RU2219108C1 - Complex electronic display system for light multi- purpose aircraft - Google Patents

Abstract

FIELD: aircraft instrumentation engineering. SUBSTANCE: proposed system includes multi-functional color displays, collimator indicator on windshield and multi-functional control console connected with on-board digital computer by means of multiplex and reserve radial information exchange channels. On-board digital computer is also connected with mode parameter sensors. Multifunctional color displays (no less than three displays) are fully interchangeable; they provide pilot with complete pilotage navigational information in case of failure of one of them and minimum scope of information in case of failure of two of them. EFFECT: enhanced operational reliability. 3 cl, 2 dwg

Description

 The invention relates to the field of aviation instrumentation and is intended for use in the implementation of the display of the state parameters of the aircraft and on-board equipment.

 The introduction of automated (director's) and automatic control systems on an airplane does not always lead to a decrease in the number of electromechanical indicators, and in some cases requires their increase in accordance with an increase in the number of monitored parameters (signals about operability and failures). Therefore, the development of options and the degree of automation of aircraft control and pilot activity algorithms should be carried out with the simultaneous introduction of new concepts for constructing information and control fields at the workplaces of flight crew members, providing for the creation of comfortable conditions for the pilot to consciously control the situation and his own actions, as well as quickly incorporate control circuit.

 Aircraft multifunctional indicator is known, made with a liquid crystal screen, a control unit for operating modes, and a line for information and computational exchange of information between composite nodes (RU 2178375 C1, B 64 D 45/00, 01/20/2002). This device has advanced functionality and can, in particular, work as an indicator of tactical conditions, an indicator of low-altitude flight, an indicator on the windshield, an indicator of visibility equipment, as well as a multifunctional control panel for an aircraft and on-board equipment. However, its operational reliability, especially in difficult operating conditions, for example in a wide temperature range, is insufficient.

 Closest to the proposed one is a comprehensive electronic display system containing multifunctional color indicators (MFCI), a collimator indicator on the windshield (KAI) and a multifunctional control panel (MFPU) connected by multiplex and redundant radial channels of information exchange with the control computer, to which the sensors are connected operating parameters (RU 20592 U1, G 06 F 17/40, 10/10/2001).

 However, the known system does not use any solutions to improve the MFCI, and therefore it also does not guarantee safe piloting.

 The objective of the invention is to increase the operational operational reliability of such a system.

 The problem is solved in that in an integrated electronic display system containing MFTS, KAI and MFPU, connected by multiplex and backup radial channels of information exchange with the control BCVM, to which the sensors of operational parameters are connected, MFCI, the number of which is brought up to three, are completely interchangeable and made with the possibility of providing the pilot with complete flight and navigation information in case of failure of one of them and with a minimum amount of flight and navigation information necessary for zopasnogo piloting, in case of failure of two of them.

 Partial essential features of the invention also contribute to the solution of the problem.

 In particular, the left MFCI is used as a flight-navigation indicator and carries information sufficient to perform any flight maneuver, as well as for aircraft navigation to the selected navigation point, the central MFCI is used as a flight-planning indicator and carries information about the position of the aircraft relative to a given track in the horizontal plane during take-off, flight along the route and approach, and the right MFCI is used as an indicator of monitoring the status of aircraft systems and carries information about the configuration of the aircraft, the operation of all systems and units.

 Two MFCIs, an MFPU and a control BCVM are connected via a power supply circuit to a storage battery and rectifier devices of alternating current generators of the main or auxiliary power units.

 The introduction of multifunctional means of displaying information and governing bodies changes the principle of "each on-board system has its own indicator (group of indicators) and governing body (group of governing bodies)", applied on third generation airplanes, to the modern principle of "integration of means of displaying information and governing bodies that change their function according to a specific plan, in the information-control fields. " Therefore, at present, a whole series of new requirements are presented to the information-control fields, due to the fact that new means and forms of information display are being introduced, which, like the installed controls, integrate the capabilities of a large number of remotes. The new requirements are due, on the one hand, to the possibility of reducing the dimensions of dashboards along with the optimization of information flows in flight between crew members, as well as the need to present flight information at the flight stages and in the event of an emergency. On the other hand, the operational determination of the functional value of the minimum number of established controls is gaining importance. This fact predetermined the need to justify new principles for constructing a rational layout of the workplaces of the Yak-130 aircraft (macro layout) and the principles of micro layout of the presentation of information on screen indicators.

 Figure 1 and 2 presents the functional diagrams of the proposed integrated electronic display system for light multi-purpose aircraft, respectively, for single and double (with an operator or instructor) versions.

 The diagrams indicate a complex electronic indication system 1, controlling a digital computer 2, a multiplex information exchange channel (MKIO) 3, a local information exchange channel (LKIO) 4, MFTS 5, 6, 7, KAI 8, MFPU 9, a rectifier 10, main generators power plant (SU) 11, the generator auxiliary power unit (APU) 12, the batteries 13, the sensor system operating parameters 14.

 The cabin of the Yak-130 aircraft is made taking into account the above trends in the development of instrumentation equipment for promising fifth-generation military aircraft. A feature of the integrated electronic display system for the Yak-130 combat trainer aircraft is the absence of primary and backup electromechanical devices.

 Indication support for flight and navigation modes, monitoring the operation of general aircraft equipment and combat use is implemented using three MFCI 5-7 on a liquid crystal matrix, KAI 8, MFPU 9, which are combined into a single integrated information system with a control computer 2 with multiplex 3 and local 4 channels information exchange, which allows not only to present an increasing amount of information from various means on a limited area of the dashboard, but also to optimize the conditions for the perception of quantitative instrumental and natural extra-cabin information, increase its visibility. Communication MFCI 5-7, KAI 8 and MFPU 9 with the control BCVM 2 is also carried out by the backup radial channels of information exchange (not shown in the diagrams).

 In order to increase survivability, two of the MFCI 5-7 and the control BCVM 2 are connected to the power supply system in the first category, i.e., as already indicated, they are powered by a rectifier device 10 of the alternator, the main 11 or auxiliary 12 power plants and battery batteries 13.

 The principle of interchangeability of indicators allows for the failure of one of the MFCI 5-7 to provide almost the full amount of information for the flight and navigation and combat missions, and for the case of failure of two of the MFCI 5-7, a special emergency information frame has been developed that ensures the issuance of a minimum flight and navigation information on one not failed MIFC, necessary for safe piloting.

 Refusal to use the main and backup electromechanical devices allows you to rationally use the area of the dashboard, while reducing the degree of information saturation in the operational field of perception.

 The layout of the cockpit is made in accordance with the necessary sequence and time spent by the crew on monitoring the system and using controls. Operational consoles (MFPUs, consoles of an integrated control system, flap control, communication control) and control elements (landing gear release-cleaning lever, emergency landing gear release switch, headlights on), work with which proceeds in a time shortage, are located under the left hand. Equipment, work with which is carried out only with the right hand, requires a short-term interception of the aircraft control wheel with the left hand. These operations are carried out when it is necessary to switch the channels of the aircraft radio compass, temperature changes in the cabin, etc. All of them do not require immediate execution.

 The logic of the distribution of indicator information on the screens of the MFCI 5-7 and KAI 8 is based on a number of provisions.

The navigation modes of the Yak-130 aircraft include the following modes:
- take off;
- flight along the route;
- "guidance" and "attack";
- return to the landing airport;
- landing;
- re-approach.

The modes of the combat (training) Yak-130 aircraft include:
- guidance;
- attack;
- exit from the attack.

(All the indicated modes, except the “TAKEOFF” mode, are provided by the complex in manual, director and automatic versions. Take-off is carried out only in the manual version.)
Information on indicators (with a 4-indicator version of the cab - 3 MFTSI + KAI) is distributed as follows.

 At KAI 8, the main flight information is posted - the position of the aircraft in space, data on altitude, speed, direction of flight, data on the target, area of destruction and instructions for using weapons. Alerts can also be issued about dangerous flight conditions and crash aboard.

 The left MFCI 5 presents flight and navigation information in an amount sufficient to perform tasks in difficult weather conditions (clouds, above the sea, out of sight of the horizon, at night, etc.).

 The average MFCI 6 represents a tactical situation, navigation data or cartographic image.

 The right MFCI 7 provides the pilot with information on the operation of aircraft systems, engines, equipment, issues recommendations for actions in special cases, in case of erroneous actions of the pilot during the flight stages within the framework of the expert system, and information from television-optical weapons.

 In case of failure of any of the MFCI 5-7, information from the failed indicator can be installed on any other MFCI.

 A video recorder is installed on board, recording an indication from KAI 8 with a cockpit space and radio exchange. If necessary, you can quickly replace the recorded MFCI with any other.

 The main task of KAI 8 is to provide targeted information to the pilot against the flight. Information "flexible" - varies by flight stages. Stages: take-off, flight en route, combat use, approach. The basis of aerobatic information is the velocity vector, which receives data characterizing the movement of the aircraft from the inertial system, and when it fails, from the sensors of the angle of attack and slip.

 When performing the aiming, an aiming mark is displayed, showing the location of the ammunition, the affected area. When working on air targets, if there is data about the target, a target mark is displayed that matches the real target, and when the target is outside the field of view of KAI 8, a signal indicating the direction to the target is displayed. When landing on KAI 8, a synthesized "pseudo" runway is formed that coincides in location and angular size with the actually visible one.

When the “TAKEOFF” mode is executed, the following symbols are displayed on the format:
- aircraft circuit;
- roll scale (fixed);
- pitch scale (movable);
- course scale;
- digital counter of the current height;
- digital instrument speed counter;
- mode pointer - the inscription "VZL" (take-off).

When the “ROUTE” mode is executed, the following symbols are displayed on the format:
- aircraft circuit;
- roll scale (fixed);
- pitch scale (movable);
- course scale;
- control mode indicator: "DIR" - director, "AVT" - automatic;
- the velocity vector, receiving data characterizing the movement of the aircraft from the inertial system;
- the symbol "DANGEROUS AREA" - appears on the screen 4-5 seconds before reaching the height from which it is necessary to start the maneuver to get away from a dangerous height;
- the symbol "OTV" (lapel to the ground) is displayed 2 seconds before reaching a dangerous altitude and is removed when entering safe flight conditions;
- digital height meter in meters;
- digital instrument speed meter in km / h;
- movement mode in the vertical channel: "HIGH" - stabilization of height, "PG" - bringing to the horizon, "STB" - stabilization of angles, "DRIVING" - mode of moving away from the earth;
- digital counter of the distance to the navigation point.

 In the “RETURN” mode (return to the landing aerodrome) on KAI 8, a frame identical to the frame of the “ROUTE” mode is formed, with the following difference: instead of specifying the “ROUTE” mode, the text “EXPLOSION” (return) is formed.

In the "LANDING" mode, the following symbols are displayed on the format:
- aircraft circuit;
- roll scale (fixed);
- pitch scale (movable);
- course scale;
- digital counter of the current height;
- digital instrument speed counter;
- set course - runway course;
- flight mode - "PIC"(landing);
- control mode indicator: "DIR" - director, "AVT" - automatic;
- the velocity vector, receiving data characterizing the movement of the aircraft from the inertial system;
- synthesized "pseudo" runway, matching in location and angular size with the real visible;
- range to the end of the runway;
- a symbol indicating a deviation from the course and glide path beacons.

KAI 8 multi-frame for RETRIEVE mode corresponds to a multi-frame for ROUTE mode with the following differences:
- the mode indicator is indicated - "PZ"(re-entry);
- the set course is formed in accordance with the reentry path.

 The KAI 8 multi-frame corresponds to the “ROUTE” multi-frame with the symbols “DANGEROUS AREA”, “REVERSE FROM THE EARTH” and the text symbol “DRIVING” appears.

The nomenclature of the flight and navigation mnemonic frames and mnemonic frames for monitoring the state of aircraft systems on the MFCI 5-7 indicators is the same and includes the following mnemonic frames:
- combined flight and navigation information: IKP + NPP;
- navigation and planning information: "REVIEW", "ROUTE", "ITO", "LANDING";
- control of the state of aircraft systems: formats - "TYPICAL (main)", "ENGINE", "HYDROPEUMO", "FUEL", "SJO", "SDU", "SES", "PREPARATION".

 The choice of a specific mnemo frame is carried out by the pilot using the multifunction buttons in the frame of the MFCI 5-7. The menu is present on all mnemo frames, at the top of the screen of the right MFCI 7.

 In the ground training and control modes, frames are provided in the form of various text menus and submenus, accompanied by text instructions, guided by which the flight or technical personnel check the status of on-board equipment, aircraft units and power plants.

 The left MFCI 5 is used as a flight-navigation indicator and carries information sufficient to perform any flight maneuver, as well as to perform aircraft navigation to the selected navigation point.

 On the frame in the format of flight and navigation information is indicated by the position of the aircraft relative to the horizontal plane. Horizontal and vertical speeds, overload, angle of attack, velocity vector, barometric and radio heights, target and dangerous flight heights, heading scale, target and current courses, distance and angular deviation relative to the current point to which the flight is carried out, deviation from course and glide path are displayed beacons (in the "LANDING" mode). Additionally, barometric pressure, time and fuel reserve are displayed.

 The central MFCI 6 is used as a flight-planning indicator and carries information about the position of the aircraft relative to a given path in the horizontal plane during take-off, flight along the route and approach (the planned flight picture or an electronic map of the area).

 The tactical situation includes information about the enemy - the front line, the location of anti-aircraft defense systems, missile defense zones, targets, in the presence of inter-aircraft communication - the position of their aircraft, tanker for refueling, etc. Symbols are removed from the display, if necessary, using the buttons on the frame of the indicator, to form the set of characters necessary in a particular case. The tactical indication reflects the characteristics of all air targets that are accompanied (in the overview) by the locator and transmitted along the line of interaction from the ground or aircraft. At KAI 8 and MFCI 5-7, recommendations are formed on how to carry out the attack, optimal trajectories for reaching a given target.

 The right MFCI 7 is used as an indicator of monitoring the state of aircraft systems and carries information about the configuration of the aircraft, the operation of all systems and units. The main form of presentation of information is mnemonic. The depth of control is sufficient for analysis and decision-making on the operation of systems by both flight and technical personnel without additional connection of control panels. If necessary, information from television-optical means of destruction is displayed.

When operating in the integrated display system of KISS aircraft systems, the screen displays generalized mnemonic information about the status of aircraft systems (TYPE format). At the same time, in the right peripheral zone the inscriptions “DVIG”, “TOPL”, “HYDR”, “SES”, “KSU”, “SZHO” are displayed to the left of the buttons from the indicator frame. When the corresponding button is pressed, the generalized mnemonic information is removed and displayed:
- when you press the "ENGINE" button - information about the state of engines and APU;
- when you press the "TOP" button - information about the state of the fuel system;
- when you press the "HYDR" button - information about the state of the hydropneumatic system;
- when you press the "SES" button - information about the state of the power supply system;
- when you press the "KSU" button - information about the state of the integrated control system;
- when you press the "SJO" button, information about the state of the oxygen system and the air conditioning system.

 When the control button is pressed, the corresponding inscription is framed by a rectangular frame.

 When the KISS button is pressed, generalized mnemonic information on the state of aircraft systems (TYPICAL format) is restored.

 In the upper part of the screen on the central (navigation) 6 and right (state of general aircraft systems) 7 of the MFCI, a working field with a size of two text lines is highlighted to indicate messages from BASK. In the upper right part of the screen of the left (aerobatic) MFCI 5, a familiarity for the yellow central navigation center is highlighted, designed to attract the attention of the pilot when warning information appears on the BASK working field.

 Thus, the proposed integrated electronic display system has wide functionality and is simultaneously characterized by increased reliability.

Claims (3)

1. A comprehensive electronic display system containing multifunctional color indicators, a collimator indicator on the windshield and a multifunctional control panel connected by multiplex and redundant radial channels of information exchange with the control computer, to which mode parameters sensors are connected, characterized in that the multifunctional color indicators, number which are brought to three, are completely interchangeable and are designed to provide the pilot with full flight avigatsionnoy information in case of failure of one of them and the minimum amount of flight and navigation information necessary for the safe piloting, in case of failure of two of them. 2. The integrated electronic display system according to claim 1, characterized in that the left multifunctional color indicator is used as a flight-navigation indicator and carries information sufficient to perform any aerobatic maneuver, as well as for aircraft navigation to the selected navigation point, a central multifunctional color indicator it is used as a flight-planning indicator and carries information about the position of the aircraft relative to a given line in the horizontal plane during take-off, flight route and approach, and the right multi-color indicator is used as an indicator of condition monitoring of aircraft systems and contains information about the configuration of the aircraft, all the systems and components. 3. The integrated electronic display system according to claim 1 or 2, characterized in that two multifunctional color indicators, a multifunctional control panel and a control computer are connected through power circuits to the battery and rectifier devices of alternating current generators of the main or auxiliary power plant.

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