An airborne optical window glass temperature-pressure difference test device

Abstract

The application discloses an airborne optical window glass temperature-pressure difference test device, a pressure transmitter is used for providing a pressure medium; one end of a pipeline is connected with the pressure transmitter, and the other end is connected to a sealed pressure test tool, which is used for realizing back-and-forth conveying of the pressure medium; a flow control valve body is installed on the pipeline, which is used for adjusting the flow of the pressure medium according to detection data of a sensor; an electric heater is installed on the pipeline, which is used for heating the pressure medium in the pipeline according to the detection data of the sensor and environmental temperature requirements; the sealed pressure test tool and the sensor are arranged in a high-low temperature test box; the sealed pressure test tool receives the pressure medium conveyed through the pipeline, simulates an aircraft cabin environment in the inside, and performs an optical window glass temperature-pressure difference strength test. The device has the advantages of simple structure, convenient installation and debugging and low cost, and can realize various safety verification tests of the optical window glass.

Description

Technical Field

[0001] This invention relates to the field of optical equipment technology, and in particular to an airborne optical window glass temperature and pressure difference testing device. Background Technology

[0002] With the integration of optical imaging equipment into airborne aircraft, optical window glass, as a crucial component of these devices, is widely used on the outer surface of the fuselage and at the light-transmitting windows of the imaging equipment. This optical window glass must ensure both functional light transmission and flight safety requirements. Regarding safety, considering the unique spatial location of the optical window glass—which isolates the aircraft into internal and external environments—during different phases of flight, the optical window glass will inevitably experience temperature and pressure differences between the cabin and the outside environment. Therefore, ground-based temperature and pressure difference tests are necessary to verify whether the optical window glass meets the safety requirements of the aircraft's flight environment at each phase. However, current technology lacks an effective solution for temperature and pressure difference testing of optical window glass. Summary of the Invention

[0003] The purpose of this invention is to provide an airborne optical window glass temperature and pressure difference testing device. This device has a simple structure, is easy to install and debug, and has low cost. It can perform various safety verification tests on optical window glass, such as temperature and pressure difference strength tests and destructive strength tests.

[0004] The objective of this invention is achieved through the following technical solution:

[0005] An airborne optical window glass temperature-pressure difference testing device, the device comprising a pressure transmitter (1), a pipeline (2), a flow control valve body (3), an electric heater (4), a high and low temperature test chamber (5), a sealed pressure test fixture (6), and a sensor (7), wherein:

[0006] The pressure transmitter (1) is used to provide a pressure medium;

[0007] One end of the pipeline (2) is connected to the pressure transmitter (1), and the other end is connected to the closed pressure test fixture (6). The pipeline (2) is divided into input and output pipelines, which are used to realize the back-and-forth transportation of pressure medium.

[0008] The flow control valve body (3) is installed on the pipeline (2) and is used to adjust the flow rate of the pressure medium according to the detection data of the sensor (7);

[0009] An electric heater (4) is installed on the pipeline (2) to heat the pressure medium in the pipeline (2) according to the detection data of the sensor (7) and the ambient temperature requirements;

[0010] The sealed pressure test fixture (6) and sensor (7) are installed in the high and low temperature test chamber (5) to control the temperature outside the aircraft cabin.

[0011] The closed pressure test fixture (6) receives the pressure medium transmitted through the pipeline (2) and simulates the cabin environment of an aircraft to conduct a temperature and pressure difference strength test on the optical window glass. The specific process is as follows:

[0012] When conducting the optical window glass temperature and pressure difference strength test, the pressure transmitter (1) inputs the pressure medium into the input pipeline (2), and the flow control valve (3) adjusts the flow rate through the input pipeline according to the pressure value measured by the sensor (7) and the test set pressure value. The pressure medium is heated by the electric heater (4), and the pressure medium that meets the temperature requirements enters the chamber of the sealed pressure test fixture (6) through the pipeline (2). At the same time, the pressure medium can also be transported back to the pressure transmitter (1) through the pipeline (2) to form a cycle. The circulating flow medium fills the chamber of the sealed pressure test fixture (6) with the temperature and pressure medium required for the test. The high and low temperature test chamber (5) provides the aircraft cabin temperature that meets the test requirements, thus forming a temperature difference and pressure difference between the aircraft cabin and the outside, thereby verifying whether the optical window glass meets the safety technical requirements of the aircraft flight environment.

[0013] The sensor (7) is installed inside the closed pressure test fixture (6) and includes a temperature sensor and a pressure sensor for measuring temperature data and pressure data.

[0014] As can be seen from the technical solution provided by the present invention, the above-mentioned device has a simple structure, is easy to install and debug, and has low cost. It can realize various safety verification tests of optical window glass, such as temperature and pressure difference strength test and destructive strength test. Attached Figure Description

[0015] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the following description of the embodiments will be briefly introduced. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram of the airborne optical window glass temperature and pressure difference testing device provided in an embodiment of the present invention;

[0017] Figure 2 This is a schematic diagram of the sealed pressure testing fixture described in an embodiment of the present invention. Detailed Implementation

[0018] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments, and do not constitute a limitation of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present invention.

[0019] like Figure 1 The diagram shown is a schematic of the airborne optical window glass temperature-pressure difference testing device provided in an embodiment of the present invention. The device includes a pressure transmitter (1), a pipeline (2), a flow control valve body (3), an electric heater (4), a high and low temperature test chamber (5), a sealed pressure test fixture (6), and a sensor (7), wherein:

[0020] The pressure transmitter (1) is used to provide a pressure medium;

[0021] One end of the pipeline (2) is connected to the pressure transmitter (1), and the other end is connected to the closed pressure test fixture (6). The pipeline (2) is divided into input and output pipelines, which are used to realize the back-and-forth transportation of pressure medium.

[0022] The flow control valve body (3) is installed on the pipeline (2) and is used to adjust the flow rate of the pressure medium according to the detection data of the sensor (7);

[0023] An electric heater (4) is installed on the pipeline (2) to heat the pressure medium in the pipeline (2) according to the detection data of the sensor (7) and the ambient temperature requirements;

[0024] The sealed pressure test fixture (6) and sensor (7) are installed in the high and low temperature test chamber (5) to control the temperature outside the aircraft cabin.

[0025] The closed pressure test fixture (6) receives the pressure medium transmitted through the pipeline (2) and simulates the cabin environment of an aircraft to conduct a temperature and pressure difference strength test on the optical window glass. The specific process is as follows:

[0026] When conducting the temperature and pressure difference strength test of the optical window glass, the pressure transmitter (1) inputs the pressure medium into the input pipeline (2), and the flow control valve (3) adjusts the flow rate through the input pipeline according to the pressure value measured by the sensor (7) and the test set pressure value. The pressure medium is heated by the electric heater (4). In specific implementation, the electric heater (4) heats the medium according to the value measured by the temperature sensor and the test set temperature value. The pressure medium that meets the temperature requirements enters the chamber of the sealed pressure test fixture (6) through the pipeline (2). At the same time, the pressure medium can also be transported back to the pressure transmitter (1) through the pipeline (2) to form a cycle. The circulating flow medium fills the chamber of the sealed pressure test fixture (6) with the temperature and pressure medium required for the test. The high and low temperature test chamber (5) provides the aircraft cabin temperature that meets the test requirements. This forms the temperature difference and pressure difference between the aircraft cabin and the outside, thereby verifying whether the optical window glass meets the safety technical requirements of the aircraft flight environment.

[0027] The sensor (7) is installed inside the closed pressure test fixture (6) and includes a temperature sensor and a pressure sensor for measuring temperature data and pressure data.

[0028] like Figure 2 The diagram shown is a structural schematic of the sealed pressure testing fixture according to an embodiment of the present invention. The sealed pressure testing fixture (6) includes a sealed chamber cover plate (601), fixing screws (602 and 610), a medium inlet (603 and 611), a medium outlet (604 and 612), a sealing gasket (605 and 608), an optical glass holder (606), an optical window glass (607), a sealed chamber main shell (609), a PT100 temperature sensor (701 and 703), and a pressure sensor (702), wherein:

[0029] The sealed chamber cover plate (601), the optical glass fixing frame (606) and the sealed chamber main shell (609) form a sealed chamber, which is the main part of the sealed pressure test fixture. This part of the structure has high strength and rigidity, and meets the corresponding test mechanical technical requirements.

[0030] The fixing screw (602) securely connects the sealed chamber cover plate (601) to the sealed chamber main shell (609), wherein the sealing gasket (605) achieves airtightness and watertightness between the sealed chamber cover plate (601) and the sealed chamber main shell (609);

[0031] The medium inlet (603 and 611) ensures that the medium is uniformly delivered into the chamber of the closed pressure test fixture (6), and the medium outlet (604 and 612) ensures that the medium flows out of the chamber of the closed pressure test fixture (6), thereby satisfying the cyclic input and output of media of different temperatures and pressures.

[0032] The optical window glass (607) is installed on the optical glass mounting bracket (606) by adhesive bonding and pressure plate pressing, and the two meet the requirements of air tightness and water tightness; wherein: the optical glass mounting bracket (606) is fastened to the main shell of the sealed cabin (609) by fixing screws (610), and the air tightness and water tightness between the optical glass mounting bracket (606) with optical window glass (607) and the main shell of the sealed cabin (609) are achieved by sealing gasket (608);

[0033] PT100 temperature sensors (701 and 703) are used to measure the temperature of the medium inside the chamber of the closed pressure test fixture (6);

[0034] The pressure sensor (702) is used to measure the pressure of the medium inside the chamber of the closed pressure test fixture (6).

[0035] In addition, in specific implementation, the medium transmitted in the device can be selected according to the actual test requirements, including gaseous medium or liquid medium, to meet the different temperature difference and pressure difference tests of the optical glass being tested.

[0036] It is worth noting that the contents not described in detail in the embodiments of the present invention belong to the prior art known to those skilled in the art. For example, the selection of different structural forms and sizes of optical window glass temperature and pressure difference test fixtures; the selection of different models and types of pressure transmitters, flow control valve bodies, electric heaters, high and low temperature test chambers and sensors; and the selection of different types of transmission media, these modifications and variations do not depart from the essential scope of the present invention.

[0037] In summary, the device described in the embodiments of the present invention has the following advantages:

[0038] 1. The optical window glass temperature and pressure difference test fixture has a simple structure, and the equipment involved is widely available in the market, making it easy and convenient to implement;

[0039] 2. This fixture has strong expandability and applicability. The structure and installation interface of the sealing pressure test fixture are designed according to the actual space conditions of the test piece to achieve the predetermined test purpose. At the same time, this fixture can also be used to conduct optical glass breaking strength tests to ensure the safety of aircraft flight and avoid the occurrence of dangerous and serious safety accidents.

[0040] The above description is merely a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims. The information disclosed in the background section is intended only to enhance the understanding of the overall background technology of the present invention and should not be construed as an admission or implication in any way that such information constitutes prior art known to those skilled in the art.

Claims

1. An airborne optical window glass thermal pressure differential test apparatus, characterized by comprising: The device comprises a pressure transmitter (1), a pipeline (2), a flow control valve body (3), an electric heater (4), a high-low temperature test box (5), a sealed pressure test tool (6) and a sensor (7), wherein: The pressure transmitter (1) is used for providing pressure medium; One end of the pipeline (2) is connected with the pressure transmitter (1), and the other end is connected to the sealed pressure test tool (6), the pipeline (2) is divided into input and output pipelines, and is used for realizing back and forth conveying of the pressure medium; The flow control valve body (3) is installed on the pipeline (2), and is used for adjusting the flow of the pressure medium according to the detection data of the sensor (7); The electric heater (4) is installed on the pipeline (2), and is used for heating the pressure medium in the pipeline (2) according to the detection data of the sensor (7) and the environmental temperature requirement; The sealed pressure test tool (6) and the sensor (7) are arranged in the high-low temperature test box (5), and the high-low temperature test box (5) is used for realizing control of the cabin temperature outside the aircraft; The sealed pressure test tool (6) receives the pressure medium conveyed through the pipeline (2), and simulates the cabin environment inside the aircraft in the inside, and performs the temperature-pressure difference strength test of the optical window glass, and the specific process is as follows: When the temperature-pressure difference strength test of the optical window glass is performed, the pressure transmitter (1) inputs the pressure medium into the input pipeline of the pipeline (2), the flow control valve body (3) adjusts the flow through the input pipeline according to the pressure value measured by the sensor (7) and the test set pressure value; the pressure medium is heated by the electric heater (4), the pressure medium meeting the temperature requirement is conveyed into the cabin body of the sealed pressure test tool (6) through the pipeline (2), and the pressure medium can also be conveyed back to the pressure transmitter (1) through the pipeline (2) to form a cycle; the circulating flow medium fills the cabin body of the sealed pressure test tool (6) with the temperature and pressure medium required by the test; the high-low temperature test box (5) provides the cabin temperature outside the aircraft meeting the test requirement, so that the temperature difference and the pressure difference between the cabin inside and outside the aircraft are formed, and whether the optical window glass meets the safety technical requirement of the flight environment of the aircraft is verified; The sensor (7) is arranged in the sealed pressure test tool (6), and comprises a temperature sensor and a pressure sensor, and is used for realizing temperature data measurement and pressure data measurement.

2. The apparatus according to claim 1, wherein The sealed pressure test tool (6) comprises a sealed cabin cover plate (601), fixing screws (602, 610), a medium input port (603, 611), a medium output port (604, 612), a sealing gasket (605, 608), an optical glass fixing frame (606), an optical window glass (607), a sealed cabin main shell (609), a PT100 temperature sensor (701, 703) and a pressure sensor (702), wherein: The sealed cabin cover plate (601), the optical glass fixing frame (606) and the sealed cabin main shell (609) form a sealed cabin. The fixed screw (602) fastens and connects the closed cabin cover plate (601) and the closed cabin main shell (609), wherein the sealing gasket (605) realizes the air and water tightness between the closed cabin cover plate (601) and the closed cabin main shell (609); The medium input port (603, 611) ensures uniform delivery of the medium into the cabin of the closed pressure test tool (6), and the medium output port (604, 612) ensures the output of the medium flow in the cabin of the closed pressure test tool (6), thereby meeting the circulation input and output of different temperature media and pressure media; The optical window glass (607) is installed on the optical glass fixing frame (606) by means of gluing and pressing, and meets the air and water tightness requirements; wherein: the optical glass fixing frame (606) is fastened and connected with the closed cabin main shell (609) by the fixed screw (610), and the air and water tightness between the optical glass fixing frame (606) with the optical window glass (607) and the closed cabin main shell (609) is realized by the sealing gasket (608); The PT100 temperature sensor (701, 703) is used to measure the medium temperature in the cabin of the closed pressure test tool (6); The pressure sensor (702) is used to measure the medium pressure in the cabin of the closed pressure test tool (6).

3. The apparatus of claim 1, wherein the apparatus is an airborne optical window glass temperature-pressure differential test apparatus. The medium transmitted in the device can select the medium type according to the actual test requirements, including gas medium or liquid medium, to meet the different temperature difference and pressure difference test of the measured optical glass.

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