INTEGRATED AVIONIC SAFETY MODULE

Abstract

The invention relates to a safety module for civilian and military aircraft that monitors the temperature, current, and voltage values ​​of equipment using a contactless and integrated sensor, and controls the power layers via a safety analysis algorithm through an internal programmable digital logic circuit to detect conditions such as overheating, excessive power consumption, overvoltage, sparks, and gas / smoke emissions.

Description

1 TARIFF INTEGRATED AVIONIC SAFETY MODULE Technical Area The invention addresses overheating, excessive power consumption, and overvoltage in civilian and military aircraft. To detect sparks, gas / smoke emissions, the equipment must have 5 features. Temperature, current, and voltage values ​​are measured using a contactless and integrated sensor. Safety analysis is monitored via an internal programmable digital logic circuit. with a safety module that controls the power layers using an algorithm It is related. Previous Tech 10 In current applications, high temperature conditions are handled by contact temperature sensors. It is measured using [method]. However, the CPU or power unit is located there. There are difficulties in positioning on surfaces. This is done in this way. These measurements are problematic in terms of both reliable measurement and sensitivity. Measurements made using this method depend on the sensor's location and the surface's 15 It depends on the situation. Therefore, the measurement data is unreliable. This is possible. On the other hand, calibration and deviations of measurement data present difficulties. It increases the level of safety. Furthermore, in current applications, it provides a higher level of safety. The risk posed by sparks, smoke, or gas emissions cannot be detected. High current and high voltage monitoring is performed using discrete sensors. Current 20 And voltage sensors also have similar measurement deviations and difficulties. It contains. In addition, the measurements of current and voltage sensors are also taken in conjunction with temperature sensors. Data integration and correlation are required. 2 According to document CN221225374U, which is included in the prior art, voltage and temperature are measured and monitored in the electronic equipment of aircraft. A method by which this is done is being discussed. According to document CN115513498A, which is included in the known state of the art, the temperature A 5-bit system that monitors temperature using a sensor and a temperature control algorithm. The system is being discussed. When examining the applications in the field, it is seen that temperature sensors are contactless. It is used in this way, and temperature, voltage and current measurements are also taken with a single module. The need arose to implement a module through which this process is carried out. Objectives of the Invention 10 The aim of this invention is to create a system where temperature sensors are used in a contactless manner. It is the implementation of an integrated avionics safety module. Another aim of this invention is to measure temperature, voltage, and current using a single module. It is the implementation of a security module through which security is ensured. Detailed Description of the Invention 15 An integrated safety module has been added to achieve the purpose of this invention. This is shown in the figures. These shapes; Figure 1: Schematic view of the safety module that is the subject of the invention. Figure 2: Contactless temperature control module 20 to be used in the safety module subject to the invention. This is a schematic view of the first layer of the sensor. 3 Figure 3: Contactless temperature to be used in the safety module subject to the invention. This is a schematic view of the second layer of the sensor. Figure 4: Contactless temperature to be used in the safety module subject to the invention. This is a schematic view of the sensor's third layer. The parts shown in the figures are individually numbered, and these numbers correspond to 5. The corresponding answers are given below. 100. Integrated avionics safety module 110. Non-contact temperature sensor 120. Power control unit 130. Voltage measurement unit 10 140. Current measurement unit 150. Programmable digital logic circuit 210. Bizmuth 220. Antimon 230. Voltage difference 15 300. Second layer 310. Cold section 320. Hot episode 400. Third layer 4 410. Mask The subject of the invention is an integrated avionics safety module (100), - Non-contact temperature sensor that enables the measurement of temperature data of avionics devices. sensor (110), - Current measurement unit (140) enabling the measurement of current data of the avionics device, 5 - a voltage measurement unit that enables the measurement of voltage data of an avionics device. (130), - non-contact temperature sensor (110), current measurement unit (140) and voltage measurement by processing the data from the unit (130) and the data from the determined threshold value A programmable 10 that generates a warning or error code if the value is too high. Digital logic circuit (150) It includes. The subject of the invention is an integrated avionics safety module (100), contactless temperature. in the sensor (110) - two U shapes joined end to end, one inverted and one upright, and each half of the U shape is 15 bismuth (210) and the other half is antimony (220) metal and the most a unit of measurement used to measure the voltage difference between open terminals at the ends, - Based on the straight U shape, the cold section (310) is at the top of the U shape and Hot section at the bottom (320), - a mask (410) covering the top of the hot section (320) located at the bottom 20 It includes. The subject of the invention is the integrated avionics safety module (100), unsafe condition. After the signal is transmitted, the alternating current and direct current power layers It includes a power control unit (120) that cuts off the power to the device by closing its outputs. The Integrated Avionics Safety Module (100) is schematically shown in Figure 1. Ensuring safety requirements in civil and military aviation equipment 5 It has been developed for this purpose. In the integrated avionics safety module (100); temperature, Current and voltage measurements are performed via a single module. Temperature The measurement is done by a non-contact temperature sensor (110). is being done. Temperature measurement is done using a non-contact temperature sensor (110) 10 thanks to this, measurement errors and unstable measurement results are avoided. This is prevented. Also, due to the distance or location from internal heat sources of the device. This also prevents measurement errors that may occur. Temperature measurement data, current Fusion of measurement unit (140) data and voltage measurement unit (130) data; It is done on a Programmable Digital Logic Circuit (150). 15 Safety analysis on Programmable Digital Logic Circuit (150) The algorithm makes its decision based on the evaluation of these three parameters. Real-time data obtained at a frequency of 100MHz is received in 5ms intervals. Evaluation of the average results obtained and comparison with threshold values. The decision is made based on the outcome. The device's internal anomaly condition is Programmable 20. With a higher reliability value on the Digital Logic Circuit (150) These can be detected. False warning and erroneous power outage situations. It reduces the risk of unsafe conditions. The algorithm for detecting unsafe conditions generally takes 5ms. The values ​​obtained in different periods giving the same result after 10 cycles It gives an alarm depending on the situation. The device has a voltage measurement unit (130) 10% of 25 increase or decrease over, increase of more than 10% in current measurement unit (140) or decrease, of the nominal temperature value in the non-contact temperature sensor (110) All of the measurement conditions simultaneously, for 10 measurement cycles. 6 If received, it triggers an alarm and detects an unsafe situation. The nominal temperature value is unique to each device and CPU and / or power module. Therefore, this value will be set during the design phase. 5ms measurement. in the cycles; voltage measurement with an increase / decrease of 10% or more and current measurement An increase / decrease of 10% or more, and exceeding the threshold value in temperature measurement. The measurement cycle must last for 50ms. Anything outside of this period... These situations are defined as instantaneous errors or inaccurate measurements. Current applications include spark, smoke, and gas detection within avionics devices. There are no designs that do this. Data in the non-contact temperature sensor (110) The spectrum of outputs of the developed Programmable Digital Logic Circuit (150) 10 By utilizing the capabilities of the safety analysis algorithm on it; spark, Unsafe conditions such as smoke and gas emissions can be detected. Non-contact temperature sensor (110); based on the Thermopile sensor structure It is achieved through innovative additions to the Thermopile sensor array. Increased sensitivity level and also Dielectric Deposit Mask (410) 15 By filtering the reflected rays through this application, stability is also ensured. The thermopile sensor array has been enhanced by using two different metal elements. a sequence of Bismuth (210) and Antimony (220) metals as an example It is a sensor model created by arranging the array. As the temperature changes, the array's array... Temperature measurement by changing the voltage difference (230) between the two poles 20 It is implemented. This model includes the known part of the technology. The string highlighting the hot section (320) and cold sections (310) and In order to increase the difference, the second layer (300) is schematically shown in Figure-3. The application was made. On the Cold Section (310) joints applied reflective aluminum, for example a Deposition-like coating 25 By creating it using this method, the relevant areas are completely isolated from IR radiation exposure. and IR rays are reflected away. Similarly IR absorber dielectric on the Hot Section (320) junctions 7 The layer is placed using a coating similar to Deposition, for example. This allows more IR rays to be transmitted to the relevant points, and the sensor to be more... It has been designed to detect excessive heat. The third one, schematically shown in Figure 4, The stability level has also been increased with layer (400). Third layer (400) In the application, the area around the hot section (320) junctions is again dielectric 5 deposition of a sample with a depth of approximately 750 micrometers using a mask (410). or is positioned in such a way as to be formed by a different coating method. This mask (410), emitted from the components that create a heat source inside the device but inside the device indirect IR rays reflected from the wall or the surface of other electronic boards It filters the temperature. This allows for a more stable, contactless temperature measurement. 10 It has been proven. If an unsafe situation is identified, the first step is to... Programmable Digital Logic Circuit (150) In-device test (Digital Data) An unsafe condition detection signal is generated via the interface. In this way, The aircraft's CIT control system identifies which piece of equipment, which 15, is in the unsafe condition. It will be able to record when and what type of problem it occurred. Unsafe Status Signal is again on the Programmable Digital Logic Circuit (150) It is also recorded in the permanent memory unit located on the aircraft's ICT system. There is a possibility that it cannot be recorded, and this record is for Device Maintenance statistics. will be used. 20 After the unsafe condition signal is transmitted, the power control unit (120) by shutting off the outputs of the alternating current and direct current power layers of the device It cuts off the power. This stops the equipment from working. The process may result in excessive temperature, power imbalance, gas / smoke emissions, etc. The influence of external factors on the events will be prevented. The other 25 on the aircraft systems, potential hazards to crew and passengers resulting in death and / or injury It is a safety device that prevents the potential consequences.

Claims

8 REQUESTS 1. The invention addresses overheating, excessive power consumption, and overheating issues in civilian and military aircraft. To detect voltage, sparks, and gas / smoke emissions, The temperature, current, and voltage values ​​of the equipment are monitored in a contactless and integrated manner. Internal programmable digital logic circuit 5 monitored by sensor control of power layers via safety analysis algorithm It is a safety module that is made, - Non-contact measurement of temperature data of avionics devices. temperature sensor (110), - Current measurement unit 10 that enables the measurement of current data of the avionics device. (140), - voltage measurement that enables the measurement of voltage data of the avionics device. unit (130), - non-contact temperature sensor (110), current measurement unit (140) and voltage measurement processing the data from unit (130) and the data up to the specified threshold 15 a system that generates a warning or error code if its value is higher than a certain level Programmable Digital Logic Circuit (150) includes and non-contact temperature sensor (110) - two U shapes joined end to end, one inverted and one upright, and each half of the U shape is 20 bismuth (210) and the other half is antimony (220) metal and the most a unit of measurement used to measure the voltage difference between open terminals at the ends, - Based on the straight U shape, the cold section (310) is at the top of the U shape and Hot section at the bottom (320), - a mask (410) covering the top of the hot section (320) located at the bottom 25 It is characterized by its inclusion. 9 2. A safety module as described in Claim 1, which transmits a signal indicating a non-safe condition. after transmission, alternating current and direct current power layers Power control unit (120) that cuts off the power of the device by closing its outputs It is characterized by its inclusion.

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