Oxygen monitor supporting self-detection of oxygen partial pressure sensor

Abstract

The utility model provides an oxygen monitor supporting self-detection of an oxygen partial pressure sensor. The oxygen monitor comprises a self-detection gas circuit, an electromagnetic valve, the oxygen partial pressure sensor and a control unit, an inlet of the self-detection gas path is connected with an onboard compressed air pipeline, an outlet of the self-detection gas path is connected with the oxygen partial pressure sensor through a first inlet of the electromagnetic valve, and a second inlet of the electromagnetic valve receives concentrated product gas; the control unit is connected with the electromagnetic valve and is used for opening a first inlet of the electromagnetic valve, closing a second inlet of the electromagnetic valve and communicating an onboard compressed air pipeline with the oxygen partial pressure sensor for self-detection when self-detection is needed; and when self-detection is not needed, the first inlet of the electromagnetic valve is closed, and the second inlet of the electromagnetic valve is opened. A detection gas circuit is additionally arranged on a structural part, so that in-situ oxygen partial pressure sensor precision detection of a product can be realized on a machine, the oxygen partial pressure sensors are ensured to be qualified products in the flight process, and the oxygen partial pressure sensors are detected outside a regular checking period of the product.

Description

Technical Field

[0001] The utility model belongs to the field of oxygen subsystems of aircraft systems and relates to an oxygen monitor supporting self-detection of an oxygen partial pressure sensor. Background Art

[0002] The oxygen monitor is a component of the oxygen concentrator and is used to detect the oxygen partial pressure during the oxygen production process of the oxygen concentrator. The high-concentration oxygen generated in the oxygen concentrator's oxygen production process is introduced into the oxygen monitor to detect the oxygen partial pressure in the gas. Therefore, when the oxygen monitor detects high-concentration gas, there are certain requirements for the accuracy of the oxygen partial pressure sensor inside the oxygen monitor. Once the detection error of the oxygen partial pressure sensor deviates too much, the detection results of the oxygen monitor will be inaccurate, resulting in some misjudgments. Utility Model Content

[0003] The purpose of this utility model is to propose an oxygen monitor with oxygen partial pressure sensor self-detection technology, add a detection air path on the structural parts, so that the product can realize in-situ oxygen partial pressure sensor accuracy detection on the aircraft, ensure that the oxygen partial pressure sensors are all qualified products during the flight, and detect the oxygen partial pressure sensors outside the product's regular inspection cycle.

[0004] The utility model provides an oxygen monitor supporting self-detection of an oxygen partial pressure sensor, comprising: a self-detection gas circuit, a solenoid valve, an oxygen partial pressure sensor and a control unit;

[0005] The inlet of the self-detection gas circuit is connected to the compressed air pipeline on the aircraft, the outlet of the self-detection gas circuit is connected to the oxygen partial pressure sensor through the first inlet of the solenoid valve, and the second inlet of the solenoid valve receives the concentrated product gas;

[0006] The control unit is connected to the solenoid valve and is used to open the first inlet of the solenoid valve and close the second inlet of the solenoid valve when self-testing is required, connect the on-board compressed air pipeline with the oxygen partial pressure sensor, and perform self-testing; when self-testing is not required, close the first inlet of the solenoid valve and open the second inlet of the solenoid valve.

[0007] Optionally, the control unit is further connected to an oxygen partial pressure sensor;

[0008] The control unit is specifically used to obtain the oxygen partial pressure detection result of the oxygen partial pressure sensor on the compressed air pipeline on the aircraft when self-test is required, compare the oxygen partial pressure detection result with the preset threshold range, and determine whether the self-test is passed.

[0009] Optionally, the control unit is specifically configured to determine that the self-test has passed when the oxygen partial pressure test result is within a preset threshold range.

[0010] Optionally, the control unit is specifically configured to receive a self-detection instruction input by a user, and upon receiving the self-detection instruction, determine that a self-detection is required.

[0011] Optionally, the control unit is specifically configured to determine that self-detection is required when it is detected that the wheel-borne signal indicates ground, the cumulative flight time is greater than a preset cumulative time, and the engine is in a starting state.

[0012] Optionally, the preset cumulative duration is 100 hours.

[0013] Optionally, the oxygen monitor is in the shape of a square box, and the self-detection gas circuit, solenoid valve, oxygen partial pressure sensor and control unit are arranged in the square box.

[0014] The present invention provides an oxygen monitor that supports self-testing of an oxygen partial pressure sensor. This self-testing technology automatically detects the oxygen partial pressure sensor after the monitor has been operating for a certain period of time, screening out sensors with substandard accuracy. This improves product quality and reduces false alarms. The advantage of this device is that, during actual flight, the product can ensure that the oxygen partial pressure sensor is tested in real time before each flight, ensuring that the oxygen partial pressure sensor's accuracy meets operational requirements and reducing false alarm rates on board. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following is a brief introduction to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are 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 labor.

[0016] Figure 1 Diagram of internal piping layout of oxygen monitor;

[0017] Figure 2 Software detection control logic principle block diagram. DETAILED DESCRIPTION

[0018] In order to make the purpose and advantages of the present invention more clearly understood, the present invention is described in detail below with reference to the following embodiments. The following text is only used to describe one or several specific implementations of the present invention and does not strictly limit the scope of protection specifically claimed by the present invention.

[0019] The oxygen supply device provided by the present invention will be explained below with reference to the accompanying drawings.

[0020] The utility model provides an oxygen monitor supporting self-detection of an oxygen partial pressure sensor, comprising: a self-detection gas circuit, a solenoid valve, an oxygen partial pressure sensor and a control unit;

[0021] The inlet of the self-detection gas circuit is connected to the compressed air pipeline on the aircraft, the outlet of the self-detection gas circuit is connected to the oxygen partial pressure sensor through the first inlet of the solenoid valve, and the second inlet of the solenoid valve receives the concentrated product gas;

[0022] The control unit is connected to the solenoid valve and is used to open the first inlet of the solenoid valve and close the second inlet of the solenoid valve when self-testing is required, connect the on-board compressed air pipeline with the oxygen partial pressure sensor, and perform self-testing; when self-testing is not required, close the first inlet of the solenoid valve and open the second inlet of the solenoid valve.

[0023] Optionally, the control unit is further connected to an oxygen partial pressure sensor;

[0024] The control unit is specifically used to obtain the oxygen partial pressure detection result of the oxygen partial pressure sensor on the compressed air pipeline on the aircraft when self-test is required, compare the oxygen partial pressure detection result with the preset threshold range, and determine whether the self-test is passed.

[0025] Optionally, the control unit is specifically configured to determine that the self-test has passed when the oxygen partial pressure test result is within a preset threshold range.

[0026] Optionally, the control unit is specifically configured to receive a self-detection instruction input by a user, and upon receiving the self-detection instruction, determine that a self-detection is required.

[0027] Optionally, the control unit is specifically configured to determine that self-detection is required when it is detected that the wheel-borne signal indicates ground, the cumulative flight time is greater than a preset cumulative time, and the engine is in a starting state.

[0028] Optionally, the preset cumulative duration is 100 hours.

[0029] Optionally, the oxygen monitor is in the shape of a square box, and the self-detection gas circuit, solenoid valve, oxygen partial pressure sensor and control unit are arranged in the square box.

[0030] like Figure 1 and 2 As shown, the utility model provides an oxygen monitor with oxygen partial pressure sensor self-detection technology. A self-detection air circuit is added inside the monitor for product self-detection. The self-detection air inlet is connected to the compressed air pipeline on the aircraft. At this time, the electromagnetic control of the air circuit is in the closed stage. When the actual work reaches 100 flight hours and is on the ground, the product meets the on-board self-detection conditions. The solenoid valve is opened using software control, and then the software enters the self-detection mode. The oxygen partial pressure value in the current compressed gas is collected through the oxygen partial pressure sensor and the value is compared with the standard threshold. If it is within the threshold range, it is determined that the oxygen partial pressure sensor has passed the self-detection, otherwise it has failed.

[0031] The technical solution of this utility model is: an oxygen monitor with oxygen partial pressure sensor self-detection technology. Based on the optimized design of the structural design, this type of oxygen monitor can realize the self-detection function of the oxygen partial pressure sensor on the aircraft. Its main application functions are as follows:

[0032] 1) Design a detection gas channel, connect it to the compressed air pipeline on the aircraft, and when the oxygen monitor needs to self-detect, open the internal gas circuit switch of the oxygen monitor to pass the self-detection gas into the oxygen monitor.

[0033] 2) Design the on-off control of the solenoid valve switch of the software to detect the switch of the air circuit and the oxygen partial pressure sensor to collect and compare with the set threshold, and judge whether the self-detection is passed based on the comparison error.

[0034] It has the functions of state selection and state monitoring.

[0035] The above description is merely a preferred embodiment of the present invention. It should be noted that those skilled in the art may make various improvements and modifications without departing from the principles of the present invention, and such improvements and modifications should be considered within the scope of protection of the present invention. Structures, devices, and operating methods not specifically described or explained in this invention shall, unless otherwise specified or limited, be implemented in accordance with conventional means in the art.

Claims

1. An oxygen monitor supporting self-detection of oxygen partial pressure sensor, characterized in that: include: Self-test gas circuit, solenoid valve, oxygen partial pressure sensor and control unit; The inlet of the self-detection gas circuit is connected to the compressed air pipeline on the aircraft, the outlet of the self-detection gas circuit is connected to the oxygen partial pressure sensor through the first inlet of the solenoid valve, and the second inlet of the solenoid valve receives the concentrated product gas; The control unit is connected to the solenoid valve and is used to open the first inlet of the solenoid valve and close the second inlet of the solenoid valve when self-testing is required, connect the on-board compressed air pipeline with the oxygen partial pressure sensor, and perform self-testing; when self-testing is not required, close the first inlet of the solenoid valve and open the second inlet of the solenoid valve.

2. The oxygen monitor according to claim 1, characterized in that The control unit is also connected to the oxygen partial pressure sensor; The control unit is specifically used to obtain the oxygen partial pressure detection result of the oxygen partial pressure sensor on the compressed air pipeline on the aircraft when self-test is required, compare the oxygen partial pressure detection result with the preset threshold range, and determine whether the self-test is passed.

3. The oxygen monitor according to claim 2, characterized in that The control unit is specifically configured to determine that the self-test has passed when the oxygen partial pressure test result is within a preset threshold range.

4. The oxygen monitor according to claim 1, characterized in that The control unit is specifically configured to receive a self-detection instruction input by a user, and upon receiving the self-detection instruction, determine that a self-detection is required.

5. The oxygen monitor according to claim 1, characterized in that The control unit is specifically used to determine that self-detection is required when it is detected that the wheel-borne signal indicates the ground, the cumulative flight time is greater than the preset cumulative time, and the engine is in the starting state.

6. The oxygen monitor according to claim 5, characterized in that The preset cumulative duration is 100 hours.

7. The oxygen monitor according to claim 1, characterized in that The oxygen monitor is in the shape of a square box, and the self-detection gas circuit, solenoid valve, oxygen partial pressure sensor and control unit are arranged in the square box.

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