Aircraft fire detection and fault isolation system and method

Abstract

The present invention belongs to the technical field of aircraft electromechanical integrated design, and specifically relates to an aircraft fire detection and fault isolation system and method. The system includes a plurality of fire detectors and a fire detection box. The fire detection box includes a self-test module, an isolation module, an alarm module, a judgment module and an isolation switch. The isolation module is internally provided with a plurality of isolation devices. The number of the isolation devices is the same as the number of the fire detectors and they are connected one-to-one. The isolation module is connected to the judgment module via the isolation switch, the judgment module is connected to the self-test module, and the self-test module is respectively connected to the isolation module and the alarm module. When a fire alarm occurs in the aircraft engine compartment, it can be determined whether the alarm is a false alarm or a real alarm by reading engine parameters and other methods, and fault isolation can be performed.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft electromechanical integrated design, and in particular relates to an aircraft fire detection and fault isolation system and method. Background Art

[0002] The aircraft fire detection system is an important component of the aircraft's electromechanical integrated system. Currently, the design of fire detection systems for aircraft both domestically and internationally has matured. Most fire detection systems use thermal detectors or light detectors in conjunction with fire detection boxes. While these two types of detectors have their own advantages and disadvantages, neither can avoid the problem of excessively high false alarm rates in complex operating environments.

[0003] When a fire alarm sounds in the aircraft's engine compartment, it can be determined whether the alarm is a false alarm or a real alarm through various methods such as reading engine parameters. However, since fault isolation is impossible, even if the pilot determines that the alarm is a false alarm, in order to prevent missing the real alarm during subsequent flights, the current mission must be aborted and returned, resulting in mission failure. Summary of the Invention

[0004] The purpose of the present invention is to provide an aircraft fire detection and fault isolation system and method to solve the problems existing in the background technology.

[0005] The technical solution of the present invention:

[0006] An aircraft fire detection and fault isolation system includes several fire detectors and a fire detection box. The fire detection box includes a self-test module, an isolation module, an alarm module, a decision module and an isolation switch. The isolation module is internally provided with several isolation devices, the number of which is the same as the number of fire detectors and is connected one-to-one. The isolation module is connected to the decision module via the isolation switch, the decision module is connected to the self-test module, and the self-test module is respectively connected to the isolation module and the alarm module.

[0007] Preferably, the plurality of fire detectors are connected in parallel to the alarm module of the fire detection box.

[0008] Preferably, the isolation module is a relay.

[0009] The invention relates to an aircraft fire detection system and a fault isolation system method. When a self-check module detects a circuit fault in one and only one fire detector, an isolation module automatically isolates the faulty fire detector.

[0010] Preferably, when the alarm module detects that one and only one fire alarm detector is alarming, the alarm module controls the isolation switch to turn on, and the judgment module makes a judgment based on the engine parameters sent by the received host. If the fire alarm detector is judged to be a false alarm, a signal is output to the isolation module, and the isolation module automatically isolates the alarm fire detector.

[0011] Preferably, the engine parameter sent by the host is engine temperature.

[0012] Preferably, when the self-check module detects circuit failures in two or more fire detectors, all isolation devices in the isolation module remain connected and the alarm module issues an alarm.

[0013] Preferably, when the alarm module detects alarms from two or more fire detectors, all isolation devices in the isolation module remain connected and the alarm module issues an alarm.

[0014] Beneficial effects of the present invention: The present invention provides an aircraft fire detection and fault isolation system and method. When a fire alarm occurs in the aircraft engine compartment, it is possible to determine whether the alarm is a false alarm or a real alarm by reading engine parameters and other methods, and to perform fault isolation. Even if the pilot determines that the alarm is a false alarm, the fault can be isolated in time, and the current mission can be returned without terminating. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is the structural schematic diagram of the aircraft fire detection and fault isolation system. DETAILED DESCRIPTION

[0016] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0017] like Figure 1As shown, the present invention provides an aircraft fire detection and fault isolation system, comprising a plurality of fire detectors numbered from !# to n#. The fire detectors are installed in corresponding positions in the engine compartment to monitor fire conditions at different locations in the engine compartment. The system also includes a fire detection box for determining the fire condition in the engine compartment based on the fire detector status and taking appropriate measures. The internal structure of the fire detection box includes a self-test module, an isolation module, an alarm module, a decision module, and an isolation switch. The isolation module is internally provided with a plurality of isolation devices, the number of which is the same as the number of fire detectors and connected in a one-to-one correspondence. The isolation devices can be electrical components such as isolation switches and circuit breakers. The isolation module is connected to the decision module via the isolation switch, the decision module is connected to the self-test module (BIT), and the self-test module (BIT) is connected to the isolation module and the alarm module, respectively.

[0018] in,

[0019] The self-test module is used to implement power-on self-test and periodic self-test of the fire alarm detection box, including line faults, etc.

[0020] The alarm module is used to receive fire alarm information;

[0021] The judgment module is used to automatically judge between false alarms and real alarms;

[0022] The isolation module is used to achieve physical isolation between the fire detector and the fire detection box;

[0023] In the present invention, the several fire detectors are connected to the alarm module of the fire detection box in parallel. The lines between the fire detectors are independent and do not affect each other. This can ensure that when any fire detector fails or a real fire occurs, the faulty fire detector or the real engine compartment fire position can be accurately located.

[0024] In the present invention, the isolation module is a relay, which operates more intelligently and quickly, and can ensure that when a real fire occurs, the fire detector and the fire detection box are quickly physically isolated.

[0025] The method of using the aircraft fire detection and fault isolation system of the present invention is as follows:

[0026] (1) When the self-test module detects that one and only one fire detector circuit is faulty, the isolation module automatically isolates the faulty fire detector. The specific operation is as follows: when the alarm module detects that one and only one fire detector is alarming, the alarm module controls the isolation switch to be turned on, and the judgment module makes a judgment based on the engine parameters sent by the host. If the fire detector is judged to be a false alarm, a signal is output to the isolation module, and the isolation module automatically isolates the alarm fire detector.

[0027] (2) When the self-check module detects that two or more fire detector circuits are faulty, all isolation devices in the isolation module remain connected and the alarm module issues an alarm.

[0028] (3) When the alarm module detects that two or more fire detectors are giving alarms, all the isolation devices in the isolation module remain connected and the alarm module gives an alarm.

[0029] In the present invention, the engine parameter sent by the host is the engine temperature. The temperature signal reflects whether there is a fire in the engine compartment, so the temperature signal is used to represent the actual fire situation.

[0030] Therefore, when a fire alarm occurs in the aircraft engine compartment, it is possible to determine whether the alarm is a false alarm or a real alarm through various methods such as reading engine parameters, and to isolate the fault. Even if the pilot determines that the alarm is a false alarm, the fault can be isolated in time and the current mission can be returned without aborting.

[0031] The above description is merely a detailed description of specific embodiments of the present invention. Any unspecified portions are conventional techniques. However, the scope of the present invention is not limited thereto. Any changes or substitutions that can be readily conceived by a person skilled in the art within the technical scope disclosed in the present invention are intended to be encompassed within the scope of the present invention. The scope of the present invention shall be determined by the scope of the claims.

Claims

1. An aircraft fire detection and fault isolation system, comprising a plurality of fire detectors, characterized in that: It also includes a fire alarm detection box, which includes a self-test module, an isolation module, an alarm module, a judgment module and an isolation switch. A number of isolation devices are arranged inside the isolation module. The number of the isolation devices is the same as the number of fire detectors and they are connected one-to-one. The isolation module is connected to the judgment module through the isolation switch, the judgment module is connected to the self-test module, and the self-test module is connected to the isolation module and the alarm module respectively; when the self-test module detects that one and only one fire alarm detector line fault occurs, the isolation module automatically isolates the faulty fire alarm detector, that is, when the alarm module detects that one and only one fire alarm detector alarms, the alarm module controls the isolation switch to turn on, and the judgment module makes a judgment based on the engine parameters sent by the received host. If the fire alarm detector is judged to be a false alarm, a signal is output to the isolation module, and the isolation module automatically isolates the alarm fire alarm detector.

2. The aircraft fire detection and fault isolation system according to claim 1, characterized in that: The plurality of fire detectors are connected in parallel to the alarm module of the fire detection box.

3. The aircraft fire detection and fault isolation system according to claim 1, characterized in that: The isolation module is a relay.

4. The aircraft fire detection and fault isolation system according to claim 1, characterized in that: The engine parameter sent by the host is the engine temperature.

5. The aircraft fire detection and fault isolation system according to claim 1, characterized in that: When the self-check module detects that two or more fire detector circuits are faulty, all isolation devices in the isolation module remain connected and the alarm module issues an alarm.

6. The aircraft fire detection and fault isolation system according to claim 5, characterized in that: When the alarm module detects that two or more fire detectors are giving alarms, all the isolation devices in the isolation module remain connected and the alarm module gives an alarm.

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