Aircraft cockpit door pressure relief lock opening force test device

Abstract

The application belongs to the field of cockpit door pressure relief design, and particularly relates to a cockpit door pressure relief lock opening force test device. The cockpit door pressure relief lock opening force test device comprises an industrial personal computer, a thrust assembly and a pressure relief lock test bench. The industrial personal computer is used for generating a control instruction. The thrust assembly is used for applying pressure load to a lock tongue part of a pressure relief lock test piece according to the control instruction. The pressure relief lock test bench is used for fixed installation of the pressure relief lock test piece and simulation of a pressure difference environment of the pressure relief lock. The cockpit door pressure relief lock opening force test device solves the problem that there is a lack of cockpit door pressure relief lock opening force test capability under a ground environment at the present stage, can simultaneously simulate a pressure difference environment of a pressure relief lock pressure sensing area when a cabin is depressurized and pressure on the lock tongue part of the pressure relief lock, and supports pressure relief lock opening force test verification.

Description

Technical Field

[0001] This application belongs to the field of cockpit door depressurization design, and specifically relates to a test device for the opening force of an aircraft cockpit door depressurization lock. Background Technology

[0002] During high-altitude, high-speed flight of a civil aircraft, if a hole appears in the cockpit windshield, the pressure inside the cockpit door drops sharply. This causes a rapid increase in the pressure difference between the cockpit and passenger cabin, necessitating rapid depressurization to balance the pressure. Failure to depressurize in time can cause serious injury to the crew and severe damage to the cockpit floor and structure. In severe cases, it can endanger the pilot's life and cause the entire aircraft to lose control. Therefore, a rapid depressurization device must be designed into the cockpit. Rapid cockpit depressurization is achieved by opening a pressure relief valve to balance the pressure on the cockpit and passenger sides. Specifically, a pressure relief plate and a pressure relief sensor lock are installed on the cockpit door. When a hole appears in the cockpit, the pressure decreases rapidly, and the pressure wave propagates quickly from the windshield to the cockpit door. The pressure sensor detects the pressure difference between the two sides. When the pressure difference reaches a certain set value, the sensor lock quickly opens the upper and lower pressure relief plates via the pressure relief plate control shaft. To avoid activating the pressure sensor lock mechanism under artificial air pressure, a set value for the opening pressure difference is established. Because the cabin pressure is much higher than the cockpit pressure, the pressure relief valve is driven to open towards the cockpit. Opening methods include mechanical and electronic. Regardless of the opening method used, the pressure relief lock must be able to unlock within a certain pressure range under a specific pressure difference to meet airworthiness requirements. As a crucial component of the cockpit door's pressure relief function, the pressure relief lock needs to be tested and verified in a ground environment to ensure flight safety. Therefore, a cockpit door pressure relief lock opening force testing device must be designed. In ground tests, the pressure difference environment experienced by the pressure relief lock during cabin depressurization and the pressure load on the lock's latch must be simulated simultaneously. This testing method verifies that the pressure relief lock can unlock and open under the required atmospheric pressure, and that the opening force must meet specific requirements.

[0003] Current research mainly focuses on cockpit door design and pressure relief plate simulation analysis. For example, the paper "Evaluation and Simulation Calculation Method of Cockpit Door Pressure Relief Plate Based on Matlab" establishes a one-dimensional mathematical model of airflow in the pressurized cabin of a civil aircraft and proposes a method for calculating the area of ​​the cockpit door pressure relief plate. The paper "Discussion on the Selection of Pressure Relief Method for Civil Aircraft Cockpit Doors" introduces and analyzes two types of pressure relief locks: mechanical and electronic. None of the above studies discuss the design method of the test verification device for pressure relief locks, nor do they provide how to conduct test verification.

[0004] Therefore, there is an urgent need for a technical solution to overcome or mitigate at least one of the aforementioned defects in the existing technology. Summary of the Invention

[0005] The purpose of this application is to provide a test device for the opening force of an aircraft cockpit door depressurization lock, in order to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] An aircraft cockpit door depressurization lock opening force testing device, comprising:

[0008] The industrial control all-in-one computer is used to generate control commands;

[0009] A thrust assembly, which is used to apply a pressure load to the latch portion of the pressure relief lock test piece according to the control command;

[0010] A pressure relief lock test bench is used for the fixed installation of the pressure relief lock test piece and for simulating the pressure differential environment of the pressure relief lock.

[0011] In at least one embodiment of this application, the industrial control all-in-one computer is equipped with a touch screen operation panel for setting control parameters.

[0012] In at least one embodiment of this application, the thrust assembly includes:

[0013] Install base plate;

[0014] A PLC controller is mounted on the mounting base plate and connected to the industrial control all-in-one computer via control lines.

[0015] A thrust bracket, which is mounted on the mounting base plate;

[0016] The motor is mounted on the thrust bracket via a motor mounting bracket, and the motor is connected to the PLC controller via a control line;

[0017] A slide rail is mounted on the thrust bracket, and a slider is slidably mounted on the slide rail;

[0018] A lead screw shaft mounting base is mounted on the thrust bracket and located at the upper end of the slide rail;

[0019] A lead screw bearing housing is mounted on the thrust bracket and located at the lower end of the slide rail;

[0020] A ball screw, wherein the upper end of the ball screw is installed in the screw shaft mounting seat and connected to the motor via a coupling, the lower end of the ball screw is connected to the screw bearing seat, and a screw nut seat is installed in the middle of the ball screw and the screw nut seat is connected to the slider.

[0021] A sensor mounting bracket is connected to the lead screw nut seat;

[0022] The pressure head is mounted on the sensor mounting bracket via a load sensor.

[0023] In at least one embodiment of this application, the pressure relief lock test bench includes:

[0024] The mounting platform is mounted on the mounting base plate. The mounting platform has a circular groove and a ventilation channel. The circular groove is used to install the pressure relief lock test piece. The circular groove has a ventilation hole that communicates with the ventilation channel.

[0025] A suction pipe, one end of which is connected to the ventilation channel and the other end of which is connected to a vacuum pump;

[0026] An air intake pipe is connected to the ventilation channel, and a differential pressure sensor and a throttle valve are installed on the air intake pipe.

[0027] In at least one embodiment of this application, a rubber gasket is provided between the pressure sensing surface of the pressure relief lock test piece and the contact surface of the circular groove.

[0028] In at least one embodiment of this application, the ventilation channel includes a main channel and two branch channels. The main channel is connected to a ventilation hole in the circular groove. One branch channel is connected to the suction pipe, and the other branch channel is connected to the intake pipe. The outlets of the two branch channels are located on two different sides of the mounting platform.

[0029] The invention has at least the following beneficial technical effects:

[0030] The aircraft cockpit door pressure relief lock opening force test device of this application can simultaneously simulate the pressure difference environment of the pressure relief lock pressure sensing area and the pressure on the lock tongue part of the pressure relief lock when the cabin is depressurized, supporting the test verification of the pressure relief lock opening force. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of an aircraft cockpit door depressurization lock opening force testing device according to one embodiment of this application;

[0032] Figure 2 This is a schematic diagram of a thrust assembly according to one embodiment of this application;

[0033] Figure 3 This is a schematic diagram of a pressure relief lock test bench according to one embodiment of this application.

[0034] in:

[0035] 1. Industrial control all-in-one computer; 2. Thrust assembly; 21. Mounting base plate; 22. PLC controller; 23. Thrust device bracket; 24. Motor; 25. Motor mounting bracket; 26. Coupling; 27. Lead screw shaft mounting seat; 28. Lead screw nut seat; 29. ​​Slider; 210. Sensor mounting bracket; 211. Ball screw; 212. Slide rail; 213. Load sensor; 214. Pressure head; 215. Lead screw bearing seat; 3. Pressure relief lock test bench; 31. Mounting platform; 32. Differential pressure sensor; 33. Throttling valve; 34. Air extraction pipe; 35. Air inlet pipe. Detailed Implementation

[0036] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0037] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.

[0038] The following is in conjunction with the appendix Figures 1 to 3 This application will be described in further detail.

[0039] This application provides a test device for the opening force of an aircraft cockpit door pressure relief lock, including: an industrial control integrated computer 1, a thrust assembly 2, and a pressure relief lock test bench 3.

[0040] Specifically, such as Figure 1 As shown, the industrial control all-in-one computer 1 is used to generate control commands, the thrust assembly 2 is used to apply pressure load to the locking tongue part of the pressure relief lock test piece according to the control commands, and the pressure relief lock test bench 3 is used for the fixed installation of the pressure relief lock test piece and the simulation of the pressure difference environment of the pressure relief lock.

[0041] The industrial control all-in-one computer 1 is equipped with a touch screen operation panel. Control parameters are set on the touch screen, generating corresponding control commands. The thrust assembly 2, driven by the PLC controller 22, drives the servo motor 24 to rotate the ball screw 211, thereby causing the pressure head 214 mounted on the ball screw 211 to move up and down, applying pressure load to the locking tongue of the pressure relief lock test piece. The pressure relief lock test bench 3 enables the fixed installation of the pressure relief lock test piece and simulates the pressure differential environment of the pressure relief lock through the ventilation channel.

[0042] like Figure 2As shown, the thrust assembly 2 includes a mounting base 21, a PLC controller 22, a thrust bracket 23, a motor 24, a motor mounting bracket 25, a coupling 26, a lead screw shaft mounting seat 27, a lead screw nut seat 28, a slider 29, a sensor mounting bracket 210, a ball screw 211, a slide rail 212, a load sensor 213, a pressure head 214, and a lead screw bearing seat 215. The mounting base 21 can serve as the positioning structure for the entire aircraft cockpit door pressure relief lock opening force test device. The industrial control integrated computer 1, the thrust assembly 2, and the pressure relief lock test bench 3 can all be integrated and installed on the mounting base 21. The PLC controller 22 is bolted to the mounting base 21 and connected to the industrial control all-in-one computer 1 via a control line. The thrust bracket 23 is bolted to the mounting base 21 and has a motor mounting bracket 25 and a U-shaped mounting seat mounted on it. The motor mounting bracket 25 is located above the U-shaped mounting seat and is used to mount the motor 24. The U-shaped mounting seat is used to house the slide rail 212 and also to mount the lead screw shaft mounting seat 27 and the lead screw bearing seat 215. The motor 24 is bolted to the motor mounting bracket 25 and connected to the PLC controller 22 via a control line. The slide rail 212 is mounted on the U-shaped mounting seat. A slider 29 is slidably mounted; a lead screw shaft mounting base 27 is mounted on a U-shaped mounting base and located at the upper end of the slide rail 212, close to the motor 24; a lead screw bearing seat 215 is mounted on the U-shaped mounting base and located at the lower end of the slide rail 212; the upper end of the ball screw 211 is mounted in the lead screw shaft mounting base 27 and connected to the motor 24 via a coupling 26; the lower end of the ball screw 211 is connected to the lead screw bearing seat 215; a lead screw nut seat 28 is mounted in the middle of the ball screw 211 and is connected to the slider 29; a sensor mounting bracket 210 is connected to the lead screw nut seat 28; a load sensor 213 is mounted on the sensor mounting bracket 210; and a pressure head 214 is mounted at the lower end of the load sensor 213. During the test, the control parameters are set through the operation panel, and the industrial control all-in-one computer 1 generates control commands and sends them to the PLC controller 22. The PLC controller 22 controls the motor 24 to drive the ball screw 211 to rotate forward and backward. During this process, the slider 29 moves up and down along the slide rail 212, and the pressure head 214 moves up and down. After the pressure relief lock test piece is installed, the locking tongue is located below the pressure head 214. When the pressure head 214 moves downward, a pressure load can be applied to the locking tongue of the pressure relief lock test piece. When it moves upward, the pressure load is released.

[0043] like Figure 3As shown, the pressure relief lock test bench 3 includes a mounting platform 31, a differential pressure sensor 32, a throttle valve 33, an extraction pipe 34, and an inlet pipe 35. The mounting platform 31 is fixedly connected to the mounting base plate 21 by bolts at its four corners. A circular groove is formed on the upper surface of the mounting platform 31, and a ventilation channel is formed inside the mounting platform 31. The circular groove is used to mount the pressure relief lock test piece. A vent hole is formed inside the lower part of the circular groove, and the circular groove communicates with the ventilation channel through this vent hole. One end of the extraction pipe 34 is connected to the ventilation channel, and the other end is connected to a vacuum pump for evacuation. The inlet pipe 35 is connected to the ventilation channel, and a differential pressure sensor 32 and a throttle valve 33 are installed on the inlet pipe 35. The differential pressure sensor 32 can monitor the pressure difference between the ventilation channel inside the mounting platform 31 and the external atmospheric pressure to ensure that the pressure difference environment during the pressure relief lock test meets the specific pressure difference requirements. The throttle valve 33 is used to control the air intake speed and balance the internal and external pressure difference of the pressure relief lock test bench 3.

[0044] In a preferred embodiment of this application, the mounting platform 31 has pressure relief lock mounting holes around its circular groove. The pressure sensing surface of the pressure relief lock test piece is placed in the circular groove, and the pressure relief lock test piece is fixedly connected to the mounting platform 3 by bolts. A rubber gasket is provided between the pressure sensing surface of the pressure relief lock test piece and the contact surface of the circular groove to ensure airtightness.

[0045] In a preferred embodiment of this application, the ventilation channel includes a main channel and two branch channels. The main channel is connected to a ventilation hole in a circular groove. One branch channel is connected to an air extraction pipe 34, and the other branch channel is connected to an air inlet pipe 35. The outlets of the two branch channels are located on two different sides of the mounting platform 31.

[0046] The aircraft cockpit door pressure relief lock opening force testing device of this application can be used for cockpit door pressure relief lock opening force testing. During the test, the pressure relief lock test piece is installed on the mounting platform 31, with the pressure relief lock sensing surface in contact with the bottom surface of the circular groove. It is connected to an external vacuum pump through the air extraction pipe 34. During the test, the vacuum pump is turned on first, and the pressure difference between the inside and outside of the test platform is detected by the differential pressure sensor 32 on the pressure relief lock test platform 3. When the pressure difference required for the test is reached, the motor 24 is controlled to rotate by the industrial control integrated computer 1, which drives the pressure head 214 on the thrust assembly 2 to move downward, applying a pressure load to the locking tongue part of the pressure relief lock test piece. At the same time, the load sensor 213 installed above the pressure head 214 can record the pressure magnitude of the locking tongue part throughout the process. When the locking tongue is rotated to the open position, the test is stopped. At this time, the pressure value recorded by the load sensor 32 can be read to verify whether the pressure relief lock is normally opened within the specified pressure difference and pressure magnitude range.

[0047] The aircraft cockpit door pressure relief lock opening force test device of this application solves the problem of the lack of ground environment testing capability for aircraft cockpit door pressure relief lock opening force. It can simultaneously simulate the pressure difference environment of the pressure relief lock pressure sensing area and the pressure on the pressure relief lock tongue when the cabin is depressurized, supporting the verification of pressure relief lock opening force test.

[0048] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A device for testing the opening force of an aircraft cockpit door depressurization lock, characterized in that, include: An industrial control all-in-one computer (1) is used to generate control commands; The thrust assembly (2) is used to apply a pressure load to the latch portion of the pressure relief lock test piece according to the control command; Pressure relief lock test bench (3), the pressure relief lock test bench (3) is used for the fixed installation of the pressure relief lock test piece and the simulation of pressure differential environment of the pressure relief lock; The thrust assembly (2) includes: Install base plate (21); The PLC controller (22) is mounted on the mounting base plate (21) and is connected to the industrial control computer (1) via a control line. A thrust bracket (23) is mounted on the mounting base plate (21); The motor (24) is mounted on the thrust bracket (23) via a motor mounting bracket (25), and the motor (24) is connected to the PLC controller (22) via a control line; A slide rail (212) is mounted on the thrust bracket (23), and a slider (29) is slidably mounted on the slide rail (212). A lead screw shaft mounting base (27) is mounted on the thrust bracket (23) and located at the upper end of the slide rail (212); A lead screw bearing housing (215) is mounted on the thrust bracket (23) and located at the lower end of the slide rail (212); A ball screw (211) is installed at its upper end in the screw shaft mounting seat (27) and connected to the motor (24) via a coupling (26). The lower end of the ball screw (211) is connected to the screw bearing seat (215). A screw nut seat (28) is installed in the middle of the ball screw (211) and is connected to the slider (29). A sensor mounting bracket (210) is connected to the lead screw nut seat (28); A pressure head (214) is mounted on the sensor mounting bracket (210) via a load sensor (213); The pressure relief lock test bench (3) includes: Mounting platform (31), which is mounted on mounting base plate (21), has a circular groove and a ventilation channel on the mounting platform (31). The circular groove is used to install the pressure relief lock test piece, and a ventilation hole communicating with the ventilation channel is opened in the circular groove. The exhaust pipe (34) has one end connected to the ventilation channel and the other end connected to the vacuum pump; An intake pipe (35) is connected to the ventilation channel. A differential pressure sensor (32) and a throttle valve (33) are installed on the intake pipe (35).

2. The aircraft cockpit door depressurization lock opening force testing device according to claim 1, characterized in that, The industrial control all-in-one computer (1) is equipped with a touch screen operation panel for setting control parameters.

3. The aircraft cockpit door depressurization lock opening force testing device according to claim 2, characterized in that, A rubber gasket is provided between the pressure sensing surface of the pressure relief lock test piece and the contact surface of the circular groove.

4. The aircraft cockpit door depressurization lock opening force testing device according to claim 3, characterized in that, The ventilation channel includes a main channel and two branch channels. The main channel is connected to the ventilation hole in the circular groove. One branch channel is connected to the suction pipe (34), and the other branch channel is connected to the air inlet pipe (35). The outlets of the two branch channels are located on two different sides of the mounting platform (31).

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