Aircraft pneumatic valve environment simulation test platform

Abstract

The utility model relates to the technical field of pneumatic test, and discloses an aircraft pneumatic valve environment simulation test platform, comprising a box body used for placing a piece to be tested; the box body is provided with an exhaust channel and a plurality of test holes; the plurality of pipelines respectively penetrate through the plurality of test holes to enter the box body and are connected with the to-be-tested piece; the heater is arranged in the box body and is used for heating the box body; the vacuum pump is arranged in the box body and is used for manufacturing a low-pressure or vacuum environment in the box body; and the refrigerator is arranged in the box body and is used for refrigerating the box body. According to the technical scheme, the technical problems that in the prior art, the test condition is single, and the low-pressure environment test condition and the high-low temperature environment test condition cannot be simulated at the same time can be solved.

Description

Technical Field

[0001] This utility model relates to the field of aerodynamic testing technology, and in particular to an environmental simulation testing platform for aircraft aerodynamic valves. Background Technology

[0002] Aircraft pneumatic valve testing platforms are widely used in aircraft manufacturing, maintenance, and testing, playing a crucial role in ensuring aircraft safety and reliability. By conducting performance tests on pneumatic valves through these platforms, potential problems can be identified and resolved promptly, improving the overall performance of aircraft pneumatic valves.

[0003] Existing aircraft pneumatic valve testing platforms have limited testing conditions and cannot simultaneously incorporate simulations of low-pressure and high / low-temperature environmental testing conditions. Utility Model Content

[0004] This utility model discloses an aircraft pneumatic valve environment simulation test platform to solve the technical problems existing in related technologies, such as the single test conditions and the inability to simultaneously simulate low air pressure and high and low temperature environmental test conditions.

[0005] To solve the above problems, the present invention adopts the following technical solution:

[0006] An aircraft aerodynamic valve environment simulation test platform includes:

[0007] The enclosure, with its interior for holding the component to be tested, includes an exhaust channel and several test holes.

[0008] Several pipes pass through several test holes and enter the housing, and are connected to the test piece;

[0009] A heater is installed inside the chamber for heating the chamber.

[0010] A vacuum pump, installed inside the chamber, is used to create a low-pressure or vacuum environment inside the chamber;

[0011] A cooler is installed inside the enclosure to cool the enclosure.

[0012] In a further technical solution, the box has an inner liner area and a placement area; the placement area is located below the inner liner area;

[0013] The inner liner area is used to place the test piece, and the heater is disposed in the inner liner area; the placement area is used to place the vacuum pump and the cooler; a plurality of exhaust channels and a plurality of test holes are disposed in the inner liner area.

[0014] In a further technical solution, the inner liner area is divided into a first area and a second area by a partition;

[0015] The first area is used to place the heater, and the second area is used to place the device under test.

[0016] In a further technical solution, the inner liner area has a heat-insulating layer.

[0017] In a further technical solution, a sensor is also included, the signal input end of which extends into the inner liner area.

[0018] In a further technical solution, several test holes are divided into two groups and respectively set on opposite sides of the housing.

[0019] The technical solution adopted in this utility model can achieve the following beneficial effects:

[0020] This utility model discloses an aircraft pneumatic valve testing platform. The test piece (DPT) is placed inside a chamber, and pipes are selected to connect to some or all of the DPT's interfaces according to testing requirements. Then, a heater, vacuum pump, and cooler are used to simulate the testing environment inside the chamber, depending on the testing needs. Furthermore, the testing environment inside the chamber can be altered by changing the operating parameters of the heater, vacuum pump, and cooler to meet multi-condition testing requirements. Moreover, by connecting multiple pipes to some or all of the DPT's interfaces, gases at different temperatures can be introduced to simulate different testing environments. Attached Figure Description

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0022] Figure 1 This is an axial view of the aircraft pneumatic valve test platform of this utility model;

[0023] Figure 2 This is a top view of the aircraft pneumatic valve test platform of this utility model;

[0024] Figure 3 yes Figure 2 A cross-sectional view of plane AA.

[0025] In the picture:

[0026] 10-Box body, 10a-Test hole, 11-Placement area, 12-Inner chamber area, 121-First area, 122-Second area, 20-Heater, 30-Refrigerator, 40-Vacuum pump, 50-Baffle. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be described in detail below. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. Based on the embodiments of this utility model, all other implementation methods obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0028] The terms "first," "second," etc., used in the specification and claims of this application are used to distinguish similar objects and not to describe a specific order or sequence. It should be understood that such use of data can be interchanged where appropriate so that embodiments of this application can be implemented in orders other than those illustrated or described herein, and the objects distinguished by "first," "second," etc., are generally of the same class and the number of objects is not limited; for example, a first object can be one or more. Furthermore, in the specification and claims, "and / or" indicates at least one of the connected objects, and the character " / " generally indicates that the preceding and following objects are in an "or" relationship.

[0029] In the various embodiments of this application, "near end" and "far end" refer to the distance of each component from the user in the usage environment. The end closer to the user is designated as the "near end", and the end farther from the user is designated as the "far end".

[0030] An aircraft aerodynamic valve environment simulation test platform, please refer to Figures 1-3 It includes a housing 10, a heater 20, a vacuum pump 40, a cooler 30, and several pipes.

[0031] like Figures 1-3 As shown, the housing 10 has several test holes 10a. The test piece can be placed inside the housing 10. Several pipes pass through the test holes 10a and enter the housing 10. One end is connected to the test piece, and the other end is connected to a gas source, so that external gas can enter the test piece to test its pressure regulation characteristics, switching characteristics, flow capacity, and sealing performance.

[0032] It should be noted that when the gas from the gas source enters the test piece, it is adaptively heated according to the simulated test requirements of the test piece to meet the test requirements.

[0033] like Figure 2As shown, the chamber 10 contains a heater 20, a vacuum pump 40, and a cooler 30. The heater 20 heats the chamber 10, simulating the test piece under a certain high-temperature environment to determine if the parameters of the test piece's pressure regulation characteristics, switching characteristics, flow capacity, and sealing performance meet the standards. The vacuum pump 40 creates a low-pressure or vacuum environment within the chamber 10, simulating the test piece under a low-pressure or vacuum environment to determine if the parameters of the test piece's pressure regulation characteristics, switching characteristics, flow capacity, and sealing performance meet the standards. The cooler 30 cools the chamber 10, simulating the test piece under a low-temperature environment to determine if the parameters of the test piece's pressure regulation characteristics, switching characteristics, flow capacity, and sealing performance meet the standards.

[0034] By using heater 20 and vacuum pump 40, and cooler 30 and vacuum pump 40 together, chamber 10 can simulate test environments of low temperature and low pressure, and high temperature and low pressure, to meet the test requirements of the test device under different environments.

[0035] After the high-temperature test is completed, the cooler 30 can be activated to rapidly lower the temperature inside the chamber 10 to normal, making it easier for the operator to remove the test piece. Similarly, after the low-temperature test is completed, the heater 20 can be activated to rapidly raise the temperature inside the chamber 10 to normal, making it easier for the operator to remove the test piece.

[0036] In this embodiment, one side of the housing 10 can be opened and closed to facilitate the removal of the test piece from the housing 10 or the placement of the test piece in the housing 10.

[0037] The chamber 10 also has an exhaust channel. After the test is completed inside the chamber 10, the low-pressure environment inside the chamber 10 can be restored to normal through the exhaust channel, which makes it easier for the operator to remove the test piece from the chamber 10.

[0038] like Figure 3 As shown, the housing 10 has an inner liner area 12 and a placement area 11, which is used to place the vacuum pump 40 and the cooler 30. Accordingly, the vacuum pump 40 and the cooler 30 are respectively connected to the placement area 11 through pipes to create a low-temperature, low-pressure environment within the placement area 11.

[0039] A heater 20 is disposed in the inner chamber region 12, and several exhaust channels and several test holes 10a are disposed on the side wall of the housing 10 corresponding to the inner chamber region 12. The inner chamber region 12 is used to place the test piece; therefore, placing the heater 20 directly in the inner chamber region 12 allows the inner chamber region 12 to heat up rapidly. Correspondingly, the several exhaust channels and several test holes 10a disposed in the inner chamber region 12 also facilitate the rapid restoration of the low-pressure environment of the inner chamber region 12 to normal, and facilitate the connection of several pipes to the test piece.

[0040] like Figure 3As shown, the placement area 11 is located below the inner liner area 12 to optimize the layout of the cabinet 10, making the connection between the vacuum pump 40 and the cooler 30 and the inner liner area 12 more compact and efficient, and reducing the overall space occupied by the cabinet 10.

[0041] In addition, since the vacuum pump 40 and the cooler 30 have a certain weight, installing the vacuum pump 40 and the cooler 30 in the placement area 11 at the bottom of the housing 10 makes the structure of the housing 10 more stable.

[0042] like Figure 3 As shown, the inner chamber area 12 is divided into a first area 121 and a second area 122 by a partition. The first area 121 is used to house the heater 20, and the second area 122 is used to house the test piece. The presence of the partition completely separates the first area 121 and the second area 122 physically, thereby avoiding the direct thermal influence of the heater 20 on the test piece. This isolation helps ensure the accuracy and reliability of the test, while reducing interference factors during the test process.

[0043] The inner chamber area 12 has an insulation layer. The insulation layer helps reduce heat conduction from inside the chamber 10 to the outside, helps maintain the required temperature conditions during testing, and reduces the impact of temperature fluctuations on the test results.

[0044] The enclosure also includes sensors, with their signal input terminals extending into the inner chamber area 12. These sensors may include temperature sensors and pressure sensors to monitor parameters within the enclosure 10 in real time, ensuring that the parameters within the enclosure 10 meet analog testing standards.

[0045] like Figures 1-3 As shown, several test holes 10a are divided into two groups and are respectively set on opposite sides of the housing 10.

[0046] Specifically, two sets of several test holes 10a are respectively set on opposite sides of the housing 10 corresponding to the second region 122, so that the pipe can pass through the test holes 10a and connect to the interface of the test piece placed in the second region 122.

[0047] The working principle of this embodiment is as follows:

[0048] The test piece (DPT) is placed inside chamber 10, and pipes are selected to connect to some or all of the DPT's interfaces according to the testing requirements. Then, according to the testing requirements, the testing environment inside chamber 10 is simulated using heater 20, vacuum pump 40, and cooler 30. Simultaneously, the testing environment inside chamber 10 can be changed by altering the operating parameters of heater 20, vacuum pump 40, and cooler 30 to meet multi-condition testing needs. Furthermore, by connecting multiple pipes to some or all of the DPT's interfaces, gases at different temperatures can be introduced to simulate different testing environments. It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element.

[0049] Furthermore, it should be noted that the scope of the methods and apparatus in the embodiments of this application is not limited to performing functions in the order shown or discussed, but may also include performing functions substantially simultaneously or in the reverse order, depending on the functions involved. For example, the described methods may be performed in a different order than described, and various steps may be added, omitted, or combined. In addition, features described with reference to certain examples may be combined in other examples.

[0050] The above description is only a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model.

Claims

1. An aircraft aerodynamic valve environment simulation test platform, characterized in that, include: The housing, with the internal components used to hold the device under test; The enclosure has an exhaust channel and several test holes; Several pipes pass through several test holes and enter the housing, and are connected to the test piece; A heater is installed inside the chamber for heating the chamber. A vacuum pump, installed inside the chamber, is used to create a low-pressure or vacuum environment inside the chamber; A cooler is installed inside the enclosure to cool the enclosure.

2. The aircraft aerodynamic valve environment simulation test platform according to claim 1, characterized in that, The enclosure has an inner liner area and a placement area; the placement area is located below the inner liner area. The inner liner area is used to place the test piece, and the heater is disposed in the inner liner area; the placement area is used to place the vacuum pump and the cooler; a plurality of exhaust channels and a plurality of test holes are disposed on the side wall of the housing corresponding to the inner liner area.

3. The aircraft aerodynamic valve environment simulation test platform according to claim 2, characterized in that, The inner liner area is divided into a first area and a second area by a partition; The first area is used to place the heater, and the second area is used to place the device under test.

4. The aircraft aerodynamic valve environment simulation test platform according to claim 2, characterized in that, The inner liner area has a thermal insulation layer.

5. The aircraft aerodynamic valve environment simulation test platform according to claim 2, characterized in that, It also includes a sensor, the signal input end of which extends into the inner liner area.

6. The aircraft pneumatic valve environment simulation test platform according to claim 1, characterized in that, Several test holes are divided into two groups and are respectively set on opposite sides of the box.

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