RU2461800C1 - Integrated system of backup devices - Google Patents

Abstract

FIELD: physics.

SUBSTANCE: integrated system of backup devices has an information sensor unit 1, an information processing unit 2, a display unit 3, a device 4 for changing frames, a device 5 for inputting pressure values, a converting device 6, two devices 7, 9 for controlling a converter 8 which converts the turning angle of a shaft to a digital code and a switching device 10. During takeoff and landing, the pilot selects frame display corresponding to the given flight conditions, and also enters the value of atmospheric pressure at the altitude of the takeoff strip of the aerodrome to determine the true flight altitude.

EFFECT: broader functional capabilities.

3 cl, 1 dwg

Description

The invention relates to measurement and display systems for piloting aircraft (L.A.) in the event of a failure of the main flight and navigation systems.

A known system of combined backup devices for aircraft [1], which provides information on the three main parameters necessary for the pilot of the aircraft in case of failure of the main devices, namely information about the instrument speed, barometric altitude and spatial position of the aircraft.

The disadvantage of this system is the limited information displayed on the indicator, which is necessary for flight safety in case of failure of the main flight and navigation systems.

A backup aircraft indication device [2] is also known, containing a set of information sources, an information processing unit, and an indication means.

The disadvantage of this device is that it displays the same frame during flight and during landing, which affects the convenience and accuracy of piloting. In addition, it is impossible to adjust the pressure at the take-off and landing points of L.A.

The problem to which this invention is directed, is to increase the convenience and accuracy of piloting.

The problem is solved due to the fact that in the integrated system of backup devices L.A., containing a series-connected block of information sensors, an information processing unit, an indication unit displaying information about the speed, altitude, course, spatial position of L.A., according to the invention additionally introduced a device for changing frames in the display unit for the flight L.A. and its landing and a device for entering the pressure value at the take-off and landing points L.A., connected to the information processing unit, the device for changing frames contains a conversion device connected to the first control device, and the device for entering the pressure value contains a rotation angle converter into a digital code connected to a second control device connected to the switching device.

A distinctive feature of the claimed system is the introduction of a device for changing frames in the display unit for the flight L.A. and its landing, containing a conversion device connected to the first control device, which allows you to change the image of the symbols on the display unit during flight and landing L.A. to increase the convenience and accuracy of piloting.

Another distinctive feature is the introduction of a device for entering the pressure value at LA take-off and landing points, which contains a rotation angle converter into a digital code connected to a second control device connected to a switching device, which allows, upon request from the airport controller, to enter the pressure value for calculating the relative flight altitude.

The drawing shows a diagram of a system that includes: information sensor unit 1, information processing unit 2, display unit 3, device 4 for changing frames, device 5 for inputting a pressure value, conversion device 6, first control device 7, rotation angle converter 8 into a digital code, a second control device 9, a switching device 10.

In the proposed system, the information sensor unit 1 is connected through the information processing unit 2 to the indication unit 3. In the device 4 for changing frames, the first control device 7 is connected via a conversion device 6 to the information processing unit 2. In the device 5 for inputting the pressure value, the switching device 10 is connected via a second control device 9 and a rotation angle converter 8 into a digital code connected in series to the information processing unit 2.

The claimed backup system operates as follows. Information about pressure, angular velocity, linear acceleration is sent from information sensors unit 1 to information processing unit 2, where information is converted for display unit 3, which displays information about speed, altitude, heading, and spatial position L.A.

Flight L.A. occurs in various modes, the main of which are flight and landing. During the flight L.A. the indicating unit 3 displays in the form of symbols, numerical and alphabetic banners the information necessary for piloting. When landing, the display of information is slightly different than during flight. In order that only information corresponding to the flight mode was present on the screen of the display unit 3, a frame change device 4 was introduced, which allows the pilot to select the desired frame. For this, the first control device 7 is displayed on the front panel of the display unit 3, which is a switch, which, through the conversion device 6, controls the information processing unit 2, which generates information for the display unit 3. The conversion device 6 is a binary code generator that varies depending on the switch position of the first control device 7.

When piloting L.A. One of the important parameters is the flight altitude, and when landing, this information is basic. Information about the height is formed by a barometric altimeter, the readings of which depend on the value of the relative pressure at the landing point of L.A. To take into account and compensate for changes in atmospheric pressure at the landing site L.A. the inventive backup system includes a device 5 for inputting the pressure value, which allows, according to the information of the dispatcher, to introduce an amendment and display the true height on the screen of the display unit 3. To compensate for the readings of the barometric altimeter, a switching device 10 is output to the front panel of the display unit 3, which, through the second control device 9, which is a code generator, controls the angle-code converter 8, which transfers the input information to the information processing unit 2 for display on the screen of the unit 3 Indications of the true flight altitude L.A. The backup system is designed as a separate unit. On the front panel there is a liquid crystal indicator of the display unit 3 with the control device 7 and the switching device 9. In the middle part there is an information processing unit 2 and an information sensor unit 1.

Information sources

1. US patent No. 6564628, IPC G01C 21/00, publ. May 20, 2003

2. RF patent No. 2350907, IPC G01C 23/00, publ. 03/27/09, (prototype).

Claims (3)

1. An integrated system of backup devices of the aircraft (L.A.), containing a series of information sensors, an information processing unit, an indication unit that displays information about the speed, altitude, course, spatial position of L.A., characterized in that she additionally introduced a device for changing frames in the display unit for the flight L.A. and its landing and a device for entering the pressure at the take-off and landing points of LA, connected to the information processing unit. 2. The integrated system of backup devices L.A. according to claim 1, characterized in that the device for changing frames in the display unit for the flight L.A. and its landing comprises a conversion device connected to the first control device. 3. The integrated system of backup devices L.A. according to claim 1, characterized in that the device for entering the pressure at the take-off and landing points L.A. comprises a rotation angle converter into a digital code connected to a second control device connected to the switching device.