RU58236U1 - INFORMATION AND TEAM SYSTEM OF AIRCRAFT - Google Patents

Abstract

The utility model relates to the field of aeronautical engineering and can be used to create promising aircraft (LA) as the main or backup means of eliminating emergency and emergency situations, which practically eliminate crew errors when working with cockpit instrumentation in special flight situations. The information-command system contains three wide-screen multi-channel liquid crystal indicators, which display all the information about the operation of the aircraft systems, an indication generation unit, electrically connected to the control signal generation module, the search and recommendation module and the data comparison module, which is connected to the aircraft navigation system calculator and with the air signal system, the on-board test control system associated with the control signal generation module and the logic generation module commands, engine control levers, pedals, side control knobs with four-position push buttons with neutral buttons installed in the workplaces of the commander and co-pilot, and a voice informant. In addition, the system includes an emergency command system unit mounted on the upper panel of the cockpit, containing a manual control module with push-button lamps with feedback, which provide control signals to the actuators of the units of the aircraft systems, and a switch module for actuators, four-position push buttons with neutral buttons located on the side control knobs are connected to both modules of the emergency command unit for manual control of this system. The presented technical solution of the information-command system of the aircraft allows: - to reduce the time for detection, recognition and liquidation of an emergency or emergency; - significantly reduce the load on the crew in the process of eliminating the phenomenon; - virtually eliminate the probability of pilot error when working with instrumentation in the process of eliminating an emergency or emergency. Using the materials of this utility model, research work was carried out on aerobatic stands, algorithms for the interaction of the system’s components with the actuators of aircraft and propulsion units were worked out, and results were obtained confirming the technical and economic efficiency of the utility model. Illustrations - 5 FIG. on 3 sheets.

Description

The utility model relates to the field of aviation technology and can find application in the creation of promising aircraft as the main or backup means of eliminating emergency and emergency situations, which practically exclude crew errors when working with cabin instrumentation in special flight situations.

On the upper panels of the cockpit of aircraft of previous generations compactly located almost all communications control systems of the aircraft and engines, placed in a strictly defined order. In case of emergency situations, the crew has to carry out control actions to eliminate the phenomenon, referring to the control panels of various systems located throughout the entire area of the upper dashboard and other remote controls of the pilot's cabin, which does not exclude the possibility of erroneous actions in working with the instrumentation of the cabin in stressful situations and adversely affects flight safety.

The use of emergency control cards available on board the aircraft does not reduce the load of pilots, since the time (15 seconds) allocated by Aviation Rules-25 (AP-25) for recognizing a phenomenon, getting emergency control cards, finding the right section and performing the necessary operations is not enough [one].

On a modern airliner IL-96-300, this drawback is partially eliminated due to the fact that in the case of an emergency situation, prompts are issued from the corresponding section of the manual for flight operation of the aircraft (RLE). But this measure does not exclude the possibility of a crew error for the reason indicated above [2].

The well-known "Information-command system of the aircraft", containing three widescreen multi-function liquid crystal indicators, which displays all the information about the operation of the aircraft systems, a display generation unit, electrically connected to the formation module, control signals, search and recommendation module and data comparison module , which is connected with the computer calculator of airborne navigation systems and with the airborne signal system, the on-board test control system associated with the control system and catch with the module form logical commands. In addition, the system includes a voice informant, engine control levers, pedals and side control knobs with push-button four-position buttons with neutral, installed at the workplaces of the commander and co-pilot [3]. This system reduces the time of pre-flight preparation of aircraft and

reduce crew load at all stages of flight preparation and execution. However, it does not allow you to quickly detect and eliminate an abnormal situation.

According to its purpose and functionality, the closest technical solution to the claimed object is the “Information and Command System of the Aircraft”, [3] which the authors adopted as a prototype.

The purpose of this utility model is to expand the functionality of the system, providing quick detection and elimination of emergency and emergency situations on board the aircraft.

This goal is achieved by the fact that in the information and command system of the aircraft, containing three widescreen multi-channel liquid crystal displays, which display all the information about the operation of the aircraft systems, a display generation unit, electrically connected to a control signal generation unit, a search and recommendation module and a module data comparison, which, in turn, is associated with a computer calculator of airborne navigation systems and with an airborne signal system, an on-board test control system associated with the mode a control signal generation module and with a logic command generation module, engine control levers, pedals, side control knobs with four-position push buttons with neutral buttons installed on the commander and co-pilot workstations, an emergency command system unit installed on the top panel of the cockpit . This unit includes a manual control module with push-button lamps with feedbacks, which, when pressed, provide control signals to the actuators of the aircraft systems, the actuator switching module, four-position push buttons with neutral buttons located on the side control knobs, connected to both modules of the emergency-command system unit for semi-automatic and manual control of this system.

The essence of the presented technical solution is illustrated by drawings, which show:

in figure 1. The layout of the elements of the information-command system in the cockpit;

figure 2. Block diagram of the connections of the elements of the information-command system;

- figure 3, 4, 5. Options for emergency response using automatic, semi-automatic and manual control systems.

Information-command system (figure 1, 2) includes three multi-channel liquid crystal indicators 1, 2 and 3, located in the dashboard 4, side

control handles of the commander and co-pilot 5 and 6, respectively, pedals 7 and 8, engine control levers 9. On the control handles four-position push buttons with neutral command buttons 10 and 11 are installed.

The display generation unit 12 is connected to three indicators 1, 2, and 3, a control signal generation module 13, a search and recommendation module 14.

The on-board test control system 15 is electrically connected to the logic command generation module 16, which is connected to the control signal generation module 13, and buttons 10, 11 (one button is shown in FIG. 2).

The voice informant 17 is connected to the control signal generation module 13. The air signal system 18 and the aircraft navigation system calculator 19 are electrically connected to the data comparison module 20, which outputs signals to the display generation unit 12 and the search and recommendation module 14.

Flight information is displayed on the right and left indicators 1 and 3, and on the middle 2 - information on the navigation situation with a three-dimensional display of the underlying surface (earth), geographical, radio engineering, reference and meteorological data necessary for the flight.

Zones 21 and 26 are highlighted on indicators 1 and 3, which are used for informational and advisory and control messages, zone 27 is allocated on the middle indicator 2 for placing devices that monitor the operation of engines and aircraft systems. This information appears at the command of the module for generating logical commands 16. The emergency command system unit 28 contains a manual control module 32 with push-button lamps 33, 34 and 35 and a switching and actuating module 36 for actuators.

Command buttons 10, 11 through the emergency-command system unit 28 are connected with actuators of systems and units 29, 30 ... 31, button lamps 33, 34 ... 35 and with the above zones 21 ÷ 27 located on indicators 1, 2 and 3.

The information-command system is used by the pilot in three operating modes:

- “machine-machine-man” (M-M-Ch);

- “machine-man-machine” (M-H-M);

- “man-machine-man” (H-M-H).

The meaning of the pilot’s communication on the basis of the “machine-machine-man” principle is that the machine, based on a set of signs, reliably determines the occurrence of a phenomenon, its place and issues a command for the operation of the corresponding actuators. At the same time, pilots not only receive information about the event, but also see the result of the system on the screens of flight information indicators and information and control fields.

The meaning of communication between the pilot and the machine on the principle of "machine-man-machine" is that the "machine" offers a list of actions appropriate to the situation and sets the cursor to priority. A person, in turn, can select what he wants with the cursor, and by pressing button 10 in the "execution" mode, activates the corresponding systems and actuators.

The “man-machine-man” mode is similar to the way a user communicates with a regular computer.

The main and backup circuits of the emergency command system (Figs. 1, 2) include a test control system block 15 connected to a logical command generation module 16, which supplies control signals to the command relay 36 of alternately turning on the actuators of the automation system of the command system 28, the formation block indications 12, the unit for searching and issuing recommendations 14. In addition, the unit for generating logical commands provides a signal to the first lamp button 33 of the module 32 for manually turning on the actuators 29, 30 ... 31, the voice informant 17, bl to the formation of the indication 12, three multi-channel liquid crystal indicators 1, 2, 3 with information and control zones 21 ÷ 26. Four-position command buttons with neutral 10, 11 on the aircraft control sticks are used to force the automatic circuit for emergency response.

During the on-board operation of the on-board equipment, all signals from the on-board sensors are concentrated in the test control system block 15, which gives them to the control signal generation module 13, which provides constant information (engine speed and exhaust gas temperature, etc.) flight information indicators 1 , 2 and 3 through the display unit 12.

In the event of an emergency for automatic elimination of the phenomenon, the logical command generation module 16 determines the nature of the failure by the sum of the signs, issues a command signal through the emergency-command signal block 28 to the switching module of the actuators 36, and to light up the first lamp-button 33 of the manual failure elimination module 32. After the actuation of the first actuator 29, the signal from it is supplied to extinguish the lamp-button 33, to light up the lamp-button 34 and to the display forming unit 12, which removes nformatsionno-recommendation Fields 22 and 25 electronic displays 1 and 3, the symbol of the triggered actuator. In addition, the signal from the module for generating logical commands is supplied to the module for searching and issuing recommendations 14 and the block for generating indications 12, which in the form of labels in zones 21, 22, 24, 25 of indicators 1, and 3, highlight the necessary recommendations, while in the zone 27 indicators 2 the control devices of the corresponding system are displayed. Actuator switching module 36

automatically starts the actuators 33, 34 ... 35 in sequence in the sequence specified in the aircraft’s flight manual. When the actuator is activated, the corresponding button lamp is extinguished by feedback, then the next button lamp lights up and so on until the cycle is completed. At the same time, in the information and recommendation zones 22, 25 of the electronic indicators 1 and 3, the nature of the failure is displayed, in the same place there is a mnemonic chain of systems and mechanisms involved in eliminating the phenomenon and made with the appropriate symbols formed by the display forming unit 12. After the actuator is activated, the symbol in zones 22 and 25, and the corresponding lamp-button of the unit go out. The additional information indicated in the aircraft’s flight manual, the search and recommendation unit 14, is supplied to zone 27 of indicator 2 through the indicator generation unit 12 and the voice informant 17 to the crew headphones. Upon completion of the process chain (operation of the last actuator), the display forming unit 1 removes all information on the phenomenon from screens 21, 22, 24, 25, and 27.

On the screens of the information control field 21 and 24, information is also displayed on the nature of the failure, the programmed inclusion of the mode of its automatic elimination of FIG. 3.

In case of failure of the automatic part of the circuit, on the screens of the information-control field 21 and 24, the inscription “LIQUIDATION SEMI-AUTO” of FIG. 4 automatically appears and the cursor is positioned opposite it. The mode is activated by pressing button 10 “COI” (execution), while the chain of automatic elimination of the phenomenon is connected forcibly.

If the automation is not turned on forcibly, on the screens of the information and control fields 21 and 24 the inscription “LIQUIDATION MANUAL” of figure 5 lights up, after which the pilot must press alternately all of the sequentially lit lamp buttons on the panel of the module 32, starting the actuators 33, 34 ... 35. Erroneous pressing of a non-burning lamp-button will not lead to undesirable consequences, since it will not connect actuators unnecessary in this situation due to the lack of power supply to it.

The implementation of this utility model will almost completely eliminate the mistakes of pilots in the elimination of adverse events on board the aircraft. At the same time, the use of emergency control cards becomes irrelevant.

The presented technical solution of the information-command system of the aircraft allows:

- reduce the time for detection, recognition and liquidation of an emergency or emergency;

- significantly reduce the load on the crew in the process of eliminating the phenomenon;

- virtually eliminate the probability of pilot error when working with instrumentation in the process of eliminating an emergency or emergency.

Using the above materials, research was carried out on the flight stands of the Research Institute of Aviation Equipment, algorithms for the interaction of the system’s components with the actuators of aircraft and propulsion units were worked out, confirming the technical and economic efficiency of this utility model. Positive feedback was received from the flight crew (one of the authors of the utility model is the Honored Test Pilot of the USSR).

Information sources:

1. “Aviation Rules 25”. Interstate International Committee. 2004 year

2 "Manual on the flight operation of the aircraft IL-96-300." 1988 year

3. RF patent for utility model No. 50689 of September 8, 2005, “Information and command system of an aircraft”.

Claims (1)

The information and command system of the aircraft, containing three widescreen liquid crystal indicators, which display all the information about the operation of the aircraft systems, an indication generation unit, electrically connected to the control signal generation module, the search and recommendation module and the data comparison module, which is associated with a calculator of aircraft navigation systems and with an air signal system, an on-board test control system associated with the control signal generation module and the mod ulem of formation of logical commands, engine control levers, pedals, side control knobs with four-position push buttons with neutral buttons installed on the workplaces of the commander and co-pilot, and a voice informant, characterized in that the emergency-command system unit installed on it is additionally inserted the top panel of the cockpit and including a manual control module with push-button lamps, feedback buttons that provide control signals to the actuators of the units system of the aircraft, and a module for switching actuators, with four-position push buttons with neutral buttons located on the side control handles, connected to both modules of the emergency command unit for manual control of this system.