and needs to apply voltage, current and other excitation to the product, and meanwhile, check the correctness of the operation of a certain element and a certain part on the product under the excitation condition.
The existing wire harness tester can only provide single voltage excitation, has no functions of multi-module voltage output, no current output, no voltage detection and the like, and can not completely meet the detection requirements of the functions of an electrical system. If the cost of purchasing new equipment is too high, the economic benefit is not great, the detection efficiency is low, and the phenomenon of error detection is easy to occur; at least 2 persons are needed to complete the matching, and the labor cost is high; when in power-up and detection, a special cable and a digital multimeter are used for carrying out power-up and test on a product needle and a hole, and the electrical interface of the product is easy to damage, so that the quality problem is caused; the excitation and detection requirements of each model are different, and the detection platform cannot realize universality.
The utility model discloses a chinese patent with publication number CN219350385U, a fault function detector for an ejector seat electrical system is disclosed, which comprises supporting legs and a detector body, the four corners of the lower end surface of the detector body are provided with supporting legs through screw fixation, a touch screen is embedded above the front end surface of the detector body, the right side of the touch screen is provided with a network interface and serial port communication through screw embedding fixation in sequence from top to bottom, a charging port is arranged below the touch screen, a storage battery is arranged in the middle of the bottom in the detector body through screw fixation, a driving main board is arranged above the storage battery and is fixed in the detector body through screw fixation, the upper end surface of the driving main board is provided with a man-machine interface module, a data generating module, a processor and a control measuring module through screw fixation in sequence from left to right, and the man-machine interface module comprises an initialization and result display module, a manual test module, an automatic test module, a module maintenance module and a connection management module; the invention has the advantages of manual detection and automatic detection, high detection efficiency and convenient fault observation. However, the device does not have a universal switching tool, can only detect the ejection seat, and cannot detect other devices on the spacecraft.
Disclosure of Invention
In order to solve the technical problems, the invention provides a spacecraft electrical system function detection device, which adopts the following technical scheme:
the invention provides a spacecraft electrical system function detection device, which is characterized by comprising:
a spacecraft electrical system function detection device, comprising: the device comprises a power module, a control module, a measurement module, a universal switching module, an operation panel and a box body;
the power module, the control module and the measurement module are fixed in the box body, are connected through the operation panel, and lead out a man-machine interaction port on the operation panel;
the opening of the box body is provided with the operation panel.
Preferably, the power supply module comprises a voltage source and a current source;
the voltage source is AC220V to DC 0-60V, and the output voltage is adjustable within the range of 0-60V;
the current source is an AC220V to 0-48V/0-10A independent module power supply.
Preferably, the current source is provided with a Hall current sensor and a display, and the output current is calibrated through a current adjusting tool of the current source.
Preferably, the operation panel is made of an aluminum plate.
Preferably, the operation panel comprises a power supply port, a panel interface, a control switch, an LED digital display meter and a measurement port; the box body is selected according to the design size of the operation panel.
Preferably, the power supply port comprises a power socket and a power switch;
the power socket is connected with an AC220V power supply;
the power switch is a red button attached with an indicator lamp and is fixed through bolts.
Preferably, the panel interface outputs the voltage and the current to the outside, and the point to be detected in the measured object is accessed into the measuring port;
the control switch comprises a toggle switch and a button switch, the toggle switch is firstly connected and then the button switch is connected, and the panel interface can be used for outputting outwards.
Preferably, the measuring port adopts a tail nut type socket and is connected through a soldering lug;
the LED digital display meter comprises an LED double-way digital display voltmeter and an LED direct current double-display meter.
Preferably, the universal switching module comprises an electrical system electrical performance testing tool and a universal switching tool;
the electrical performance testing tool of the electrical system is a conductive insulation testing cable of the electrical system, and the port of the connecting harness tester is a Y2-65ZJLM plug;
the universal switching tool comprises a measuring tool and a switching tool, wherein the switching tool selects a bullet male-female butt-joint terminal, and the measuring tool distinguishes signal types by using terminal colors and marks with numbers.
Preferably, the color distinguishing signal type is specifically red for power supply, blue for current, and black for measurement route.
The invention has the following beneficial effects:
1. two different voltages of 6 paths can be simultaneously output, 6 paths of 0-10A current output can be output, 15 paths of voltage and resistance measurement are realized, 30 paths of conduction and insulation measurement are realized, the universal detection of equipment of various types is realized, and the detection efficiency is improved;
2. the alternating current mains supply is adopted for power supply, the structure is simple, the operation is simple and convenient, and the interface display is clear;
3. the integrated design, integrated module power, detection device are as an organic whole, need not external excitation power and check out test set, and detection efficiency is high when possessing the convenience.
Drawings
FIG. 1 is a schematic diagram of a detection system connection according to an embodiment of the present invention;
FIG. 2 is a schematic overall structure of an embodiment of the present invention;
FIG. 3 is a schematic view of an operation panel according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of a box structure according to an embodiment of the present invention;
FIG. 5 is a design of an operator panel according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of a general switching tool according to an embodiment of the present invention;
fig. 7 is a schematic structural diagram of a general adapter tool according to an embodiment of the present invention after connection;
fig. 8 is a schematic diagram of an unconnected structure of a universal switching tool according to an embodiment of the present invention;
fig. 9 is a schematic diagram of a complete structure of a universal adapter tool according to an embodiment of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1, 2, 4, 5, and 9, a spacecraft electrical system function detection device includes: the device comprises a power supply module 1, a control module 2, a measurement module 3, a universal switching module 4, an operation panel 5 and a box 6;
the power module 1, the control module 2 and the measurement module 3 are fixed in the box 6, are connected through the operation panel 5, and lead out a man-machine interaction port on the operation panel 5;
one side of the control module 2 is provided with a power module 1, and the other side is provided with a measuring module 3;
the opening of the box body 6 is provided with the operation panel 5.
The power module 1 is used for excitation required by the detection of the functions of an electrical system;
the power module 1 comprises a voltage source and a current source;
the power module 1 provides voltage excitation and current excitation required by the detection of the functions of the electrical system;
the voltage source is AC220V to DC 0-60V, and the output voltage is adjustable within the range of 0-60V;
the current source is an AC220V to 0-48V/0-10A independent module power supply.
The current source carries out calibration on the output current through a current adjusting tool of the current source with a Hall current sensor and display, and the stability of the power supply is ensured.
The control module 2 is used for realizing the branching of the power supply module 1 and the output control of each path of excitation;
the measuring module 3 is used for finishing the detection of the resistance, voltage, conduction and insulation performance of the measured object;
the measuring module 3 is used for finishing the detection of the resistance, voltage, conduction and insulation performance of the measured object and displaying the actually measured voltage and current data through numbers;
the universal switching module 4 is used for connecting excitation output to the power supply port 7 of the electrical system, connecting detection points to a test interface and realizing function detection;
as shown in fig. 6-9, the universal switching module 4 includes an electrical performance testing tool and a universal switching tool for an electrical system;
the electrical performance testing tool of the electrical system is a conductive insulation testing cable of the electrical system, and the port of the connecting harness tester is a Y2-65ZJLM plug;
the universal switching frock is including measuring frock and switching frock, the public female butt joint terminal of bullet is selected to switching frock, and the plug is durable, and it is convenient to change, it marks just to make the number to measure the terminal colour differentiation signal type for the frock, convenient quick search.
The color distinguishing signal type is specifically red for representing a power supply, blue for representing a current, and black for representing a measuring route.
The power supply, voltage and other excitation outputs are connected to the power supply port 7 of the electrical system through the switching module, and detection points are connected to the test interface to realize function detection, and the universal switching module 4 is a difficulty in designing the detection device, so that the universal checking among various models is required to be completed through the universal switching module 4.
The stimulus includes a voltage and a current.
An operation panel 5 shown in fig. 3 and 5: the device is used for connecting each module, controlling input and output, and displaying measured voltage and current data through numbers;
the operation panel 5 is made of an aluminum plate.
The operation panel 5 comprises a power supply port 7, a panel interface 12, a control switch, an LED digital display meter 11 and a measurement port 10;
the control switch comprises a toggle switch 8 and a button switch 9, the control switch is used for controlling the panel interface 12 to output outwards, the toggle switch 8 is firstly switched on and then the button switch 9 is switched on, and the panel interface 12 can output outwards;
the power supply port 7 is used for supplying power to the power supply module 1, and the power supply port 7 comprises a power socket and a power switch;
the power socket adopts a national standard three-core power socket and is connected with an AC220V power supply;
the power switch is a red button attached indicator lamp, is fixed through bolts, is connected safely, does not shake, and guarantees safety.
The panel interface 12 is used for outputting voltage and current outwards, and connecting points to be detected in the measured object into the measurement port 10;
the panel interface 12 is arranged at the upper left corner of the operation panel 5, the toggle switch 8 is arranged at one side of the panel interface 12, the LED digital display meter 11 is arranged at the other side of the toggle switch 8, the button switch 9 is arranged below the panel interface 12, the measurement port 10 is arranged below the LED digital display meter, and the power supply port 7 is arranged below the button switch 9.
The measuring port 10 adopts a tail nut type socket which is connected through a soldering lug, and wiring is not easy to fall off;
in this embodiment, the adjustable voltage and current excitation are respectively 6 paths of output controls S1 to S6, and a redundant design has been adopted, and the X1 connector is an external interface of the operation panel 5, through which 12 paths of voltages and 6 paths of currents are externally output, and points to be detected in the measured object are introduced into the measurement ports 10J1 to J30 on the panel.
The LED digital display meter 11 comprises an LED double-circuit digital display voltmeter and an LED direct current double-circuit display meter, the LED digital display meter 11 is used for displaying power supply voltage, current and measurement voltage, the measurement range is 0-100V, the digital display digit is 3, and the decimal point is automatically shifted.
The digital display meters all adopt a wide power supply range, and the power supply is reversely connected without burning.
The case 6 as shown in fig. 4: for placing and securing the modules;
the box 6 is selected according to the design size of the operation panel 5, a power supply is arranged at the bottom of the box 6, and the operation panel 5 is arranged at the opening of the box 6.
The invention relates to a spacecraft electrical system function detection device, which is integrated equipment integrating a power module 1, a control module 2, a measurement module 3 and a universal switching module 4, and has the following functions: the excitation of voltage, current and the like can be provided for the spacecraft electrical system; the corresponding response signal test of the spacecraft electrical system, such as voltage, resistance, conductivity and the like, is realized; the detection requirements of the electric systems of the spacecraft of various types are different (different in excitation voltage, excitation current, electric interfaces, detection lines, detection requirements and the like), so that the function detection of the electric systems of the spacecraft of various types is met; the operation is simple and the portable.
The foregoing is merely illustrative of the present invention, and the present invention is not limited thereto, and any person skilled in the art will readily recognize that variations or substitutions are within the scope of the present invention. Therefore, the protection scope of the invention is subject to the protection scope of the claims.
Claims (10)
1. A spacecraft electrical system function detection device, comprising: the device comprises a power module (1), a control module (2), a measurement module (3), a universal switching module (4), an operation panel (5) and a box body (6);
the power module (1), the control module (2) and the measurement module (3) are fixed in the box body (6), are connected through the operation panel (5), and lead out a man-machine interaction port on the operation panel (5);
the opening of the box body (6) is provided with the operation panel (5).
2. A spacecraft electrical system function detection device as claimed in claim 1, wherein said power module (1) comprises a voltage source and a current source;
the voltage source is AC220V to DC 0-60V, and the output voltage is adjustable within the range of 0-60V;
the current source is an AC220V to 0-48V/0-10A independent module power supply.
3. A spacecraft electrical system function test device as claimed in claim 2, wherein said current source is provided with a hall current sensor and display, and wherein said output current is calibrated by means of a current regulation fixture thereof.
4. A spacecraft electrical system function test device as claimed in claim 1, wherein said operator panel is fabricated from aluminum.
5. The spacecraft electrical system function detection device of claim 1, wherein said operation panel (5) comprises a power supply port (7), a panel interface (12), a control switch, an LED digital display meter (11) and a measurement port (10); the box body (6) is selected according to the design size of the operation panel (5).
6. A spacecraft electrical system function detection device as claimed in claim 5, wherein said power supply port (7) comprises a power outlet and a power switch;
the power socket is connected with an AC220V power supply;
the power switch is a red button attached with an indicator lamp and is fixed through bolts.
7. The spacecraft electrical system function detection device of claim 5, wherein said panel interface (12) outputs voltage and current to the outside and connects points to be detected in the object to be detected into the measurement port (10);
the control switch comprises a toggle switch (8) and a button switch (9), the toggle switch (8) is firstly connected and then the button switch (9) is connected, and the panel interface (12) can output outwards.
8. A spacecraft electrical system function test device as claimed in claim 5, wherein said measurement port (10) is a tail nut socket connected by a solder tab;
the LED digital display meter (11) comprises an LED double-way digital display voltmeter and an LED direct current double-display meter.
9. A spacecraft electrical system function test device as claimed in claim 1, wherein said universal adapter module (4) comprises an electrical system electrical performance test fixture and a universal adapter fixture;
the electrical performance testing tool of the electrical system is a conductive insulation testing cable of the electrical system, and the port of the connecting harness tester is a Y2-65ZJLM plug;
the universal switching tool comprises a measuring tool and a switching tool, wherein the switching tool selects a bullet male-female butt-joint terminal, and the measuring tool distinguishes signal types by using terminal colors and marks with numbers.
10. A spacecraft electrical system function detection device as claimed in claim 9, wherein the colour discrimination signal type is specifically red for power, blue for current and black for measurement path.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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CN202311604200.3A CN117368619A (en) | 2023-11-28 | 2023-11-28 | Spacecraft electrical system function detection device |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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CN202311604200.3A CN117368619A (en) | 2023-11-28 | 2023-11-28 | Spacecraft electrical system function detection device |
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CN117368619A true CN117368619A (en) | 2024-01-09 |
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CN202311604200.3A Pending CN117368619A (en) | 2023-11-28 | 2023-11-28 | Spacecraft electrical system function detection device |
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CN (1) | CN117368619A (en) |
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2023
- 2023-11-28 CN CN202311604200.3A patent/CN117368619A/en active Pending
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