Aircraft overspeed alarm system and alarm method

Abstract

The invention relates to an aircraft overspeed alarm system and an alarm method, and the system comprises an alarm processing device, an atmosphere data system, an undercarriage control system, a flap control system and a signal alarm device which are mutually crosslinked, and the atmosphere data system sends the current indicated airspeed of an aircraft to the alarm processing device in real time; the undercarriage control system sends an undercarriage state signal to the alarm processing device in real time, the flap control system sends an airplane flap state signal to the alarm processing device in real time, and the alarm processing device judges the current configuration of an airplane according to the undercarriage state signal and the flap state signal. And the alarm processing device judges whether the aircraft is overspeed according to the current configuration and the current indicated airspeed of the aircraft, and sends an overspeed signal to the alarm device for overspeed alarm.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation instruments, and in particular relates to an aircraft overspeed warning system and a warning method. Background Art

[0002] As an important human-computer interaction system integrated into the aircraft cockpit, the warning system can monitor the status of various aircraft systems and provide warning information and its urgency to the crew to attract their attention, so as to take appropriate corrective or adjustment measures to improve the flight conditions of the aircraft. It plays an important role in helping the crew detect dangers in time and reduce flight accidents.

[0003] The core of the modern aircraft warning system is the warning processing device. The advanced warning processing device can automatically collect the sensor network data of the whole aircraft, process the collected data, form the original description of the abnormal situation through complex calculations, sort the collected fault and warning information according to the importance, and inform the crew. The notification methods usually include: 1) visual warning, which is displayed on the integrated display system through a simple diagram or text information; 2) auditory warning, which sends the warning information that has a greater impact on the safety of the aircraft (such as stall, autopilot disconnection, etc.) to the sound warning system in the form of discrete signal, so that it emits a corresponding warning sound; 3) light warning, which usually has two forms of light warning: red master warning light warning and yellow master warning light warning. Red indicates relatively important warning information that requires immediate action, and yellow indicates warning information that requires attention but does not need to be taken immediately; 4) tactile warning, such as the vibrator when the aircraft stalls. The warning system uses these means to remind the crew of the aircraft's status that affects flight safety, so that the crew can take corrective measures immediately or in advance.

[0004] If an aircraft is "overspeeding" during flight, it will cause various hazards to the aircraft: 1) The various parts of the aircraft structure are subjected to different forces during flight. Overspeeding will cause the forces on each part to exceed the designed load limit. Slight overspeeding may cause the aircraft to deform and damage the life of the aircraft. Severe overspeeding may even cause the aircraft to disintegrate in the air, endangering the lives of the crew. 2) Overspeeding will cause the pilot to bear too much load, causing a large amount of blood to rush to the brain and eyes, causing temporary blindness or causing the pilot to faint or go into shock. 3) In addition, due to different aerodynamic shape designs, the operating speed range of the aircraft is also different. The aircraft has an economic cruising speed. Overspeeding will greatly increase the fuel consumption rate of the aircraft and increase the operating cost of the aircraft.

[0005] Since overspeeding seriously endangers flight safety, it is extremely important to monitor and warn about overspeeding. Existing overspeeding warning devices for aircraft are relatively simple, and most of them only warn about overspeeding in cruising state, but cannot judge overspeeding under complex conditions, and the overspeeding warning form is relatively single. The present invention provides an overspeeding warning system and an alarm method, which can monitor the overspeeding state of an aircraft in different states and give multiple forms of alarms. Summary of the invention

[0006] The object of the present invention is to provide an overspeed warning system and a warning method which can be used for different aircraft forms.

[0007] An aircraft overspeed warning system comprises an interconnected warning processing device, an atmospheric data system, a landing gear control system, a flap control system and a signal warning device, wherein the atmospheric data system sends the current indicated airspeed of the aircraft to the warning processing device in real time, the landing gear control system sends the landing gear status signal to the warning processing device in real time, and the flap control system sends the aircraft flap status signal to the warning processing device in real time; the warning processing device determines the current configuration of the aircraft according to the landing gear status signal and the flap status signal; the warning processing device determines whether the aircraft is overspeeding according to the current configuration of the aircraft and the current indicated airspeed, and sends the overspeed signal to the warning device for overspeed warning.

[0008] The aircraft overspeed warning system is characterized in that the warning processing device is equipped with a built-in logic judgment software, and the maximum safe speeds corresponding to different configuration states of the aircraft are stored in the logic judgment software. The logic judgment software receives the aircraft landing gear status signal and the aircraft flap status signal in real time, judges the current configuration of the aircraft based on these signals, and determines the maximum safe speed of the aircraft corresponding to the current configuration of the aircraft. The logic judgment software compares the current aircraft indicated airspeed with the maximum safe speed of the aircraft corresponding to the current configuration of the aircraft to determine whether the aircraft is overspeeding.

[0009] The aircraft overspeed warning system is characterized in that the warning processing device is also interconnected with the aircraft's electronic flight instrument. The warning processing device sends the maximum safe speed of the aircraft's current configuration to the electronic flight instrument. The electronic flight instrument system makes a judgment based on the received maximum safe speed and the current indicated airspeed, and displays the overspeed trend and overspeed warning on the airspeed band of the primary flight display.

[0010] The aircraft overspeed warning system is characterized in that the warning signal device includes an audio warning device and a light warning device, the audio warning device receives the overspeed signal from the warning processing device and sends out an audio warning signal, and the light warning device receives the overspeed signal from the warning processing device and sends out a light warning signal.

[0011] An aircraft overspeed warning method, characterized by comprising the following contents: 1) an aircraft overspeed warning system as described in any one of claims 1 to 4 is arranged on an aircraft platform; 2) during the flight of the aircraft, an atmospheric data system sends the current indicated airspeed of the aircraft to an alarm processing device in real time, a landing gear control system sends a landing gear status signal to the alarm processing device in real time, and a flap control system sends an aircraft flap status signal to the alarm processing device in real time; 3) the alarm processing device determines the current configuration of the aircraft according to the landing gear status signal and the flap status signal; 4) the alarm processing device obtains the maximum safe speed corresponding to the current configuration of the aircraft according to the current configuration of the aircraft; 5) the alarm processing device sends the maximum safe speed corresponding to the current configuration of the aircraft to an electronic flight instrument, and the electronic flight instrument system makes a judgment based on the received maximum safe speed and the current indicated airspeed, and displays the overspeed trend and overspeed warning on the airspeed band of the primary flight display; 6) the alarm processing device judges whether the aircraft is overspeeding according to the maximum safe speed corresponding to the current configuration of the aircraft and the current indicated airspeed, and sends the overspeed signal to the alarm device for overspeed warning.

[0012] The invention is beneficial in that: by introducing the landing gear status signal, flap position signal, and indicated airspeed signal into the warning processing device, the warning processing device can determine the current configuration state of the aircraft; the warning processing device sends the maximum safe speed to the electronic flight instrument system according to the current configuration state, and the electronic flight instrument system performs logical judgment and performs an overspeed warning visual prompt on the main flight display; the warning processing device drives the light warning device (main warning light) to flash when the aircraft is overspeeding, so that the crew can get a more eye-catching light reminder; the warning processing device sends a discrete quantity signal to the sound warning device when the aircraft is overspeeding, and the sound warning device sends an overspeed warning sound. Through the invention, the crew can obtain various forms of overspeed warnings in various configuration states of the aircraft, so that the crew can discover the overspeed risk early, make corrections in advance, and reduce the occurrence of flight accidents. The invention does not need to add new equipment, the amount of aircraft modification is small, the airworthiness review is simple, and the capital cost and the time cost of civil aircraft airworthiness certification are greatly saved. The scheme proposed by the invention is reasonable and feasible, and has obtained airworthiness certification.

[0013] The present application is further described in detail below with reference to the accompanying drawings of the embodiments: BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the configuration of the aircraft overspeed warning system of the present application. DETAILED DESCRIPTION

[0015] As shown in the figure, the core of the overspeed warning system of the present application, which can be used for a variety of different aircraft forms, is a warning processing device, which is interconnected with the landing gear control system, flap control system, atmospheric data system, electronic flight instrument system, sound warning device and light warning device.

[0016] During flight, the warning processing device collects three landing gear uplock discrete signals, namely, the front landing gear uplock lock signal, the left landing gear uplock lock signal, and the right landing gear uplock lock signal, from the landing gear control system, collects the flap position signal from the flap control system, and collects the aircraft's indicated airspeed signal from the atmospheric data computer. The warning processing device makes a comprehensive judgment based on the collected landing gear retraction and extension status signal and flap position signal, determines the current aircraft configuration state, and outputs the maximum safe operating speed under the configuration to the electronic flight instrument system. The primary flight display of the electronic flight instrument system combines the current aircraft airspeed and displays the overspeed trend and overspeed visual warning on the speed scale of the primary flight display. Inside the warning processing device, a logical judgment is made in combination with the current aircraft airspeed. When the airspeed is greater than the maximum safe speed of the current configuration, a discrete signal is sent to drive the light warning device, i.e., the main warning light, to flash, and a discrete signal is sent to the sound warning device to make it issue an overspeed sound warning.

[0017] The present application will be further described below in conjunction with an example of a certain type of civil aircraft using this method to implement an overspeed warning function under various aircraft configurations:

[0018] In the warning system originally used by a certain type of aircraft, only the maximum operating speed VMO overspeed warning function is set in the cruising state, that is, when the aircraft airspeed reaches VMO, the primary flight display of the electronic flight instrument system displays an overspeed warning visual warning, the audio warning device emits an overspeed warning sound, and the main warning light warning when the overspeed condition is reached is missing. The maximum safe operating speed of the aircraft in other configuration states is only provided by the speed limit sign installed at the pilot, and there is a lack of visual warnings and audio warnings when the overspeed condition is reached.

[0019] The maximum safe operating speeds of the aircraft in different configurations are as follows: when the flaps are at 0°, the maximum operating speed VMO = 220kt; when the flaps are at 5°, the flap extended speed VFE = 167kt; when the flaps are at 15° or 30°, the flap extended speed VFE = 159kt; when the landing gear is retracted / extended, the landing gear extended speed VLO = 159kt; when the landing gear is lowered, the landing gear extended speed VLE = 159kt.

[0020] Based on the above requirements, the aircraft should implement the following overspeed warning functions: 1) When the aircraft speed reaches the maximum safe speed VMO in cruising state, a visual and audible overspeed warning should be provided to the pilot; 2) When the landing gear is retracted / extended, if the airspeed exceeds 159kt+4kt, a visual and audible overspeed warning should be provided to the pilot; 3) When the landing gear is extended, if the airspeed exceeds 159kt+4kt, a visual and audible overspeed warning should be provided to the pilot; 4) When the flap control switch is in the 5° position, if the airspeed exceeds 167kt+4kt, a visual and audible overspeed warning should be provided to the pilot; 5) When the flap control switch is in the 15° or 30° position, if the airspeed exceeds 159kt+4kt, a visual and audible overspeed warning should be provided to the pilot.

[0021] The maximum allowable safe operating speed of the aircraft's landing gear and flaps in different states is shown in Table 1:

[0022] Table 1

[0023]

[0024] From the analysis of Table 1, the maximum safe operating speed of the aircraft under different configurations can be divided into four states as shown in Table 2: Configuration state 1: flaps 0° and landing gear retracted and locked; Configuration state 2: landing gear retracted and locked and flaps set to 5° configuration state; Configuration state 3: when the landing gear is retracted and locked, since the VFE values ​​at flaps 15° and flaps 30° are both 159kt, this state is merged into the configuration state of landing gear retracted and locked and flaps set at 15° or 30°; Configuration state 4: since the VLO value and VLE value when the landing gear is retracted / extended and the landing gear is extended and locked are both 159kt in any flap position, this state is merged into the configuration state of "landing gear not in the up lock".

[0025] Table 2

[0026]

[0027]

[0028] Configuration 1 implementation plan, the maximum safe operating speed (VMO) warning function in the clean configuration has been implemented in the main flight display and the sound warning device. However, the warning processing device adds logic judgment to realize the flashing of the main warning light when overspeeding.

[0029] For implementation schemes of configuration 2, configuration 3, and configuration 4, the warning processing device collects the landing gear retraction and extension status signal and the flap position signal, and determines the current configuration of the aircraft based on this information. Then, the warning processing device transmits the maximum safe operating speed under this configuration state to the primary flight display through the ARINC429 digital bus. The primary flight display combines the current aircraft airspeed to display the overspeed trend and visual warning of overspeed on its speed scale. Inside the warning processing device, a logical judgment is made in combination with the current aircraft airspeed. When the airspeed is greater than the maximum safe operating speed under the current configuration state, the main warning light is driven to flash and a 28V discrete signal is output to the sound warning device to trigger the sound warning.

[0030] In the actual upgrade, the main changes made to this type of aircraft are: 1) The alarm processing device adds a line to collect the landing gear upper lock signal, a total of 3 28V / suspended discrete signals. 2) The alarm processing device adds a line to collect the flap control switch signal, a total of 28V / suspended discrete signals. 3) The alarm processing device adds a line to output a 28V / suspended overspeed warning discrete signal to the audio warning system. 4) The alarm processing device adds software logic judgment, uses the collected flaps and landing gear to make judgments, and outputs the maximum safe speed to the display through the bus. When the airspeed exceeds the maximum safe operating speed + 4kt, the 28V / suspended overspeed warning discrete signal is output and the main warning light is driven to flash. 5) When the airspeed exceeds VMO+4kt, the alarm processing device drives the main warning light to flash. 6) The main flight display only needs to change the internal software. The primary flight display receives the maximum allowable operating speed of the ARINC429 bus signal sent by the warning processing device. When the current airspeed exceeds the maximum allowable operating speed, the visual warning of the maximum allowable operating speed under this configuration appears on the speed scale of the primary flight display, and the display method is the same as the VMO warning display method. When the maximum allowable operating speed is 159kt, when the airspeed trend vector exceeds 159kt, the overspeed warning mark appears. At this time, the overspeed mark extends from the top of the airspeed tape downward to 159kt, and the airspeed reading turns yellow; when the current airspeed is greater than 159kt+4kt, the airspeed reading turns red. When the maximum safe operating speed is 167kt, when the airspeed trend vector exceeds 167kt, the overspeed warning mark appears. At this time, the overspeed mark extends from the top of the airspeed tape downward to 167kt, and the airspeed reading turns yellow; when the current airspeed is greater than 167kt+4kt, the airspeed reading turns red.

[0031] Finally, in accordance with CCAR-25-R4 "Airworthiness Standards for Transport Category Aircraft", the upgraded overspeed warning system was tested and airworthiness reviewed.

[0032] During the ground power-on inspection and air test flight, the improved aircraft can complete the expected overspeed warning function in different configurations of the landing gear and flaps during landing. When the aircraft reaches or exceeds the expected maximum safe operating speed in different configurations, the main flight display can display a maximum safe speed overspeed visual warning, while the main warning light flashes and the audio warning device emits an overspeed warning sound, providing visual, auditory and light warnings to the flight crew.

[0033] Through the implementation method of overspeed warning under various aircraft forms in the present application, the overspeed warning function under various different configuration states of the aircraft can be realized, and various forms of warnings such as visual warnings, audio warnings, and light warnings can be provided to the crew, effectively improving the man-machine efficiency and comfort of the aircraft, and gaining recognition from the airworthiness department and aircraft users.

Claims

1. An aircraft overspeed warning system, comprising an interconnected warning processing device, an air data system, a landing gear control system, a flap control system and a signal warning device, characterized in that: The atmospheric data system sends the current indicated airspeed of the aircraft to the alarm processing device in real time, the landing gear control system sends the landing gear status signal to the alarm processing device in real time, and the flap control system sends the aircraft flap status signal to the alarm processing device in real time. The alarm processing device determines the current configuration of the aircraft according to the landing gear status signal and the flap status signal. The alarm processing device determines whether the aircraft is overspeeding according to the current configuration of the aircraft and the current indicated airspeed, and sends the overspeed signal to the alarm device for overspeeding alarm.

2. The aircraft overspeed warning system according to claim 1, characterized in that: The alarm processing device is equipped with logic judgment software, which stores the maximum safe speeds corresponding to different configuration states of the aircraft. The logic judgment software receives the aircraft landing gear status signal and the aircraft flap status signal in real time, judges the current configuration of the aircraft based on these signals, and determines the maximum safe speed of the aircraft corresponding to the current configuration of the aircraft. The logic judgment software compares the current aircraft indicated airspeed with the maximum safe speed of the aircraft corresponding to the current configuration of the aircraft to determine whether the aircraft is speeding.

3. The aircraft overspeed warning system according to claim 1, characterized in that: The warning processing device is also interconnected with the aircraft's electronic flight instrument. The warning processing device sends the maximum safe speed of the aircraft's current configuration to the electronic flight instrument. The electronic flight instrument system makes a judgment based on the received maximum safe speed and the current indicated airspeed, and displays the overspeed trend and overspeed warning on the airspeed band of the primary flight display.

4. The aircraft overspeed warning system according to claim 1, characterized in that: The warning signal device comprises an audible warning device and a light warning device. The audible warning device receives the overspeed signal from the warning processing device and sends out an audible warning signal. The light warning device receives the overspeed signal from the warning processing device and sends out a light warning signal.

5. An aircraft overspeed warning method, characterized in that The invention comprises the following contents: 1) an aircraft overspeed warning system as described in any one of claims 1 to 4 is provided on an aircraft platform; 2) during the flight of the aircraft, the atmospheric data system sends the current indicated airspeed of the aircraft to the warning processing device in real time, the landing gear control system sends the landing gear status signal to the warning processing device in real time, and the flap control system sends the aircraft flap status signal to the warning processing device in real time; 3) the warning processing device determines the current configuration of the aircraft according to the landing gear status signal and the flap status signal; 4) The warning processing device obtains the maximum safe speed corresponding to the current configuration of the aircraft according to the current configuration of the aircraft; 5) The alarm processing device sends the maximum safe speed corresponding to the current configuration of the aircraft to the electronic flight instrument. The electronic flight instrument system makes a judgment based on the received maximum safe speed and the current indicated airspeed, and displays the overspeed trend and overspeed alarm on the airspeed band of the primary flight display. 6) The alarm processing device determines whether the aircraft is overspeeding based on the maximum safe speed corresponding to the current configuration of the aircraft and the current indicated airspeed, and sends the overspeed signal to the alarm device for overspeed alarm.

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