KR101212218B1 - Flight monitoring apparatus for aircraft, separation method of sensor trouble, and flight alarm monitoring method - Google Patents

Abstract

PURPOSE: A flight simulation system for an aircraft, a method for separating a malfunctioned sensor thereof, and an altitude flight alarm simulation method for the aircraft can efficiently provide vital flight data on the flight and navigation of an aircraft to a pilot. CONSTITUTION: A flight simulation system for an aircraft comprises a first sensor device(131), a second sensor device(132), a first automatic flight device, a second automatic flight device, first task computer(121), a second task computer(122), a fist simulation part, a second simulation part, an independent gauge, and a selection switch. When one of the first and second sensor devices is normally operated, the other one is operated in a backup mode. The first and second automatic flight devices make an aircraft automatically fly based on signals detected from the first or second sensor device. The first and second task computers control one of the first and second automatic flight devices with the signals detected from the first or second sensor device. The first simulation part simulates information on the first sensor device and the first automatic flight device. The second simulation part simulates information on the second sensor device and a second automatic flight device. The independent gauge displays flight information which is independent to the first and second sensor devices. The selection switch is operated to ignore the signals transmitted from one of the sensor devices exceeding a predetermined threshold valve.

Description

How to isolate the sensor faults of the aircraft's flight essential display system, the aircraft's flight essential display system and how to display the aircraft altitude flight warning {FLIGHT MONITORING APPARATUS FOR AIRCRAFT, SEPARATION METHOD OF SENSOR TROUBLE, AND FLIGHT ALARM MONITORING METHOD}

The present invention relates to a display device for transmitting information to an aircraft pilot, a method of demonstrating a flight instrument to deliver the sensor (ADC, AHRS, GPS / INS, RALT, VOR / ILS) information of the aircraft to the pilot, two The present invention relates to a method of controlling dual sensor data in four display devices that transmit information to a pilot, a method of displaying an automatic flight mode state, and a flight warning method according to an altitude.

The method of converting independent analog instruments, such as altitude, speed, attitude and nose, which are essential for flight instrument flight, to electronic instruments, respectively. (10-2009-0117182, 10-2009-0117185) It electronically converts each instrument to provide individual functionality, but integrates and processes data from one or more sensor units installed in a dual structure and provides a pilot with a multi-structure display. There is a need for a method of efficiently communicating information. In addition, to improve aircraft safety, the integrated data processing unit manages dual structure sensor data and responds to failures, and an effective way to provide pilots with autopilot mode information in conjunction with autopilot signals is a fast situational awareness and Required for proper response maneuvers.

The present invention provides a management state by interworking with a dual structure autopilot control signal and processing one or more dual structure sensor device signals to solve the problems of the above technology and isolating a failure in the event of a failure in the sensor device. To provide. In addition, an object of the present invention is to provide a flight essential display device for an aircraft including flight essential information (posture, speed, altitude, ascent rate, nose) display, flight status display and flight altitude warning display.

Flight essential display device for an aircraft according to an embodiment of the present invention for achieving the above object of the present invention means to display the sensor information of the aircraft, aircraft sensor fault separation control means, flight essential instrument display means, aircraft height Flight warning display means, aircraft autopilot mode status display means.

In addition, according to another embodiment of the present invention, the flight essential display device for aircraft integrated processing of the automatic flight control device operating in a dual structure, at least one dual structure sensor device, dual structure automatic flight control device and sensor device data The mode may be changed using a dual structure mission computer, a switch for selectively applying a dual structure automatic flight control device and a sensor device, and a switch including one or more aircraft control and display devices.

On the other hand, the above object according to an embodiment of the present invention, the display of the sensor information of the aircraft, the step of outputting the graphics to the four display devices in each of the two data integrated processing device, and one or more dual structure Connecting the sensor device data to the two data integrated processing devices via a data bus, and connecting a switch for selectively using the sensor data to the data integrated processing device, and interworking with each other. Disclosed are a method of dividing one or more sensor device data into two groups of essential flight display devices, each of which is performed when a data integrated processing unit operates normally and a single data integrated processing unit operates in a backup mode.

According to an example related to the present invention, the aircraft sensor fault separation control is a dual structure data integrated processing device uses a data communication in a structure in which one or more sensor device data is divided into two groups of essential flight display devices. Comparing the sensor data and determining a sensor failure when the threshold value is exceeded; Identifying failures in such a way as to flash colors and boxes indicating failure warnings on the flight instrument using the data of the sensor using colors; Determining a failed sensor among the dual structured sensor data by comparing a pilot independent comparable instrument data with sensor data separately displayed as in claim 3; Manipulating a switch for selecting sensor data to separate the failed sensor data from the data representation; Disclosed is a control method of isolating a sensor failure in a manner including a.

According to an example related to the present invention, the flight essential instrument display, the aircraft world to indicate the aircraft pitch, roll displacement; A circular horizontal status clock indicating the aircraft nose, air route point direction and course by numbers, the circular compass turning and indicating the nose and direction by arrows; A speedometer in which the aircraft speed is represented numerically and the scale of the tape measure is changed; An altimeter that indicates the aircraft's altitude numerically and changes the scale in a tape measure; An indicator needle with a number indicating an aircraft ascent rate / descent rate and having a pointer that moves a fixed scale; A radar altitude clock with a bar shape that is varied according to the aircraft's surface altitude and the scale is fixed; Disclosed is a flight essential instrument display method comprising a.

According to an example related to the present invention, the radar altitude clock using two types of instruments varying the range of the instrument according to the surface elevation; A radar altitude clock that uses altitude in a certain area as a hysteresis section at the surface altitude where two types of instruments change; A speedometer using a speed of a predetermined area as a hysteresis section at a speed in which the aircraft speed is indicated by a number; Disclosed is a flight essential instrument display method comprising a.

According to an embodiment related to the present invention, the flight warning display according to the aircraft altitude, the step of setting the aircraft high altitude warning value using a switch; Setting an aircraft low altitude warning value using a switch; Determining whether the aircraft is in flight or waiting to fly on the ground; Determining a low altitude warning indication when the aircraft altitude rises above the low altitude warning value and then falls below the low altitude warning value with reference to the sensor data; The aircraft flying above the high altitude warning value to determine the high altitude warning display; Flashing a warning value for the low altitude warning and the high altitude warning and providing a voice warning; Disclosed is a method for displaying an aircraft altitude flight warning operating in a manner including.

According to an embodiment related to the present invention, the aircraft automatic flight mode state display, consisting of two rows and three columns on the center top of the aircraft flight essential display device, divided by three columns of collective axis, roll / yaw axis, pitch axis information; Automatic flight active (Armed) mode, in which the automatic flight is not immediately applied and is in preparation, is shown in two rows; Engaged mode, controlled simultaneously with maneuvering the aircraft, is shown in one row; Demonstration of the automatic flight mode setting applied to the flight essential instrument in conjunction with the flight essential instrument; Disclosed is an automatic flight mode presentation method comprising the steps of:

When applying the flight essential display device for the aircraft according to the present invention to the cockpit, it is possible to efficiently provide the flight essential data such as flight and navigation to the pilot.

It is especially useful for aircraft that need to provide information to pilots by processing one or more dual sensor devices and autopilot signals using a mission computer, a dual-structure integrated data processing device, to ensure the flight safety of the aircraft. .

It is expected to reduce the pilot's workload and improve flight awareness by using the flight altitude warning function and the automatic flight mode entry and automatic flight mode status display technology.

FIG. 1 is a conceptual diagram illustrating four essential flight display devices capable of identifying and separating faults in conjunction with an automatic flight control device and a sensor device in which two mission computers, which are data integrated processing devices, operate in a dual structure.
2 is a conceptual diagram showing an instrument arrangement form of the flight essential display device for an aircraft.
3 is a conceptual diagram in which two types of instruments used in the radar altitude indicator are selectively displayed according to the altitude.
4 is a conceptual diagram showing the automatic flight mode state of the flight essential display device for an aircraft.

In order to improve the flight safety of the aircraft, a dual structured automatic flight control system and a dual structure sensor device are used, and the reliability of the system is increased by using two mission computers, which integrate various types of data.

As shown in FIG. 1, a fault separation technique is required in which the data of devices interoperating with each other in a dual structure are integrated and managed to identify a failure when one sensor data fails and to remove the defective sensor from the flight essential display device. Since the data used for the same purpose are doubled, we devised a technique to identify whether the sensor device has a failure or, if a failure occurs, which sensor device data is the failure so as not to use the data. In order to check whether there is a failure and to remove the failure sensor in the signal interworking process so that it cannot be used in the flight essential display device for aircraft, the dual structure sensor data is separated and displayed in four essential flight display devices.

In a double seated aircraft, two pilots each use two visual devices.

Thus, the flight essential display devices 111 and 112 display the sensor device 131 and the automatic flight control device 132 data, and the flight essential display devices 113 and 114 display the sensor device 134 and the automatic flight control device 135 data.

Compare flight instrument data (pitch, roll, yaw, speed, altitude, ascent rate) displayed on the flight essential display device for aircraft to blink the fault symbol when the above threshold is exceeded To identify sensor failures.

In order to isolate the fault, the instrument panel indicating the attitude, nose, speed, altitude, and rate of climb are completely installed in the cockpit instrument panel. A selection switch 133 for excluding a defective sensor from the dual structure sensor device data and instructing the use of a normal sensor is installed. If a fault symbol indicating a sensor failure is blinking on the flight essential display device, the pilot identifies the fault and compares the sensor device data 131, 134 and the independent instrument data 115 with the independent instrument data to isolate the fault. It will recognize the sensor device with a big difference. The pilot operates the sensor selector switch to point to a number representing the normal sensor and uses the normal sensor data for the four flight essential display units without displaying the faulty sensor device data. Data used in the flight essential display device according to the operation of the sensor device selection switch 133 for fault separation is shown in the table below.

The flight mandatory instrument of the flight mandatory display device for the aircraft consists of the pilot world, horizontal status watch, speedometer, altimeter, and radar altitude watch.The instrument type and optimal instrument layout are needed to provide the pilot with quick flight information and situation recognition. Devise Figure 2.

The mandatory flight gauge used in Figure 2 is used in the form of a rod, a tape measure and a circular gauge, the aircraft world 212 indicating the aircraft pitch, roll displacement, a speedometer that indicates the aircraft speed numerically and the scale of the tape measure changes (211), an altimeter (213) for indicating the aircraft barometric altitude numerically and the scale of the tape measure is changed, a number indicating the aircraft ascent rate and descent rate is displayed, and an ascending meter (214) having an indication needle for moving a fixed scale, The radar altitude indicator (215), the aircraft's nose, route point bearing, and course of which the bar shape is changed and the scale is fixed according to the aircraft's surface altitude, the circular compass is rotated, and the nose and the bearing are indicated by the arrows. A circular horizontal status clock 216 and the like are displayed together with the engine related information 217 and the navigation / communication information 218. The automatic flight mode information 219 is disposed at the top of the center, and provides a flight essential display device for an aircraft configured as shown in FIG. 2, the flight essential instrument, engine information, navigation / communication information, and automatic flight mode information described above.

The radar altitude clock of the flight essential display device for an aircraft provides a method of displaying by using two types of instruments varying the range of the instrument according to the surface altitude as shown in FIG. The radar altitude watch uses a high altitude range (0 to 200 feet) and a high altitude range of 200 feet or more to measure the overall range (0 to 2000 feet), so it is possible to increase resolution at low altitudes requiring attention to aircraft safety. This allows the pilot to quickly identify the exact altitude change. And at more than 2000 feet without affecting safety, the radar altitude clock is not visible. The use of two types of gauges causes frequent changes in the altitude due to airflow while the aircraft is flying in the critical section where the two gauges intersect, causing frequent fatigue for the pilots. As a way to prevent this, the hysteresis section is set at 190 to 200 feet and 1900 to 2000 feet to maintain the previous form without changing the instrument type when the aircraft altitude is in the hysteresis section. An example of the change in instrument type with altitude is shown below.

How to display two types of radar altitude indicators selectively or not according to the surface altitude, how to use a certain area as a hysteresis section near the threshold at which two instruments change, and a certain area at the speed of numerical display of aircraft speed To provide an essential flight display device for an aircraft employing a speedometer display method using the speed as a hysteresis section.

The flight warning display according to the aircraft altitude of the flight essential display device for the aircraft is applied to the radar altitude indicator and barometric altimeter indicating the surface altitude, and instructs the pilot the aircraft status according to the altitude change. In addition, flight warnings based on aircraft altitude apply separately to low and high altitudes.

The flight warning based on the aircraft altitude is determined by setting the aircraft low altitude warning value using a switch and determining whether the aircraft is in flight or waiting to fly on the ground. When lowered below, the low altitude setting value 331 or 332 of FIG. 3 flashes in red to display a low altitude warning, and a voice warning is provided to the pilot. In case of the high altitude warning, when the aircraft flies above the high altitude warning setting value, the altitude setting value 321 or 322 of FIG. 3 is blinked in yellow, and a voice warning is provided to the pilot. It provides a flight essential display device for aircraft having a low altitude flight warning and high altitude flight warning function.

The flight essential display device for the aircraft automatic flight mode display is located in the upper center 219 in FIG. 2 and composed of two rows and three columns as shown in FIG. 4 to display the collective axis information in the 411, 421, the roll, yaw and yaw axis information 412, It is implemented by displaying at 422 and pitch axis information at 413 and 423. Changes to auto flight mode, change of auto flight mode setting value, deviation from auto flight mode and trim mismatch for each axis of collective, roll / pitch and pitch are as follows.

Armed mode, which is not ready for automatic flight mode and is ready, is displayed in Cyan on two rows (421, 422, 423), and Engaged mode is controlled at the same time as pilot operation. It is shown in green in rows 411, 412, 413. If auto flight mode is associated with a flight essential instrument, the applied auto flight mode settings are displayed adjacent to the gauge, and the set symbol (Bug) is superimposed on the flight essential gauge in the same color as the auto flight mode demonstration in the flight essential gauge scale. It provides a flight essential display device for an aircraft comprising a method.

111: flight essential display device for aircraft screen 1
112: flight essential display device for aircraft screen 2
113: essential flight display device 3 aircraft
114: essential flight display device for aircraft 4
115: Independent instrument used for comparison of flight essential data
121: mission computer 1
122: mission computer 2 as an integrated data processing unit
131: dual structure sensor device 1
132: dual structure sensor device 2
133: sensor device selection switch
134: dual structure automatic flight control device 1
135: dual structure autopilot 2
211: speedometer
212: flight essential display device
213: mandatory display pressure barometer
214: flight essential display system
215: Radar Elevation Clock
216: flight essential display device horizontal status clock
217: essential flight engine information
218: flight essential display navigation / communication information
219: flight essential display device automatic flight mode information
301: Radar High Altitude Clock for Low Altitude
302: Radar altitude clock
311: Low altitude meter surface altitude indication value
312: Indicator indicator for all parts
321: Low altitude meter high altitude warning setting
322: All-in-one instrument high altitude warning setpoint
331: Low altitude meter low altitude warning setpoint
332: all-in-one meter low altitude warning setpoint
411: Collective Axis Engaged Mode
412: Roll / Yaw Axis Engaged Mode
413: Pitch Axis Activated Mode
421: Collective axis active mode
422: Rolled / Yaw axis active (Armed) mode
423: Pitch axis active mode

Claims (7)

In the aircraft's vision system for presenting information related to flight to the coordinator,
When one of the devices operates normally, the other device includes a first and a second sensor device formed in a dual structure to operate in the backup mode;
First and second automatic flight devices formed in the dual structure and configured to automatically fly an aircraft based on a signal detected from the first or second sensor device;
The dual structure is connected to the sensor devices and the automatic flight devices so as to receive a signal sensed by the first or second sensor device to control any one of the first or second automatic flight devices. First and second mission computers;
A first viewer configured to display information of the first sensor device and the first automatic flight device;
A second viewer configured to display information of the second sensor device and the second automatic flight device;
An independent instrument for displaying information related to flight independently of the first and second sensor devices; And
And a selector switch operable to ignore a signal transmitted from any one sensor device exceeding a preset threshold compared to the independent instrument. The method of claim 1,
If the signal of the sensor devices exceeds a predetermined threshold value from the information displayed on the independent instrument, the flight essential display system of the aircraft, characterized in that a fault symbol corresponding to the failure is displayed on the first or second display. The method of claim 2,
The first and second mission computer,
And a data integrated processing device connected to the sensor devices and the automatic flight devices to process information, respectively.
And the data integration processing device is configured to be connected to the selection switch and the display parts to output signals from the sensor devices through the display parts. The method of claim 1,
The independent instrument,
A pilot world indicative of the pitch and roll displacement of the aircraft;
A circular horizontal status clock indicating the aircraft nose, air route point direction and course by numbers, the circular compass turning and indicating the nose and direction by arrows;
A speedometer in which the aircraft speed is represented numerically and the scale of the tape measure is changed;
An altimeter that indicates the aircraft's altitude numerically and changes the scale in a tape measure;
An ascending system having an indicator needle for displaying a figure indicating an aircraft ascent or descent rate and moving a fixed scale; And
The flight essential display system of the aircraft, characterized in that it comprises a radar altitude altitude watch of the bar shape is changed according to the aircraft surface altitude and the scale is fixed. 5. The method of claim 4,
The independent instrument,
Radar altitude clocks that use two types of gauges with varying ranges of instruments depending on surface altitude;
A radar altitude clock that uses altitude in a certain area as a hysteresis section at the surface altitude where two types of instruments change; And
The flight essential display system of the aircraft further comprises a speedometer that uses the speed of a certain area as a hysteresis section at the speed indicated by the number of aircraft speed. In the sensor fault isolation method of the flight essential display system of the aircraft according to claim 3 to present information related to the flight to the coordinator,
Determining, by the data integration processing device, that a sensor failure occurs when a predetermined threshold value is exceeded by comparing the signals of the sensor devices with information displayed on the independent instrument using data communication;
When determined to be a failure, flashing a failure warning through a display unit connected to a failed sensor among the display units; And
When the selection switch is operated, separating a signal input from the failed sensor so that the signal is not displayed through the flashing display unit. In the aircraft altitude flight warning display method of the flight essential display system of the aircraft according to claim 3 to provide information related to the flight to the pilot,
Setting high and low altitude warning values of the aircraft;
When the aircraft altitude received from the sensor devices rises above the low altitude warning value and then falls below the low altitude warning value, or when the aircraft altitude rises above the high altitude, the data integration processing device raises the altitude of the aircraft to the low altitude warning or high altitude. Judging by a warning; And
And displaying predetermined information about the low altitude warning or the high altitude warning through at least one of the display units, and outputting a voice warning if it is determined to be a warning.

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