RU2270141C2 - System selection panel - Google Patents

Abstract

FIELD: aircraft instrumentation engineering.

SUBSTANCE: proposed panel has micro-controller with permanent storage including recorded program, on-line storage and analog-to-digital converter. Energy-independent storage for storage of settings is connected with micro-controller through synchronous successful interface. Push buttons of sensor systems are connected to micro-controller input/output. Indicator of number of selected sensor-system is connected to micro-controller data busbar. Photo-sensors are connected to analog-to-digital converter of micro-controller. Provision is also made for interface part connected between micro-controller and display system for transmission and reception of messages by serial code.

EFFECT: enhanced safety of flights.

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Description

The invention relates to the field of aviation instrumentation. It can be used as a device to indicate the display system of an aircraft from which sensor system to take parameters for display. Controls the reception of data from the following systems:

BCC - airplane navigation computing system;

ANN - inertial navigation system;

SHS - air signal system;

ILS - meter landing system;

RV - radio altimeter;

DAU - aerodynamic angle sensor.

Allows you to force the display system to receive data only from the systems indicated by the pilot. This is done to block data from a faulty system.

Information about analogues with the same purpose as the remote control system selection could not be found.

The purpose of the invention is to improve flight safety.

On modern commercial aircraft always installed at least two of the same type of system, issuing aerobatic parameters. The electronic display system, taking flight parameters from sensor systems, compares the parameters with each other. If the discrepancy between the parameters is more than acceptable, then warnings about the unreliability of this parameter are displayed on the pilot indicators. Since the display system determines the operability of sensor systems by formal signs, it cannot always select and display the correct parameter value. For the indicator of the first pilot, one sensor system is assigned to the "main" one, and for the second - another. If the display system cannot determine: which of the sensor systems gives an incorrect value, then the value displayed by the "main" sensor system is displayed. Thus, in case of a malfunction, the correct value is displayed on the indicator of one of the pilots, and the wrong value is displayed on the indicator of the other. Flight safety is reduced, as one of the pilots does not have important flight parameters. Prior to the appearance of the system selection console, the pilot was not able to turn off the sensor system issuing an incorrect parameter value. Now the pilot, through the system selection console, indicates to the display system: from which of the same sensor systems to receive information. Other sensor systems are ignored by the display system. Thus, even if there remains one correctly working sensor system, the correct information from it is displayed on the indicators of both pilots, which facilitates the working conditions of the pilots and improves flight safety.

To minimize the depth of the remote control, the remote control is divided into two parts: front and interface.

The appearance of the front of the remote control is shown in figure 1. There are buttons on it: BCC; ANN; SHS; ILS; PB; DAU1; DAU2; ABT; +; -, indicator for sixteen familiarity and two photosensors. The "AUT" button is used to return to automatic operation mode, the "+" and "-" buttons adjust the brightness of the remote control indicator. The remaining buttons select the appropriate system. The overall dimensions of the front of the console are 64 × 146 × 43. The existing technologies today did not allow to place all the necessary equipment in these sizes. Therefore, the shaper of the sequential code according to GOST 18977-79 [1] is placed in the interface part. The interface part is a separate construct, to which two front parts are connected, and if necessary other devices can be connected. As a result of using this solution, it was possible to reduce the depth of the device (from the mating plane) from the usual 200 to 35 mm. Devices with such a small depth can be installed not only on the dashboard, but even on the inner casing between the power elements, i.e. the deficient internal volume of the cockpit is released.

The connection diagram of the remote control to the display system is shown in figure 2. The display system displays the navigation, flight and other parameters necessary for the pilot. The display system consists of several indicators (up to 5 pcs.), Of which two are shown - indicator 1 and 2, accepts and displays the parameters from the sensor systems 5, 6, 7. A system selector for systems 3 or 4 is connected to the indicators of each pilot. the remote control for selecting systems 3 and 4 does not interfere with the work, the indicators, in accordance with the built-in algorithm, themselves choose a working sensor system. If a malfunction is suspected, the pilot selects the sensor system by repeatedly pressing the desired button. For example, it presses BCC two times, thereby choosing that the display system receives parameters only from BCC2, ignoring the parameters from BCC1 and BCCZ. Above the BCC button, the number of the selected system "2" is displayed on the remote control indicator. The indicator software, having received the instruction from the system selection console, displays the parameters only from BCC2. To return to normal operation, the pilot presses the "AUT" button and the BCC button. That is, the system selection console does not switch the inputs of the display system, but only issues an indication: from which sensor systems should the parameters be considered correct. At the same time, the reliability of data transmission paths from sensor systems to the display system does not decrease, since the system selection console is not included in these paths. In the event of a failure of the system selection console, the display system will function normally.

Functional diagram of the front of the remote control is shown in figure 3. The remote control contains: 11 buttons, 12 remote control indicator (not included in the aircraft display system), 13 photosensors, 14 microcontroller, which includes nodes 15, 16, 17, 15 long-term memory, 16 random-access memory, 17 analog-to-digital converter, 18 non-volatile storage device, 19 power supply unit, 20 interface part, 21 input and output channels in accordance with GOST 18977-79. The buttons 11 are connected to the input ports of the output of the microcontroller 14. The indicator of the remote control 12 is connected to the data bus of the microcontroller 14. The photosensors are connected to the analog-to-digital converter 17, which is part of the microcontroller 14. The non-volatile storage device 18 is connected to the microcontroller 14 through a synchronous serial interface. The interface part is connected to the microcontroller 14.

Remote control operation. The microcontroller 14, under the control of a program recorded in the built-in long-term memory 15, continuously polls the buttons 11. If a button is found, the number of the selected system is displayed on the indicator of the remote control 12. The microcontroller 14 through the interface part 20 with a code sequential in accordance with GOST 18977-79, transmits an indication to the display system to indicate the parameters from the selected sensor system. Non-volatile memory device 19 stores personal settings, for example, the set brightness of the indicator and information about failures detected by self-monitoring. Received and transmitted information is placed in a specially allocated area of RAM 16. The required brightness of the indicator of the remote control 12 is set using the "+" and "-" buttons. The signal from the photosensor 13 increases or decreases the brightness of the indicator depending on the ambient lighting. Two photosensors are installed to compare their values with each other in order to detect malfunctions of the photosensors. The power supply 19 converts the on-board network 27 V into 5 V secondary power. The microcontroller 14 transmits and receives data to and from the display system through the interface part 20. The interface part 20 issues and receives messages in a code consistent with GOST 18977-79. The input and output channels 21 are connected by plane to the display system.

At present, a working model of the system selection panel has been manufactured. The performance of the selected technical solutions has been demonstrated to the customer. Debugging software is in progress. The remote control is being developed for the modernized TU-214 aircraft display system.

Literature

1. GOST 18977-79 Complexes of airborne equipment for aircraft and helicopters. Types of functional connections, types and levels of electrical signals. Moscow. USSR State Committee for Standards. 1979 year

Claims (1)

Remote control for selecting sensor systems for an aircraft parameter display system, including a microcontroller with long-term memory, including a recorded program, random-access memory and an analog-to-digital converter, non-volatile memory settings, connected to the microcontroller via a synchronous serial interface, push-buttons of sensor systems connected to the input / output ports of the microcontroller, the indicator number of the selected sensor system, connected th to the data bus of the microcontroller, photo sensors, connected to the analog-to-digital converter of the microcontroller and connected between the microcontroller and display system interface portion adapted to transmit and receive messages serial code.

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