Airtight test joint for aircraft cockpit system
By designing an airtight test joint for the aircraft cockpit system that includes multiple airtight input and output interfaces, the combination of sealing gaskets and plugs is used to solve the problem of poor airtightness of the existing joints, achieving higher airtightness and ease of operation.
Patent Information
- Application Number
- CN202422116653.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-29
- Publication Date
- 2025-05-27
- Estimated Expiration
- 2034-08-29
AI Technical Summary
The airtight test joints of the existing aircraft cockpit system are connected due to limited operating space, which leads to poor airtightness, affecting the test cycle and production progress.
An airtight test joint of the aircraft cockpit system is designed, including the joint body, a pressure relief port, a first airtight input interface, a second airtight input interface and an airtight output interface. The airtightness of the connection is ensured through the combination of a sealing gasket and an airtight interface plug cover, and the operation is simplified by the design of the pressure relief port.
It improves the airtightness and simplicity of the joint, reduces the difficulty of operation, shortens the test cycle, and meets the high requirements for airtightness of the aircraft cockpit system.
Smart Images
Figure CN222911107U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the technical field of aviation manufacturing, and particularly relates to an airtight test joint for an aircraft cockpit system. Background Technique
[0002] The cockpit system is used to collect the air pressure value and the pressure change rate in the cockpit, and issue an ultra-high alarm when the set altitude value is exceeded to prevent dangerous situations such as hypoxia and coma of the pilot caused by insufficient air pressure. When the cockpit system conducts an airtight test, an air pump or an airtight test vehicle needs to be connected to the on-board cockpit environment parameter acquisition host for air extraction (simulating the pressure drop when the altitude increases); since the airtight joint of the on-board cockpit environment parameter acquisition host is an M4 metric internal thread interface, the air pump is equipped with a pagoda head thread interface (equipped with a rubber hose), and the diameter of the rubber hose is relatively large. When connecting to the M4 internal thread interface of the airtight joint of the on-board cockpit environment parameter acquisition host, airtightness cannot be guaranteed. It is necessary to use a fuse or binding wire to tie the joint part. Since the length of the protruding part of the interface is short (about 15 mm) and the operating space is limited, the tying operation is difficult, which affects the connection airtightness and further affects the test cycle and production progress. The airtight test vehicle is equipped with an M6 external thread interface (equipped with a rubber hose with a threaded joint), which cannot be connected to the airtight interface of the on-board cockpit environment parameter acquisition host, and thus the airtight test cannot be carried out. Content of the Utility Model
[0003] The purpose of the utility model is to overcome the above-mentioned deficiencies of large limited operating space, difficult operation and weak connection airtightness, and provides an airtight test joint for an aircraft cockpit system.
[0004] In order to achieve the above purpose, the utility model adopts the following technical solutions.
[0005] In the first aspect, the utility model provides an airtight test joint for an aircraft cockpit system, which includes a joint body, a pressure relief port, a first airtight input interface, a second airtight input interface and an airtight output interface. The pressure relief port and the airtight output interface are respectively arranged at the left and right ends of the joint body. The first airtight input interface and the second airtight input interface are arranged side by side on the upper surface of the joint body. The upper ends of the first airtight input interface and the second airtight input interface are respectively provided with a first airtight interface plug and a second airtight interface plug. A first sealing washer is arranged at the connection between the first airtight input interface and the joint body, and a second sealing washer is arranged at the connection between the airtight output interface and the joint body. The first airtight input interface, the second airtight input interface and the airtight output interface are interconnected inside the joint body.
[0006] The utility model is further improved in that the joint body is a horizontally placed octagonal prism with a hollow cavity inside.
[0007] A further improvement of the present utility model lies in that the pressure relief port at one end of the joint body is a button with a spring plug.
[0008] A further improvement of the present utility model lies in that the first airtight input interface is an M6 threaded interface, which can be connected to an airtight test vehicle with a rubber hose having a threaded joint.
[0009] A further improvement of the present utility model lies in that the first airtight interface plug at the upper end of the first airtight input interface is adapted to the M6 threaded interface, and the first sealing washer provided at the lower end of the first airtight input interface is adapted to the M6 input threaded interface.
[0010] A further improvement of the present utility model lies in that the second airtight input interface is a taper-threaded interface, which can be connected to an air pump with a rubber hose.
[0011] A further improvement of the present utility model lies in that the outer side of the second airtight input interface is evenly distributed with threads. When connected to the hose of the air pump, the hose covers the threads.
[0012] A further improvement of the present utility model lies in that the second airtight interface plug at the upper end of the second airtight input interface is adapted to the taper-threaded interface, and a second airtight interface locking device is provided on the outer side of the second airtight interface plug.
[0013] A further improvement of the present utility model lies in that the airtight output interface is an M4 metric threaded output interface, which can be connected to the airtight test interface of an airborne cockpit environment parameter collector.
[0014] A further improvement of the present utility model lies in that a second sealing washer adapted to the M4 threaded interface is provided at the connection between the airtight output interface and the joint body, and a third airtight interface plug adapted to the M4 threaded interface is provided at the outer end of the airtight output interface.
[0015] Compared with the prior art, the present utility model has the following beneficial effects:
[0016] For the airtight test joint of the aircraft cockpit system disclosed by the present utility model, the first airtight input interface, the second airtight input interface and the airtight output interface are interconnected in the internal cavity of the joint body, rationally utilizing the equipment space and increasing the space utilization rate. The airtight interface plugs provided at the upper ends of the first airtight input interface and the second airtight input interface can be tightened and sealed with the plugs when the interfaces are not in use, ensuring airtightness. At the same time, the setting of the sealing washer further strengthens the airtightness of the equipment connection, and using the plugs and the sealing washer to ensure airtightness reduces the operation difficulty. In addition, the input interface is provided on the upper surface of the joint body, and the pressure relief port and the output interface are provided at both ends of the joint body, rationally utilizing the equipment resources.
[0017] Further, the joint body of the present utility model is a horizontally placed octagonal prism, which increases the utilization rate of its surface. The internal hollow cavity provides space for the connection of three interfaces, reduces the waste of space use, and improves the space utilization rate;
[0018] Further, the pressure relief port at one end of the joint body of the present utility model is a button with a spring plug. When the pressure relief function of the airtight test equipment fails, pressing the pressure relief port button can perform pressure relief. This function is easy to operate and effectively reduces the operation difficulty.
[0019] Further, the interface caps of the first airtight input interface and the second airtight input interface of the present utility model are respectively adapted to the threads of their corresponding input interfaces. By screwing for encryption or opening, the airtightness of the equipment connection can be effectively improved. In combination with the sealing gasket, the connection airtightness is further ensured.
[0020] Further, when the second airtight input interface of the present utility model is connected to the air pump, the hose configured by the air pump covers at least three thread pitches outside the input interface to ensure the connection airtightness between the air pump and the airtight input interface.
[0021] Further, after the second airtight input interface of the present utility model is connected to the air pump hose, the hose connection is locked and fixed by a locking device, which further improves the connection airtightness between the air pump and the airtight input interface.
[0022] Further, the airtight output interface of the present utility model is connected to the airborne cockpit environment parameter acquisition host by using a threaded interface that is mutually adapted, and in combination with a sealing gasket, which ensures the connection airtightness at the airtight output port connection. Description of the Drawings
[0023] Figure 1 is a three-dimensional view of an airtight test joint for an aircraft cockpit system;
[0024] Figure 2 is a side view of an airtight test joint for an aircraft cockpit system.
[0025] Number Explanation: 1. Joint body; 2. First airtight input interface; 3. First airtight interface cap; 4. Second airtight input interface; 5. Second airtight interface cap; 6. Airtight interface locking device; 7. Airtight output interface; 8. Pressure relief port; 9. Third airtight interface cap; 10. First sealing gasket; 11. Second sealing gasket; 12. Thread pitch. Detailed Embodiment
[0026] To further understand the content of the present utility model, the following describes the present utility model in detail with reference to the drawings and specific embodiments. It should be understood that the embodiments are only for explaining the present utility model and not for limiting it.
[0027] See Figure 1 and Figure 2 As shown in Figure 1 and Figure 2 , the joint body 1 of the airtight test joint for the aircraft cockpit system is an octagonal prism with a hollow cavity inside, placed horizontally. The first airtight input interface 2 and the second airtight input interface 4 are arranged side by side on the upper surface of the joint body 1. The first airtight input interface 2 is an M6 threaded interface, used to connect with the airtight test vehicle with a threaded joint rubber hose. The second airtight input interface 4 is a taper-threaded interface, used to connect with an air pump with a rubber hose. At the lower end of the first airtight input interface 2, there is a first sealing washer 10 adapted to the M6 threaded interface. At the upper ends of the first airtight input interface 2 and the second airtight input interface 4, there are respectively a first airtight interface plug 3 adapted to the M6 threaded interface and a second airtight interface plug 5 adapted to the taper-threaded interface. On the outside of the second airtight interface plug 5, there is also an airtight interface locking device 6. On the outside of the second airtight input interface 4, there are evenly distributed teeth 12. When the second airtight input interface 4 is connected to the air pump, the rubber hose of the air pump covers at least three teeth 12 on the outside of the second airtight input interface 4. On the left and right ends of the joint body 1, there are respectively a pressure relief port 8 and an airtight output interface 7. The pressure relief port 8 is a button with a spring flap. When the pressure relief function of the airtight test equipment fails, the pressure relief port 8 button can be pressed to relieve pressure. The airtight output interface 7 is an M4 metric threaded output interface. At the connection between the airtight output interface 7 and the joint body 1, there is a second sealing washer 11 adapted to the taper-threaded interface. At the outer end of the airtight output interface 7, there is a third airtight interface plug 9 adapted to the M4 threaded interface. The airtight output interface 7 is internally connected to the first airtight input interface 2 and the second airtight input interface 4 in the joint body 1.
[0028] A method for using the airtight test joint for the aircraft cockpit system:
[0029] When using an air pump to conduct an airtight test on the airtight test joint for the aircraft cockpit system, unscrew the third airtight interface plug 9 along the thread of the airtight output interface 7, connect the airtight output interface 7 to the airtight test interface of the on-board cockpit environmental parameter collector, and tighten it along the M4 thread until the second sealing washer 11 is pressed tightly for sealing; after one end of the hose is connected to the air pump, the other end of the hose is connected to the second airtight input interface 4. The second airtight interface plug 5 of the second airtight input interface 4 is in an open state. There are evenly distributed teeth 12 on the outside of the second airtight input interface 4. When the hose is connected to it, it covers at least three teeth 12 to ensure airtightness. The first airtight input interface 2 is sealed with the first airtight interface plug 3. At this time, the connection between the air pump and the on-board cockpit environment collector is completed, and the airtight test can be carried out;
[0030] When performing an airtightness test using an airtightness test vehicle, unscrew the third airtight interface plug 9 along the thread of the airtight output interface 7, connect the airtight output interface 7 to the airtightness test interface of the on-board cockpit environmental parameter collector, and tighten it along the M4 thread until the second sealing washer 11 is tightly pressed for sealing; the first airtight interface plug 3 of the first airtight input interface 2 is in the open state. One end of the hose equipped with the airtightness test vehicle is connected to the airtight interface of the airtightness test vehicle, and the other end is connected to the first airtight input interface 2. After connection, tighten it along the M6 thread until the first sealing washer 10 is tightly pressed for sealing. After the second airtight interface plug 5 of the second airtight input interface 4 is tightened for sealing, lock and seal the airtight interface locking device 6 outside the second airtight interface plug 5. At this time, the connection between the airtightness test vehicle and the on-board cockpit environmental parameter collector is completed, and the airtightness test can be carried out;
[0031] After the airtightness test is completed, when the pressure relief valve of the air pump or the airtightness test vehicle is damaged and cannot relieve pressure, press the button of the pressure relief port 8. The plug inside the pressure relief port 8 is pressed down with the spring, and the pressure is released. After the pressure relief is completed, release the pressure relief port 8, and disassemble and connect the first airtight input interface 2, the second airtight input interface 4, and the airtight output interface 7 in sequence, and use the recovery plug.
[0032] The utility model can be tested using an air pump or an airtightness test vehicle, providing flexibility in operation, adapting to different test conditions and requirements, and including the design of using sealing washers and coated screw threads to ensure the airtightness of the connection parts, improving the test accuracy and reliability. The use of an airtight interface locking device can further enhance the sealing performance, protect the equipment from external influences, and extend the service life of the equipment. When the pressure relief valve of the air pump or the airtightness test vehicle is damaged, safe pressure relief can be achieved by pressing the button of the pressure relief port to prevent danger caused by excessive pressure. The airtightness test joint of the utility model is reasonably designed, easy to operate, has high airtightness and safety, and has good flexibility and adaptability, and can meet the high requirements for the airtightness of the aircraft cockpit system.
[0033] In the present utility model, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present utility model, "a plurality of" means two or more, unless otherwise specifically defined. In the present utility model, unless otherwise clearly specified and defined, terms such as "installed", "connected", "joined", "fixed", etc. shall be construed in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection, an electrical connection, or a communication connection; it may be directly connected, or indirectly connected through an intermediate medium, and it may be the internal communication of two components or the interaction relationship between two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0034] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present utility model and not to limit them. Although the present utility model has been described in detail with reference to the above embodiments, those of ordinary skill in the art should understand that: modifications or equivalent replacements can still be made to the specific implementation manners of the present utility model, and any modifications or equivalent replacements that do not depart from the spirit and scope of the present utility model should be covered by the protection scope of the claims of the present utility model.
Claims
1. An airtight test joint for an aircraft cabin system, characterized in that: The invention comprises a joint body (1), a pressure relief port (8), a first airtight input interface (2), a second airtight input interface (4) and an airtight output interface (7); the pressure relief port (8) and the airtight output interface (7) are respectively arranged at the left and right ends of the joint body (1); the first airtight input interface (2) and the second airtight input interface (4) are arranged in parallel on the upper surface of the joint body (1); the upper ends of the first airtight input interface (2) and the second airtight input interface (4) are respectively provided with a first airtight interface plugging cover (3) and a second airtight interface plugging cover (5); a first sealing gasket (10) is provided at the connection between the first airtight input interface (2) and the joint body (1); a second sealing gasket (11) is provided at the connection between the airtight output interface (7) and the joint body (1); and the first airtight input interface (2), the second airtight input interface (4) and the airtight output interface (7) are interconnected inside the joint body.
2. The airtight test joint for an aircraft cabin system according to claim 1, characterized in that: The joint body (1) is a horizontally placed octagonal prism, the interior of which is a hollow cavity.
3. The airtight test joint for an aircraft cabin system according to claim 1, characterized in that: The pressure relief port (8) at one end of the connector body (1) is a button with a spring plug.
4. The airtight test joint for an aircraft cabin system according to claim 1, characterized in that: The first airtight input interface (2) is an M6 threaded interface and can be connected to an airtight test vehicle with a threaded joint rubber hose.
5. The airtight test joint for an aircraft cabin system according to claim 1, characterized in that: The first airtight interface plugging cover (3) at the upper end of the first airtight input interface (2) is adapted to the M6 threaded interface, and the first sealing gasket (10) provided at the lower end of the first airtight input interface (2) is adapted to the M6 input threaded interface.
6. The airtight test joint for an aircraft cabin system according to claim 1, characterized in that: The second airtight input interface (4) is a pagoda-shaped threaded interface, which can be connected to an air pump with a rubber hose.
7. The airtight test joint for an aircraft cabin system according to claim 6, characterized in that: The outer side of the second airtight input interface (4) is a uniformly distributed threaded opening (12), and when connected to the hose of the air pump, the hose covers the threaded opening (12).
8. The airtight test joint for an aircraft cabin system according to claim 1, characterized in that: The second airtight interface plugging cover (5) at the upper end of the second airtight input interface (4) is adapted to the pagoda-shaped threaded interface, and a second airtight interface locking device (6) is provided on the outer side of the second airtight interface plugging cover (5).
9. The aircraft cabin system airtight test joint according to claim 1, characterized in that: The airtight output interface (7) is an M4 metric thread output interface, which can be connected to the airtight test interface of the airborne cabin environmental parameter collector.
10. An aircraft cabin system airtight test joint according to claim 9, characterized in that: A second sealing gasket (11) adapted to the M4 threaded interface is provided at the connection between the airtight output interface (7) and the joint body (1), and a third airtight interface plugging cover (9) adapted to the M4 threaded interface is provided at the outer end of the airtight output interface (7).