CN111409852B - Direct-current stabilized power supply device for airplane structural strength test - Google Patents
Direct-current stabilized power supply device for airplane structural strength test Download PDFInfo
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- CN111409852B CN111409852B CN202010282720.7A CN202010282720A CN111409852B CN 111409852 B CN111409852 B CN 111409852B CN 202010282720 A CN202010282720 A CN 202010282720A CN 111409852 B CN111409852 B CN 111409852B
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- Prior art keywords
- power supply
- relay
- structural strength
- stabilized power
- current stabilized
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01H—ELECTRIC SWITCHES; RELAYS; SELECTORS; EMERGENCY PROTECTIVE DEVICES
- H01H47/00—Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current
- H01H47/001—Functional circuits, e.g. logic, sequencing, interlocking circuits
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M7/00—Conversion of ac power input into dc power output; Conversion of dc power input into ac power output
- H02M7/02—Conversion of ac power input into dc power output without possibility of reversal
Abstract
The application provides a direct current stabilized power supply device for aircraft structural strength test, include: the plurality of 24V direct current stabilized power supplies are arranged in parallel and are used for converting 220V alternating current into 24V direct current; the voltage output control circuit comprises a first relay, a second relay and a potential distribution terminal, wherein the first relay is connected with a service manifold of the aircraft structural strength test control system and a first electromagnetic valve conversion panel and is used for outputting control signals of the first electromagnetic valve conversion panel, and the second relay is connected with a 24V direct current stabilized voltage supply and the potential distribution terminal and is used for outputting distributed 24V control signals; the first electromagnetic conversion panel and the second electromagnetic valve switching panel are respectively connected with electromagnetic valves with different powers used in the aircraft structural strength test. Compared with the prior art, the direct-current stabilized power supply device has the advantages that the circuit structure is compact and regular, the cable laying consumable amount is reduced, and the output efficiency is high.
Description
Technical Field
The application belongs to the technical field of electric power, and particularly relates to a direct-current stabilized power supply device for an aircraft structural strength test.
Background
At present, in the fatigue test of the structural strength of an airplane, a 24V power supply vehicle is mainly used as power supply equipment of an oil way control electromagnetic valve. The 24V power supply vehicle mainly comprises three parts of a special direct-current stabilized power supply, a 24V voltage output control circuit, an electromagnetic valve socket switching panel and the like, and the working principle of the 24V power supply vehicle is as follows: the special direct current stabilized power supply is used as power supply equipment, the output control circuit controls the high oil pressure and the low oil pressure of the oil way electromagnetic valve according to the output signal of the control system, and the special direct current stabilized power supply is connected to each electromagnetic valve through the switching panel.
The current test is that the 24V power supply vehicle has the problems of high cost, large size, poor heat dissipation and lower utilization rate of a special direct current stabilized power supply, and particularly has poor long-term use stability in a fatigue test.
Disclosure of Invention
The purpose of the application is to provide a direct current stabilized power supply device for an aircraft structural strength test, so as to solve any one of the problems.
The technical scheme that this application provided is: a dc regulated power supply apparatus for structural strength testing of an aircraft, comprising:
the plurality of 24V direct current stabilized power supplies are arranged in parallel and are used for converting 220V alternating current into 24V direct current;
the voltage output control circuit comprises a first relay, a second relay and a potential distribution terminal, wherein the first relay is connected with a service manifold of the aircraft structural strength test control system and a first electromagnetic valve conversion panel and is used for outputting control signals of the first electromagnetic valve conversion panel, and the second relay is connected with the 24V direct-current regulated power supply and the potential distribution terminal and is used for outputting distributed 24V control signals;
the first electromagnetic conversion panel and the second electromagnetic valve switching panel are respectively connected with electromagnetic valves with different types of rates used in the aircraft structural strength test.
In an embodiment of the present application, the number of 24V dc regulated voltages and the number of second relays are the same.
In an embodiment of the present application, the solenoid valve load connected to the first electromagnetic conversion panel is smaller than the solenoid valve load connected to the second electromagnetic conversion panel.
In one embodiment of the present application, the second relay is a mechanical relay.
In one embodiment of the present application, the first relay is a solid state relay.
In an embodiment of the present application, the power supply further includes a rack-mounted power supply bracket, where the rack-mounted power supply bracket is used to fix the 24V dc regulated power supply and the voltage output control circuit.
Compared with the power supply vehicle in the prior art, the direct-current stabilized power supply device has the advantages that the circuit structure is more compact and regular, the cable laying consumable amount is reduced, the standardized installation is more convenient to maintain, the power supply short circuit and the voltage output state can be protected, the utilization rate and the load capacity of the special power supply are improved through the electromagnetic valve adapter plate according to test requirement distribution, and the output efficiency is high.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
Fig. 1 is a schematic diagram of the composition structure of the dc voltage-stabilized power supply of the present application.
Fig. 2 is a schematic diagram of the wiring of the dc regulated power supply line of the present application.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
In order to solve the problems of large size, low efficiency and the like of a 24V power supply vehicle in the prior art, the application provides a direct current stabilized voltage supply device for an aircraft structural strength test.
As shown in fig. 1, the dc regulated power supply device of the present application includes:
the plurality of 24V direct current stabilized power supplies are arranged in parallel, and the direct current stabilized power supplies are connected with the mains supply and are used for converting alternating current of 220V mains supply into 24V direct current;
the voltage output control circuit comprises a first relay, a second relay and a potential distribution terminal, wherein the first relay is connected with a service manifold of the aircraft structural strength test control system and a first electromagnetic valve conversion panel, an excitation signal of the first relay is output and controlled by the service manifold of the test control system and is used for outputting a control signal of the first electromagnetic valve conversion panel, the second relay is connected with a 24V direct current stabilized power supply and the potential distribution terminal, and a signal output by the 24V direct current stabilized power supply is connected with the potential distribution terminal after being connected with the second relay and can be used for outputting a distributed 24V control signal;
the first electromagnetic conversion panel and the second electromagnetic valve switching panel are respectively connected with electromagnetic valves of different types used in the aircraft structural strength test.
The distributed 24V signals can be connected from the potential distribution terminals to all solenoid valve switching panels of the test site by using long wires, the number and the scale of the switching panels are determined by the layout of the solenoid valves for fatigue test, all solenoid valve switching plates are connected into solenoid valve sockets after overcurrent protection is performed by using fuse terminals, and finally all solenoid valves are connected through solenoid valve cables.
In one embodiment of the present application, the number of 24V dc regulated voltages and the number of second relays are the same.
In one embodiment of the present application, the solenoid valve load connected to the first solenoid switch panel is less than the solenoid valve load connected to the second solenoid switch panel.
In one embodiment of the present application, the second relay is a mechanical relay.
In one embodiment of the present application, the first relay is a solid state relay.
In an embodiment of the present application, the power supply further includes a rack-mounted power supply bracket, where the rack-mounted power supply bracket is used for fixing the first relay, the second relay, the potential distribution terminal, etc. of the 24V dc stabilized power supply and the voltage output control circuit.
Compared with the power supply vehicle in the prior art, the direct-current stabilized power supply device has the following advantages:
1. the 24V direct current stabilized power supply, the solid-state relay, the potential distribution terminal and other hardware can be fixedly arranged in the integrated machine room through the rack-mounted power supply bracket, and the integral size is reduced to 1/4 due to the innovative use of the direct current stabilized power supply device, so that the integration level is improved;
2. the 24V direct current stabilized power supply has the advantages that the self heat dissipation is faster, the power supply is used in a constant temperature environment of an integrated machine room for testing, the working state of the power supply is more stable, and the test proves that the power supply can run for more than 30 days and completely meets the requirements of fatigue tests;
3. the solid-state relay, the potential distribution terminal and the fuse terminal are adopted in electrical connection, so that the circuit structure of the direct-current stabilized power supply special for fatigue test is more compact and regular, the cable laying consumable amount is reduced, and standardized installation is more convenient to maintain;
4. the solenoid valve switching panel uses the fuse terminal both can protect the power short circuit, can indicate the voltage output state again, and the solenoid valve switching board distributes according to the test demand and improves the utilization ratio and the load capacity of special power, and every 24V direct current steady voltage power all can independently load 40 solenoid valves, and output reaches 80%.
Fig. 2 is a schematic diagram of a connection of a dc voltage-stabilized power supply device according to an embodiment:
firstly, planning the overall design scheme of a direct current stabilized power supply device for an aircraft structural strength test according to test requirements, and determining the positions and the number of a 24V direct current stabilized power supply, first and second relays, potential distribution terminals and the like and the layout planning of all parts;
then, each part of products or structures are installed and fixed on a U-shaped parallel guide rail of a rack-type power supply bracket, the power supply bracket is arranged in an integrated machine room, a 220V power supply PDU socket is reserved for a 24V direct current stabilized power supply in the integrated machine room, the solid state relay is coated with insulating heat conduction silicone grease and an installation radiating fin in advance, and electric elements such as a potential distribution terminal, an air switch and the like are sequentially arranged according to the power supply output flow direction;
then, the second relay 120A in the 24V voltage output line adopts 6mm of both red and black colors 2 High-quality copper wire, 2.5mm of solid state relay adopting three colors of red, green and yellow 2 High-quality copper wires, and service manifold cables of all relays are 0.5mm in red and black colors 2 The high-quality copper wires are characterized in that the cables at the connecting terminals are inserted into the connecting terminals by adopting insulating cold-pressing terminals, and the cables at the connecting positions pressed by the bolts are welded with copper terminals, so that firm connection and reliable contact of all the cables are ensured;
finally, according to the number of the test solenoid valve switching panels, fuse terminals are arranged, and 6mm of red and black colors are laid in the wire slots from the potential distribution terminals to the solenoid valve switching panels 2 High-quality copper wires.
After the implementation mode is finished, the special direct current stabilized power supply for the structural fatigue test is debugged, the normal work of the direct current stabilized power supply is ensured, and in addition, the contacts of the relay are periodically checked and timely replaced when the contacts are oxidized.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (3)
1. A dc regulated power supply apparatus for structural strength testing of an aircraft, comprising:
the plurality of 24V direct current stabilized power supplies are arranged in parallel and are used for converting 220V alternating current into 24V direct current;
the voltage output control circuit comprises a first relay adopting a solid-state relay, a second relay adopting a mechanical relay and a potential distribution terminal, wherein the first relay is coated with insulating heat-conducting silicone grease and is provided with a radiating fin, the first relay is connected with a service manifold and a first electromagnetic valve conversion panel of an aircraft structural strength test control system and is used for outputting control signals of the first electromagnetic valve conversion panel, and the second relay is connected with the 24V direct-current stabilized power supply and the potential distribution terminal and is used for outputting distributed 24V control signals;
the first electromagnetic conversion panel and the second electromagnetic valve switching panel are respectively connected with electromagnetic valves of different types used in the aircraft structural strength test; and
the rack-mounted power supply support is used for fixing the 24V direct-current stabilized power supply and the voltage output control circuit, wherein the 24V direct-current stabilized power supply and the voltage output control circuit are fixed on the rack-mounted power supply support through guide rails.
2. The dc regulated power supply apparatus for use in aircraft structural strength testing of claim 1, wherein the number of 24V dc regulated power supplies and the number of second relays are the same.
3. The direct current stabilized power supply device for aircraft structural strength test of claim 1, wherein the solenoid valve load connected to the first solenoid valve switching panel is smaller than the solenoid valve load connected to the second solenoid valve switching panel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010282720.7A CN111409852B (en) | 2020-04-12 | 2020-04-12 | Direct-current stabilized power supply device for airplane structural strength test |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010282720.7A CN111409852B (en) | 2020-04-12 | 2020-04-12 | Direct-current stabilized power supply device for airplane structural strength test |
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| Publication Number | Publication Date |
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| CN111409852A CN111409852A (en) | 2020-07-14 |
| CN111409852B true CN111409852B (en) | 2023-06-20 |
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| CN202010282720.7A Active CN111409852B (en) | 2020-04-12 | 2020-04-12 | Direct-current stabilized power supply device for airplane structural strength test |
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Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IT1289120B1 (en) * | 1996-07-04 | 1998-09-25 | Fki Fai Komatsu Ind Spa | HYDRAULIC CONTROL CIRCUIT FOR WORKING PARTS, IN PARTICULAR IN EARTH-MOVING MACHINES |
| CN101539483B (en) * | 2009-04-29 | 2010-11-03 | 北京航空航天大学 | Electric propulsion testing platform measurement control device |
| CN103631168A (en) * | 2013-12-04 | 2014-03-12 | 中国飞机强度研究所 | Structural function test control device |
| CN105136200A (en) * | 2015-08-19 | 2015-12-09 | 哈尔滨电机厂有限责任公司 | Universal wind pressure and wind speed testing device for large water turbine generator set ventilation system |
| CN108731974B (en) * | 2017-11-15 | 2024-03-19 | 江苏核电有限公司 | Multichannel sampling device and application method thereof |
| CN110195821B (en) * | 2019-05-09 | 2021-05-07 | 中国飞机强度研究所 | Hydraulic substation and electromagnetic valve control device |
| CN110543161B (en) * | 2019-07-16 | 2021-08-03 | 中航通飞华南飞机工业有限公司 | Static test device for control box of airplane direct current generator |
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