阅读说明：本技术 一种用于飞机结构强度试验的直流稳压电源装置 (Direct-current voltage-stabilized power supply device for airplane structural strength test ) 是由 毛爽 张永兴 米征 牧彬 刘振宇 于 2020-04-12 设计创作，主要内容包括：本申请提供了一种用于飞机结构强度试验的直流稳压电源装置,包括：多个并联设置的24V直流稳压电源,用于将220V交流电转化为24V直流电；电压输出控制电路,电压输出控制电路包括第一继电器、第二继电器和电位分配端子,第一继电器连接飞机结构强度试验控制系统的服务歧管及第一电磁阀转换面板,用于输出第一电磁阀转换面板的控制信号,第二继电器连接24V直流稳压电源及电位分配端子,用于输出分配后的24V控制信号；第一电磁转换面板及第二电磁阀转接面板,分别连接飞机结构强度试验中所使用的不同功率的电磁阀。本申请的直流稳压电源装置相比于现有技术来说,电路结构紧凑规整、线缆敷设耗材量减少,输出效率高。(The application provides a direct current voltage-stabilized power supply device for aircraft structural strength is experimental, includes: the 24V direct current stabilized power supplies are arranged in parallel and 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 used for outputting a control signal of the first electromagnetic valve conversion panel, and the second relay is connected with a 24V direct-current stabilized power supply and the potential distribution terminal and 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 with different powers used in the aircraft structural strength test. Compared with the prior art, the direct-current voltage-stabilized power supply device has the advantages that the circuit structure is compact and regular, the quantity of consumed cable laying materials is reduced, and the output efficiency is high.)

1. A direct current voltage-stabilized power supply device for aircraft structural strength test, its characterized in that includes:

the 24V direct current stabilized power supplies are arranged in parallel and 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 used for outputting a control signal of the first electromagnetic valve conversion panel, and the second relay is connected with the 24V direct-current stabilized voltage power supply and the potential distribution terminal and used for outputting a distributed 24V control signal;

the first electromagnetic conversion panel and the second electromagnetic valve switching panel are respectively connected with different types of electromagnetic valves used in the aircraft structural strength test.

2. A regulated dc power supply apparatus for aircraft structural strength testing according to claim 1 wherein the number of said 24V regulated dc power supplies and said second relays are the same.

3. A regulated dc power supply apparatus for aircraft structural strength testing according to claim 1 wherein the solenoid valve load to which the first electromagnetic conversion panel is connected is less than the solenoid valve load to which the second electromagnetic conversion panel is connected.

4. A regulated dc power supply apparatus for aircraft structural strength testing according to claim 3 wherein the second relay is a mechanical relay.

5. A regulated DC power supply apparatus for aircraft structural strength testing according to claim 4 wherein the first relay is a solid state relay.

6. The regulated power supply apparatus for testing structural strength of an aircraft according to claim 4, further comprising a rack-mount power supply bracket for fixing the 24V regulated power supply and the voltage output control circuit.

Technical Field

The application belongs to the technical field of electric power, in particular to a direct current voltage-stabilized power supply device for an airplane structural strength test.

Background

In the current airplane structure strength fatigue test, 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, namely a special direct-current stabilized voltage supply, a 24V voltage output control circuit, an electromagnetic valve socket adapter panel and the like, and the working principle is as follows: the special direct current stabilized voltage power supply is used as power supply equipment, the output control circuit controls the high and low oil pressures of the oil way electromagnetic valves according to the output signals of the control system, and then the oil way electromagnetic valves are connected to the electromagnetic valves through the switching panel.

The problems that a 24V power supply vehicle used in the current test has high cost, large size, poor heat dissipation and low utilization rate of a special direct-current stabilized power supply are solved, and particularly, the stability of the vehicle used in the fatigue test for a long time is poor.

Disclosure of Invention

The application aims to provide a direct-current voltage-stabilized power supply device for an airplane structural strength test, so as to solve any one of the problems.

The technical scheme provided by the application is as follows: a direct current voltage-stabilized power supply device for aircraft structural strength tests comprises:

the 24V direct current stabilized power supplies are arranged in parallel and 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 used for outputting a control signal of the first electromagnetic valve conversion panel, and the second relay is connected with the 24V direct-current stabilized voltage power supply and the potential distribution terminal and 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 with different types and rates used in the aircraft structural strength test.

In one embodiment of the present application, the number of the 24V dc regulated voltage and the number of the second relays are the same.

In an embodiment of the present application, a solenoid valve load connected to the first solenoid conversion panel is smaller than a solenoid valve load connected to the second solenoid conversion panel.

In an embodiment of the present application, the second relay is a mechanical relay.

In an 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 voltage-stabilized power supply and the voltage output control circuit.

Compared with a power supply vehicle in the prior art, the direct-current voltage-stabilized power supply device is more compact and regular in circuit structure, the amount of consumed materials for cable laying is reduced, the normalized installation is more convenient to maintain, the power supply short circuit and the voltage output state can be protected, the electromagnetic valve adapter plate is distributed according to test requirements to improve the utilization rate and the loading capacity of a special power supply, and the output efficiency is high.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

Fig. 1 is a schematic diagram of a composition structure of a dc regulated power supply according to the present application.

Fig. 2 is a schematic diagram of the connection of the dc regulated power line of the present application.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

In order to overcome 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 voltage-stabilized power supply device for an airplane structural strength test.

As shown in fig. 1, a dc regulated power supply apparatus of the present application includes:

the system comprises a plurality of 24V direct current stabilized power supplies which are arranged in parallel, wherein the direct current stabilized power supplies are connected with commercial power and are used for converting alternating current of 220V commercial power 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 an 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 into 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 different types of electromagnetic valves used in the aircraft structural strength test.

The distributed 24V signals can be connected to each electromagnetic valve adapter panel on the test site from the potential distribution terminal by using a long wire, the number and scale of the adapter panels are determined by the layout of the fatigue test electromagnetic valves, each electromagnetic valve adapter panel is connected to an electromagnetic valve socket after overcurrent protection is performed by using a fuse terminal, and finally each electromagnetic valve is connected through an electromagnetic valve cable.

In one embodiment of the present application, the number of the 24V dc regulated voltage and the number of the second relays are the same.

In one embodiment of the present application, a solenoid valve load connected to the first solenoid switching panel is smaller than a solenoid valve load connected to the second solenoid switching 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, and the rack-mounted power supply bracket is used for fixing the first relay, the second relay, the potential distribution terminal, and the like of the 24V dc voltage-stabilized power supply and the voltage output control circuit.

Compared with a power supply vehicle in the prior art, the direct-current voltage-stabilized power supply device has the following advantages:

1. hardware such as a 24V direct-current stabilized power supply, a solid-state relay and a potential distribution terminal are fixed through a rack type power supply support and can be installed in an integrated machine room, and due to the innovative use of the direct-current stabilized power supply device, the overall size is reduced to 1/4, and the integration level is improved;

2. the 24V direct-current stabilized power supply has the advantages that the heat dissipation is fast, the power supply is used in the constant-temperature environment of the tested integrated machine room, the working state of the power supply is more stable, the test proves that the power supply can run for more than 30 days, and the requirements of a fatigue test are completely met;

3. the electric connection adopts the solid-state relay, the potential distribution terminal and the fuse terminal, so that the circuit structure of the direct-current stabilized voltage power supply special for the fatigue test is more compact and regular, the cable laying material consumption is reduced, and the standardized installation is more convenient for maintenance;

4. the electromagnetic valve switching panel uses the fuse terminal to protect the power supply short circuit and prompt the voltage output state, the electromagnetic valve switching panel improves the utilization rate and the loading capacity of the special power supply according to the distribution of test requirements, each 24V direct-current voltage-stabilized power supply can independently load 40 electromagnetic valves, and the output power reaches 80%.

Fig. 2 is a schematic diagram of a dc voltage regulator 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, a first relay, a second relay, a potential distribution terminal and the like, and the layout plan of each part;

then, products or structures of each part are installed and fixed on a U-shaped parallel guide rail of a rack type power supply support, the power supply support 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, a solid relay is coated with insulating heat-conducting silicone grease in advance and is provided with radiating fins, and electric elements such as a potential distribution terminal and an air switch are sequentially arranged according to the output flow direction of a power supply;

then, the second relay 120A in the connection cable, 24V voltage output line, takes 6mm of two colors of red and black²The high-quality copper wire and the solid-state relay adopt 2.5mm of red, green and yellow²The service manifold cables of the high-quality copper wires and all the relays are 0.5mm in red and black²The cables at the connecting terminals are inserted into the connecting terminals by adopting insulated cold-pressed terminals, and the cables at the bolt pressing connection positions are all welded with copper terminals, so that all the cables are ensured to be firmly connected and reliably contacted;

finally, fuse terminals are installed according to the number of the electromagnetic valve switching panels to be tested, and 6mm of red and black colors are laid in the wire grooves from the potential distribution terminals to the electromagnetic valve switching panels²High-quality copper wire.

After the implementation is completed, the direct-current stabilized voltage power supply special for the structural fatigue test needs to be debugged to ensure the normal work of the direct-current stabilized voltage power supply, and in addition, the contact of the relay needs to be regularly checked and timely replaced when the contact is oxidized.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.