An electromagnetic valve signal controller for airplane full machine static and fatigue test
By designing a miniaturized solenoid valve signal controller and adopting a 5U standard cabinet and standard socket interface, the problems of large size and complex wiring of solenoid valve signal controllers have been solved, achieving the effect of easy handling and placement.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- CHINA AIRPLANT STRENGTH RES INST
- Filing Date
- 2025-07-02
- Publication Date
- 2026-06-09
Smart Images
Figure CN224339578U_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the technical field of aircraft static and fatigue test design, specifically relating to a solenoid valve signal controller for aircraft static and fatigue tests. Background Technology
[0002] The static and fatigue tests of the entire aircraft involve numerous loading points located in various positions. The actuators and their hydraulic substations are also scattered. The currently used solenoid valve signal controllers are large in size, making them difficult to transport and arrange. Furthermore, connecting the solenoid valves of the actuators and their hydraulic substations requires long control lines, resulting in complex wiring that is time-consuming and labor-intensive.
[0003] This application is made in view of the aforementioned technical deficiencies. Utility Model Content
[0004] The purpose of this application is to provide a solenoid valve signal controller for static and fatigue testing of an aircraft, so as to overcome or mitigate at least one of the known technical defects.
[0005] The technical solution of this application is:
[0006] A solenoid valve signal controller for static and fatigue testing of an aircraft includes a chassis and a power module;
[0007] The chassis uses a 5U standard rack, with an insulating board inside, and the power module is installed on the insulating board;
[0008] Multiple actuator solenoid valve sockets are installed on the front panel of the chassis;
[0009] The rear panel of the chassis is equipped with multiple actuator solenoid valve sockets, hydraulic substation solenoid valve high-pressure sockets, and hydraulic substation solenoid valve low-pressure sockets.
[0010] The power module includes a power supply, a high-voltage relay for the hydraulic substation, a low-voltage relay for the hydraulic substation, and an actuator relay.
[0011] The power supply, hydraulic substation high-voltage relay, hydraulic substation low-voltage relay, and actuator relay are mounted on the insulating plate via guide rails.
[0012] The power supply connects to the hydraulic substation high-voltage relay and hydraulic substation low-voltage relay on the rear panel. The hydraulic substation high-voltage relay and hydraulic substation low-voltage relay are connected to the hydraulic substation solenoid valve high-voltage socket and hydraulic substation solenoid valve low-voltage socket. The high-voltage and low-voltage terminals of the hydraulic substation solenoid valve are connected through the hydraulic substation solenoid valve high-voltage socket and hydraulic substation solenoid valve low-voltage socket, as well as the ground terminal of the hydraulic substation solenoid valve. The hydraulic substation high-voltage relay and hydraulic substation low-voltage relay are connected to the control system service manifold for control.
[0013] The power supply connects to each actuator relay, which in turn connects to each actuator solenoid valve socket on the front and rear panels. Through each actuator solenoid valve socket, the low-voltage and ground potential distribution terminals of multiple actuator solenoid valves are connected. The actuator relays are then connected to the control system service manifold for control.
[0014] According to at least one embodiment of this application, in the above-mentioned electromagnetic valve signal controller for static and fatigue testing of the entire aircraft, there are 18 actuator solenoid valve sockets on the front panel of the chassis, arranged in two rows. Each row of actuator solenoid valve sockets is equipped with a fault indicator light, which illuminates when a fault occurs in the corresponding row of actuator solenoid valve sockets.
[0015] There are 18 actuator solenoid valve sockets on the rear panel of the chassis, arranged in three rows. Each row of actuator solenoid valve sockets is equipped with a fault indicator light, which lights up when a fault occurs in the corresponding row of actuator solenoid valve sockets.
[0016] According to at least one embodiment of this application, in the above-mentioned electromagnetic valve signal controller for static and fatigue testing of the entire aircraft, a power indicator light is provided on the front panel of the chassis, the power indicator light illuminates when the power is turned on, and handles are provided on both sides of the front panel of the chassis.
[0017] The rear panel of the chassis is equipped with a power socket, a power switch, an input connector, and an output connector, wherein the input connector and the output connector are internally short-circuited.
[0018] The power supply is connected to the power switch and power socket on the rear panel. An external power supply is connected through the power socket, and the power switch controls the operation.
[0019] According to at least one embodiment of this application, in the above-mentioned solenoid valve signal controller for static and fatigue testing of the entire aircraft, a wiring terminal is provided on the front panel and the rear panel. The wiring terminal is connected in parallel with the actuator solenoid valve socket on the front panel and the rear panel, and serves as an interface for power output to the front panel and the rear panel.
[0020] According to at least one embodiment of this application, in the above-mentioned electromagnetic valve signal controller for static and fatigue testing of the entire aircraft, the connecting wires are treated with cold-pressed terminals or soldered copper wire lugs.
[0021] According to at least one embodiment of this application, in the above-mentioned electromagnetic valve signal controller for static and fatigue testing of the entire aircraft, the power supply is a 24V / 40A DC regulated power supply, the high-voltage relay and low-voltage relay of the hydraulic substation are 25A solid-state relays, and the actuator relay is a contactor.
[0022] This application has at least the following beneficial technical effects:
[0023] This invention provides a solenoid valve signal controller for static and fatigue testing of an aircraft. It is small in size, easy to transport, and can be flexibly arranged according to the distribution of loading points. It can be installed in a standard cabinet. In locations with many loading points, multiple solenoid valve signal controllers can be connected in series via input and output connectors, avoiding the use of long control lines and their complicated wiring. Attached Figure Description
[0024] Figure 1 This is a schematic diagram of the front panel of the chassis provided in an embodiment of this application;
[0025] Figure 2 This is a schematic diagram of the rear panel of the chassis provided in an embodiment of this application;
[0026] Figure 3 This is a schematic diagram of the power module provided in an embodiment of this application;
[0027] Figure 4 This is a schematic diagram showing the connection relationship between the power supply and the high-voltage relay, low-voltage relay, and hydraulic substation of the hydraulic substation provided in the embodiments of this application.
[0028] Figure 5 This is a schematic diagram showing the connection relationship between the power supply, the actuator relay, and its actuator provided in an embodiment of this application;
[0029] Figure 6 This is a sequence diagram of the sockets and their soldering wires on the front and rear panels provided in the embodiments of this application;
[0030] in:
[0031] 1-Power supply; 2-High-voltage relay of hydraulic substation; 3-Low-voltage relay of hydraulic substation; 4-Actuator relay.
[0032] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation
[0033] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.
[0034] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms indicating direction used in this application description are used only to indicate relative direction or positional relationship; when the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "comprising" as used in this application description indicates that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, but does not exclude other elements or objects.
[0035] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.
[0036] A solenoid valve signal controller for static and fatigue testing of an aircraft includes a chassis and a power supply module.
[0037] The chassis uses a 5U standard rack, which has a small size. It has an insulating board inside, and the power module is installed on the insulating board.
[0038] The front panel of the chassis is equipped with multiple actuator solenoid valve sockets, specifically up to 18 actuator solenoid valve sockets. The 18 actuator solenoid valve sockets are arranged in two rows, and each row of actuator solenoid valve sockets is equipped with a fault indicator light. The fault indicator light will illuminate when a fault occurs in the actuator solenoid valve socket in the corresponding row.
[0039] The front panel of the chassis can also be equipped with a power indicator light, which illuminates when the power is on, and handles can be placed on both sides, such as... Figure 1 As shown.
[0040] The rear panel of the chassis is equipped with multiple actuator solenoid valve sockets, specifically up to 18 actuator solenoid valve sockets. The 18 actuator solenoid valve sockets are arranged in three rows, and each row of actuator solenoid valve sockets is equipped with a fault indicator light. The fault indicator light will illuminate when a fault occurs in the actuator solenoid valve socket in the corresponding row.
[0041] The rear panel of the chassis also includes a high-pressure socket for the hydraulic substation solenoid valve and a low-pressure socket for the hydraulic substation solenoid valve.
[0042] The rear panel of the chassis may also include a power socket, power switch, input connector, and output connector. The input and output connectors are internally short-circuited, such as... Figure 2 As shown.
[0043] The solenoid valve sockets on the front panel and the solenoid valve sockets, high-pressure solenoid valve sockets, and low-pressure solenoid valve sockets on the rear panel can use original imported Amphenol products, model MS 3102A 14S-2S. The input and output connectors on the rear panel can use crimp terminals, with internal shorting for easy connection to a solenoid valve signal controller of the same model.
[0044] The power module includes power supply 1, hydraulic substation high-pressure relay 2, hydraulic substation low-pressure relay 3, and actuator relay 4, such as... Figure 3 As shown, in each relay, 1 and 2 are normally open, and 3 and 4 are 24V positive and negative.
[0045] Power supply 1, hydraulic substation high voltage relay 2, hydraulic substation low voltage relay 3, actuator relay 4 can be mounted on the insulating plate via guide rails, specifically using C45 standard guide rails.
[0046] Power supply 1 can be a 24V / 40A DC regulated power supply, specifically model Phoenix QUINT4-PS / 1AC / 24DC / 40 2904603, with dimensions of 120*130*140. The high-voltage relay 2 and low-voltage relay 3 of the hydraulic substation can be 25A solid-state relays, and the actuator relay 4 can be a contactor.
[0047] Power supply 1 connects to the power switch and power socket on the rear panel, and is powered by an external power source through the power socket, with the power switch controlling the switch.
[0048] Power supply 1 connects to the hydraulic substation high-pressure relay 2 and hydraulic substation low-pressure relay 3 on the rear panel. These relays connect to the high-pressure and low-pressure sockets of the hydraulic substation solenoid valves. The high-pressure and low-pressure terminals of the hydraulic substation solenoid valves are connected via these sockets, as well as to the ground terminal. The high-pressure and low-pressure relays 2 and 3 connect to the control system service manifold for control. Figure 4 As shown.
[0049] Power supply 1 connects to each actuator relay 4. Actuator relay 4 connects to each actuator solenoid valve socket on the front and rear panels. Through each actuator solenoid valve socket, the low-voltage and ground potential distribution terminals of multiple actuator solenoid valves are connected. Actuator relay 4 connects to the control system service manifold for control. Figure 5 As shown.
[0050] The front panel and rear panel have a terminal block connected in parallel with the actuator solenoid valve socket on the front panel and rear panel, which is the interface for power supply 1 to be output to the front panel and rear panel.
[0051] In the electromagnetic valve signal controller used for static and fatigue testing of the entire aircraft, the connecting wires are treated with cold-pressed terminals or soldered copper wire lugs, and the connections use potential distribution terminals and wiring terminals, such as... Figure 6 As shown.
[0052] The solenoid valve signal controller for static and fatigue testing of the entire aircraft disclosed in the above embodiments is small in size, easy to transport, can be flexibly arranged according to the distribution of loading points, and can be placed in a standard cabinet. In locations with many loading points, multiple solenoid valve signal controllers can be connected in series through input and output connectors, avoiding the use of long control lines and their complicated wiring.
[0053] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.
Claims
1. A solenoid valve signal controller for static and fatigue testing of an aircraft, characterized in that, Includes chassis and power supply module; The chassis uses a 5U standard rack, with an insulating board inside, and the power module is installed on the insulating board; Multiple actuator solenoid valve sockets are installed on the front panel of the chassis; The rear panel of the chassis is equipped with multiple actuator solenoid valve sockets, hydraulic substation solenoid valve high-pressure sockets, and hydraulic substation solenoid valve low-pressure sockets. The power module includes a power supply (1), a high-voltage relay for the hydraulic substation (2), a low-voltage relay for the hydraulic substation (3), and an actuator relay (4); The power supply (1), hydraulic substation high-voltage relay (2), hydraulic substation low-voltage relay (3), and actuator relay (4) are mounted on the insulating plate via guide rails. The power supply (1) is connected to the hydraulic substation high-pressure relay (2) and hydraulic substation low-pressure relay (3) on the rear panel. The hydraulic substation high-pressure relay (2) and hydraulic substation low-pressure relay (3) are connected to the hydraulic substation solenoid valve high-pressure socket and hydraulic substation solenoid valve low-pressure socket. The high-pressure and low-pressure terminals of the hydraulic substation solenoid valve are connected through the hydraulic substation solenoid valve high-pressure socket and hydraulic substation solenoid valve low-pressure socket, as well as the ground terminal of the hydraulic substation solenoid valve. The hydraulic substation high-pressure relay (2) and hydraulic substation low-pressure relay (3) are connected to the control system service manifold for control. The power supply (1) is connected to each actuator relay (4), the actuator relay (4) is connected to each actuator solenoid valve socket on the front panel and the rear panel, and the low-voltage and ground potential distribution terminals of multiple actuator solenoid valves are connected through each actuator solenoid valve socket. The actuator relay (4) is connected to the control system service manifold for control.
2. The electromagnetic valve signal controller for static and fatigue testing of an aircraft as described in claim 1, characterized in that, There are 18 actuator solenoid valve sockets on the front panel of the chassis, arranged in two rows. Each row of actuator solenoid valve sockets is equipped with a fault indicator light, which lights up when a fault occurs in the corresponding row of actuator solenoid valve sockets. There are 18 actuator solenoid valve sockets on the rear panel of the chassis, arranged in three rows. Each row of actuator solenoid valve sockets is equipped with a fault indicator light, which lights up when a fault occurs in the corresponding row of actuator solenoid valve sockets.
3. The electromagnetic valve signal controller for static and fatigue testing of an aircraft as described in claim 2, characterized in that, The front panel of the chassis is equipped with a power indicator light, which illuminates when the power is turned on, and handles are located on both sides of the front panel of the chassis. The rear panel of the chassis is equipped with a power socket, a power switch, an input connector, and an output connector, wherein the input connector and the output connector are internally short-circuited. The power supply (1) is connected to the power switch and power socket on the rear panel. The power supply is connected to an external power source through the power socket, and the power switch controls the switch.
4. The electromagnetic valve signal controller for static and fatigue testing of an aircraft as described in claim 3, characterized in that, The front panel and the rear panel have a wiring terminal, which is connected in parallel with the actuator solenoid valve socket on the front panel and the rear panel, and serves as the interface for power (1) output to the front panel and the rear panel.
5. The electromagnetic valve signal controller for static and fatigue testing of an aircraft as described in claim 4, characterized in that, The connecting wires are made using cold-pressed terminals or soldered copper wire lugs.
6. The electromagnetic valve signal controller for static and fatigue testing of an aircraft as described in claim 5, characterized in that, The power supply (1) adopts a 24V / 40A DC regulated power supply, the hydraulic substation high voltage relay (2) and the hydraulic substation low voltage relay (3) adopt 25A solid-state relays, and the actuator relay (4) adopts a contactor.