A method for error detection in components that provide altitude detection in aircraft

Abstract

The invention is related to a computer-implemented method that can detect clogging / icing or malfunctions that may occur in the static port and / or altitude detection components such as inertial reference system and / or altimeter in the aircraft during flight.

Description

[0001] A METHOD FOR ERROR DETECTION IN COMPONENTS THAT PROVIDE ALTITUDE DETECTION IN AIRCRAFT

[0002] Technical Field

[0003] The invention relates to a computer-implemented method that can detect clogging / icing and / or malfunctions that may occur in the static port and / or altitude detection components such as inertial reference system or altimeter in the aircraft during flight.

[0004] State of the Art

[0005] It is of great importance to read the environmental information in the aviation sector. For this reason, both aircraft status information and ambient information are detected through various components in aircraft and similar aircraft and shown to the pilot through interfaces.

[0006] One of the most important environmental information is the aircraft altitude information. Since the pilot cannot access this information and cannot make a healthy prediction, not being able to get altitude information or getting it wrong can cause fatal accidents.

[0007] Altitude information in aircraft is detected by the inertia reference system or altimeters provided from the static port and transferred to the pilot. The static port is a special opening or inlet on the aircraft that connects to the static pressure system. The static port allows the altimeter and other instruments to detect the static pressure of ambient air at the height of the aircraft. This static pressure measurement is crucial for accurate altitude and air velocity indicators.

[0008] Clogging / icing may occur in the static port due to technical malfunctions and adverse environmental conditions that may occur in the aircraft. For these reasons, an error may occur in the altitude information received from the static port. Meanwhile, technical malfunctions may occur in the mechanism of the altimeter system. The altitude information can be read incorrectly by the pilot in this case. As a result of these reasons, aircraft accidents may occur. Altitude information is also obtained from the gyroscope and accelerometers in the inertial reference system (IRS) in aircraft. Since this system is a closed system, data closer to reality are obtained. At the same time, such a closed system is less likely to malfunction.

[0009] All the problems mentioned above have made it necessary to make an innovation in the relevant field as a result.

[0010] Brief Description and Objects of the Invention

[0011] The main object of the invention is to detect and notify the pilot of altimeter and / or static port errors and malfunctions in aircraft and to provide a computerized method and the structure of a system to carry out this method to prevent accidents due to incorrect altitude measurements.

[0012] According to this object, by matching the flight phase (climb, descent, level flight) and inertia reference system and altimeter data in the existing aircraft system, errors in the altimeter and / or static port freezing and clogging problems are detected.

[0013] Detailed Description of the Invention

[0014] The subject matter of the invention relates to a computer-implemented method that can detect clogging / icing or malfunctions that may occur in the static port and / or altitude detection components such as inertial reference system or altimeter in the aircraft during flight.

[0015] It has been revealed in the studies carried out for the subject matter of the present invention that the specific combinations of the comparisons of the flight phase and inertia reference system and altimeter data of the aircraft, preferably an aircraft, indicate various malfunctions (altimeter malfunction, freezing or clogging in the static port) on the aircraft and a method for obtaining the results depending on these combinations and a system to carry out this method and a program required to carry out the method have been proposed.

[0016] Firstly, the flight phase of the aircraft is determined in the method of the invention. Said flight phase refers to the climb, descent, and level flight states of the aircraft. In order to detect said flight phases; gyroscope, accelerometer, inertial reference system, indicators for the orientation of the axes of the aircraft according to the reference line or plane and similar systems can be used. Here, climbing means that the altitude of the aircraft gradually increases, descending means that the altitude of the aircraft gradually decreases and level flight means that the altitude of the aircraft remains constant.

[0017] In addition to the flight phase, altitude data is read in two different systems. These are the inertia reference system and the altimeter. An altimeter is an instrument used to measure the height of an object above a fixed level, usually the Earth's surface. It is a very important tool in aviation, mountaineering and other activities where it is important to know the height or altitude. The most common type of altimeter used in aviation is the barometric altimeter. The altimeter basically measures atmospheric pressure. As the altitude of the aircraft increases, the atmospheric pressure decreases and as the altitude decreases, the atmospheric pressure increases. The altimeter performs altitude detection through this change. For the present invention, the altimeter receives information from the static port.

[0018] At this point, the altitude data read by the inertia reference system and the altimeter are compared with each other. The comparison is preferably performed by a data processing unit. Preferably the data processing unit can communicate directly with the inertia reference system and the altimeter in such a way that it can receive the altitude data. Alternatively, the data read by the inertial reference system and the altimeter are transferred to the data processing unit.

[0019] Table 1: Table of results obtained by considering the altimeter- IRS altitude data comparison according to the flight phase

[0020] As can be seen in Table 1, if the altitude data obtained from the altimeter while the aircraft is climbing is greater than the altitude data obtained by the inertial reference system, it is a static port problem; if the altitude data obtained from the altimeter is less than the altitude data obtained by the inertial reference system, it is an altimeter problem; if the altitude data obtained from the altimeter is equal to the altitude data obtained by the inertial reference system, it is concluded that there is no problem.

[0021] When the aircraft is descending, it is concluded that there is an altimeter problem if the altitude data obtained from the altimeter is greater than the altitude data obtained by the inertial reference system, a static port problem if the altitude data obtained from the altimeter is less than the altitude data obtained by the inertial reference system, and no problem if the altitude data obtained from the altimeter is equal to the altitude data obtained by the inertial reference system.

[0022] When the aircraft is in level flight, if the altitude data obtained from the altimeter is greater than the altitude data obtained by the inertial reference system, there is an altimeter problem; if the altitude data obtained from the altimeter is less than the altitude data obtained by the inertial reference system, there is an altimeter problem; if the altitude data obtained from the altimeter is equal to the altitude data obtained by the inertial reference system, there is no problem.

[0023] After the data processing unit in the system for the current method detects the problems for the match combinations, it creates a special warning response to the relevant problem and this response is forwarded to the pilot or related units.

Claims

CLAIMS1. A computer-implemented method that can detect clogging / icing or malfunctions that may occur in the static port and / or altitude detection components such as altimeter in the aircraft during flight, characterized by:Receiving the flight phase data indicating whether the aircraft is in climb, descent, or level flight state, receiving the altitude data read by the inertial reference system and the altimeter positioned at the static port and comparing them with each other, generating a response to the static port and / or altimeter status based on flight phase and comparison data.

2. A method according to claim 1, characterised in that the flight phase is taken as climbing and the altitude data obtained from the altimeter is greater than the altitude data obtained by the inertial reference system, the static port problem response is generated; if the altitude data obtained from the altimeter is less than the altitude data obtained by the inertial reference system, the altimeter problem response is generated; if the altitude data obtained from the altimeter is equal to the altitude data obtained by the inertial reference system, the non-issue response is generated.

3. A method according to claim 1, characterized in that; if the flight phase is taken as descent and the altitude data obtained from the altimeter is greater than the altitude data obtained by the inertial reference system, the altimeter problem response is generated; if the altitude data obtained from the altimeter is less than the altitude data obtained by the inertial reference system, the static port problem response is generated; if the altitude data obtained from the altimeter is equal to the altitude data obtained by the inertial reference system, the non-issue response is generated.

4. A method according to claim 1, characterized in that; if the flight phase is taken as level flight and the altitude data obtained from the altimeter is greater than the altitude data obtained by the inertial reference system, the altimeter problem response is generated, and if the altitude data obtained from the altimeter is less than the altitude data obtained by the inertial reference system, the altimeter problem response is generated, if the altitude dataobtained from the altimeter is equal to the altitude data obtained by the inertial reference system, the non-issue response is generated.

5. A data processing device comprising means for performing the steps of the method according to any one of claims 1-4.

6. A computer program comprising instructions that, when executed by a computer, cause the computer to perform the steps of the method according to any one of claims 1-4.

7. A computer-readable storage medium comprising instructions that, when executed by a computer, cause the computer to perform the steps of the method according to any one of claims 1-4.

Images