RU2392586C1 - Aircraft information-control system - Google Patents

Abstract

FIELD: physics; control.

SUBSTANCE: invention relates to aerospace instrument making and specifically to systems for controlling and indicating the state of an aircraft. The aircraft information-control system has an information-control field, an onboard digital computer system, an input-output and exchange control unit, a unit for setting pilot-navigation parametres and a flight mission database. The system also has a signal concentrator unit, a unit for generating and integrating display data and receiving control input, a unit for controlling and monitoring general aircraft equipment, an electronic countermeasure control unit, a unit for enabling low-altitude flying, a unit for enabling group aircraft navigation, a unit for controlling recording on objective control apparatus and a mode control unit.

EFFECT: broader functional capabilities.

4 cl, 1 dwg

Description

The invention relates to the field of aeronautical engineering, namely to control and indication systems.

Known sighting and navigation complex equipment multifunctional aircraft (RF patent No. 2282156), containing interconnected inputs and outputs on the on-board channel of information exchange pilot information and control system, display information and control system of the operator, a complex of navigation and flight means, a complex of sighting and sighting means , a control system for countermeasures, an on-board computer system, including interconnected I / Os on the highway in numeral information exchange computationally logic modules combined database forming navigational flight parameters forming sighting-flight parameters forming the display information, and input-output control information exchange, the other input of which the output is input-output of the onboard computer system. In addition, the complex is equipped with computer logic modules introduced in the on-board computer system for the mutual correction of navigation and sighting parameters, the mutual synthesis of navigation and sighting parameters, the formation of acceptable parameters of the state of the aircraft, the simultaneous coordinated use of countermeasures interconnected by inputs and outputs between themselves and the computational logical modules of the integrated database, the formation of navigation and flight parameters, input-output and control detecting information exchange, forming precisely-flight parameters and forming information displayed on line computing information exchange.

Known sighting and navigation system of a multifunctional aircraft carrier and ground-based (RF patent No. 2276328), containing a set of multifunctional indicators interconnected by inputs and outputs on the information exchange channel, an indicator on the windshield, an on-camera television camera, operational controls, a set of sighting equipment , a set of navigation and flight control aids, a portable data carrier, a control system for countermeasures, a computer system him, including interconnected inputs and outputs along the highway of computational information exchange, the computational and logical modules of the integrated database, the formation of navigation and aerobatic parameters, the formation of aiming aerobatic parameters, the formation of the displayed information, input-output and information exchange control, the input-output of the last of which is the input-output of a computing system. The complex is also equipped with computational and logical modules for virtual control of equipment introduced into the computer system, inertial-satellite mode for generating relative coordinates of the aircraft’s location, an exhibition at the heading on a moving and oscillating base, optimal use of resources, interconnected with each other and with computational and logical modules of the integrated base data, the formation of navigation and flight parameters, the formation of sighting and flight parameters of the formation I display information, input-output and information exchange management on the highway of computational information exchange.

The closest analogue is the information and control complex of an aircraft (LA) (RF patent No. 2232376), which includes the information and control field interconnected by inputs and outputs on the information exchange channel, the on-board digital computer system, which includes the input-output block interacting via the information exchange computer channel and exchange control, a block for the formation of flight and navigation parameters, a flight task database.

As disadvantages of the closest analogue, you can specify the following:

- the complex consists of functionally complete systems that autonomously solve all problems from obtaining information with their sensors to issuing control information to a display system, signals to aircraft control systems and weapons. As a result, each of the information systems has its own problem solving algorithms that do not take into account the information of other systems, its own autonomous output channel for indication, its own control bodies. The integrated use of information from other systems, with the exception of the task of targeting from one system to another and correcting the navigation system from a satellite navigation system (SNA) or a radar station (radar), is practically not implemented;

- the lack of information coming through analog lines, as a result of which the blocks from the composition of the VSK have limited information;

- the lack of a built-in display processor in the display means, designed to solve computational problems, in addition to forming an indication, makes the complex virtually inoperable in case of a failure of the VSK.

The objective of the invention is to expand the functionality of the information management system, as a consequence of this, to increase the efficiency of its operation when used for multi-functional aircraft. The functionality of the information management system is expanded by adding the following functions:

- management of general aircraft equipment;

- Monitoring the status of the systems of the BWC, CCA and SU, ASP;

- a comprehensive solution to the problem of electronic countermeasures;

- automatic and automated control of the operating modes of the BWC, CCA and SU systems.

The problem is solved in that the information-control system of the aircraft, containing the information-control field interconnected by inputs and outputs on the information exchange channel, the on-board digital computer system, including the input-output and exchange control unit interacting via the information exchange computer channel, and the flight navigation parameters, flight task database, equipped with a signal concentrator unit and integrated digital computer System unit of formation and integration of data for display and reception of control actions by the control unit and control obschesamoletnogo equipment, electronic warfare control unit, providing a low-altitude flight unit, a software group piloting, recording control unit of the means of objective control, mode control unit.

The system may further comprise an external storage device interconnected by inputs / outputs with an information exchange channel.

The system may further comprise a television signal conversion unit interconnected by inputs / outputs with an information exchange channel.

The system may further comprise an aircraft control unit incorporated in the on-board digital computer system.

The invention is illustrated in the drawing, which shows a block diagram of an information management system.

The proposed information management system (IMS) contains the following elements:

1. BPTS - unit for converting television signals,

2. VZU - external storage device,

3. IUP - information management field,

4. BCS - signal concentrator block,

5. BTsVS - on-board digital computer system,

6. KIO - information exchange channel,

7. VVUO - block input-output and exchange control,

8. FVIDIPUV - data generation and integration unit for indicating and receiving control actions,

9. UKOSO - control and monitoring unit for general aircraft equipment,

10. FPNP - block for the formation of flight and navigation parameters,

11. UEP - electronic countermeasure control unit,

12. BDP3 - flight mission database,

13. OMVP - low-altitude flight support unit,

14. OGSV - block providing group aircraft navigation,

15. ULA - aircraft control unit,

16. UZSOK - control unit recording on the means of objective control,

17. OBPiUO - unit for the combat use and control of weapons,

18. BUR - control unit modes

19. VKIO - computing channel of information exchange.

The block for converting television signals (BPTS) 1 is a device for receiving, switching, converting and issuing in the information-control field (IUP) 3 television signals (images) received at its inputs, both in analog and digital form from the BCVS 5, CCD and ASP systems. BPTS 1 is connected by KIO 6 output with IUP 3 and input / output 5 (BTsVS).

External storage device (VZU) 2 is a device that provides input of information through a removable medium from the ground-based training complex, its storage and delivery to the on-board digital computer system (BCVS) 5, documentation of the results of the IMS for subsequent express analysis. VZU 2 is connected via KIO 6 input / output with the BCVS 5.

The information-control field (IUP) 3 is a set of on-board display and control devices of aircraft, which include, for example, multifunction indicators (MFIs), including those with built-in display processors (the display processor is a processor capable of not only to form an image, but also to solve computational problems), multifunctional indicator displays (MFPI), collimator aviation indicator (KAI), control and display panel. IUP 3 is connected by KIO 6 input with BPTS 1 and inputs / outputs with BTsVS 5 and BCS 4.

The Signal Block Concentrator (BCS) 4 is a device designed to receive analog signals in accordance with GOST 18977-79 from aircraft systems, commands from control units, convert them to digital format, and also receive signals in digital form and issue them in analog view of actuators. BCS 4 is connected by KIO 6 inputs / outputs with BTsVS 5 and IUPZ.

Information interconnection inside the IMS is carried out through the channel of information exchange 6 (KIO). Blocks 1-4 are connected by their inputs / outputs to KIO 6, to which the input / output of the BCBC 5 is also connected.

At the same time, the input / output of the BCVS 5 is the input / output of the input / output and exchange control unit (VVUO) 7 included in the BCVS 5, and the other input / output of the VVUO 7 is connected to the internal computing channel of the information exchange 19 (VKIO), to which also the inputs / outputs of the computational-logical blocks 8-18 included in the BCVS 5 are connected, and through which information exchange between these blocks is carried out.

The channels KIO 6 and VKIO 19 are known lines of communication and information exchange, for example, by serial code, by parallel code, multiplexed and others.

The WSUO 7 block is a well-known device for interfacing a calculator with communication lines, which carries out the reception, control and delivery of information.

Blocks 8-18 are made in the form of computational logic modules placed on uniprocessor computers.

The data generation and integration unit for indicating and receiving control actions (FVIDIPUV) 8 generates and issues information for indication from the systems of the avionic equipment complex (BWC), general aircraft equipment (OSO) and power equipment according to VKIO 19 through VVUO 7 to IUP 3 according to KIO 6 installations (CS) (BWC, CCA, and CS are not shown in the figure), as well as receiving, processing, and issuing to other computational logic modules (such as FPNP 10, UKOSO 9, ULA 15, BUR 18, and others) the parameters of control actions from the pilot.

The control and monitoring unit for general aircraft equipment (UKOSO) 9 analyzes the state of the CCA and control systems, as well as automatic and automated control of these systems.

The block for the formation of flight and navigation parameters (FPNP) 10 calculates the state parameters of the aircraft, including its coordinates, motion and orientation parameters, and construction of flight paths.

The electronic countermeasure control unit (EEC) 11 provides automatic or automated command control of electronic countermeasures (EPR), electronic reconnaissance (RTR), optoelectronic counteraction (OEP) and ejection devices (HC), false targets (ALC), and a radar station (Radar) to ensure individual, individual, mutual and group protection of the aircraft, including in case of equipment failures and errors in crew actions (REP, RTR, ALTs, radar in the figure n e shown).

The block of the flight task database (BDL) 12 provides access to the database of the flight task (PZ), the transfer of data PZ at the request of the blocks using them, with the synchronization of read-write data PZ; PP data changes: adding, deleting, editing data, monitoring the integrity of the PP.

The low-altitude flight support unit (OMVP) 13 provides the tasks of the low-altitude flight (MVP) mode using a digital terrain map (CCM) with the issuance of automatic control signals according to VKIO 19 through the WSIS 7 to the automatic control system (ACS) (not shown) according to the KIO 6.

The group navigation support unit (OGSV) 14 provides the implementation of the group navigation mode using information from the aircraft's onboard systems to determine the relative location of aircraft.

The aircraft control unit (ULA) 15 provides the formation of parameters for manual, director and automatic control of the aircraft and engine thrust according to information from computational logic modules, such as FPNP 10, OMVP 13, OBPiUO 17 and others according to VKIO 19, as well as from Self-propelled guns, systems of limiting signals (SOS), systems of air signals (SHS) (not shown in the figure) according to KIO 6.

The recording control unit for the means of objective control 16 (UZSOK) provides the issuance of external exchange means (not shown) of the exchange parameters from the computing and logical modules and from external systems according to KIO 6.

The unit for providing combat use and control of weapons (OBPiUO) 17 provides the solution to the problems of the combat use of aviation weapons (TSA, not shown in the figure) with the help of intelligent crew support, control of the modes and reconfiguration of combat use.

The mode control unit (BUR) 18 provides control of the coordinated operation of the systems of the aircraft onboard equipment complex and the computer-logic modules BTsVS 5.

IMS works as follows.

Measured information from the BWC systems (flight and navigation, airspeed parameters, targets and their characteristics, weapon control status, information received from communication equipment, etc.), CCA (tire voltage, cabin pressure, chassis condition parameters, etc.) and control system (engine speed, fuel quantity, etc.) in digital form enters through KIO 6, block VVUO 7 in the highway VKIO 19, then to the inputs of blocks 8-18. The measured information from the BWC, CCA, and SU systems is transmitted in analog form to the BCS 4 and through KIO 6, the VVUO 7 block to the VKIO 19 highway, from where to the inputs of blocks 8-18.

At the input of the BPTS 1 block according to KIO 6, the television information is received in digital form from the BWC, ASP, and BTsVS 5 systems. By the commands from the BTsVS 5 coming through KIO 6, the BPTS 1 carries out the following image processing: combining several images, cropping according to a given format, increase, - and according to KIO 6 it issues to the input of IUPZ.

In the block VZU 2, a removable storage medium is installed, after which, upon commands from the BDPZ 12, the information on the KIO 6 is transmitted to the input of the BDPZ 12. The BDPZ 12, upon request, issues it to the inputs of the other BCCV 5. Upon request, the BCCV 5 blocks can change the information and transmit it to the BDPZ block 12 to clarify the data stored there. Also, in flight, various information from the BCVS 5 blocks used for analysis after the flight is recorded in the VZU 2 using KIO 6.

The ICP 3 unit receives information from the BCVS 5, BCS 4 and the BWC, OSO and ASP systems through the KVO 6 input and receives commands from the pilot through the built-in control elements and transmits them through the KVO 6 to the input of the BCVS 5 and the BWC, OSO and ASP systems. In the standard configuration (in the absence of failures of the ICS blocks), ICP 3 only works with information from the BCVS 5. The presence of the built-in display processor allows, in the event of a failure of the BCVS 5, receiving information directly from the BWC, CCA, and ASP systems, to solve the display problems and, in part, control over the KIO 6 lines, to the extent necessary to solve the problems of ensuring the return and landing of the aircraft. Also, this feature reduces the load of KIO 6, allowing you to transfer only parametric information and image formatting commands, instead of sending a very large number of commands for drawing primitives (line, square, circle, etc.) and the features of their display (color, fill, location etc.)

The BCS 4 unit receives input in analog form from the BWC, OSO and SU, ASP systems for solving control and indication tasks and transmits it via KIO 6 to the inputs of the BCVS 5 and IUP 4. The BCVS 5 processes this information and generates control impacts transmitted by KIO 6 to the input of BCS 4, for converting them into analog form.

All measured information about the orientation and spatial position of the aircraft, its position relative to other objects and the earth’s surface, is transmitted via KIO 6 to the WSIS block 7, from where it is fed to the VKIO highway 19 to the input of the FPNP block 10. Information about the specified flight parameters (route, navigation points, given course, etc.) enters the FPNP 10 through VKIO 19 from the BDPZ 12. Having built-in algorithms, taking into account signs of serviceability of the systems and the reliability of the information, the FPNP 10 carries out complex processing of flight and navigation information and issues it according to the FRI 19 blocks at inputs 8, 9 and 11-18 and via the ECC VVUO 7 to 6 in other systems, such as radar, RL, flight and navigation equipment, and others.

FVIDIPUV 8 unit receives input information for indication from aircraft systems, BPTS 1, BKS 4 blocks transmitted via KIO 6 through VVUO 7 and from blocks 9-18 according to VKIO 19. Forming packets in accordance with the current operating mode and indication of FVIDIPUV 8 issues them according to WKIO 19 to the input of WSIS 7 for issuing according to KIO 6 to IUP 3. IUP 3 only parameter information and configuration management commands IUP 3 are perceived. All tasks associated with drawing characters are solved autonomously in IUP 3. Also, taking into account the information received from OBPiUO 17 and IUP 3, FVIDIPUV 8 generates control actions for BPTS 1. In providing a response to the pilot’s commands, FVIDIPUV 8 receives control actions from IUP 3, which processes it with reference to the current state of IUP 3 and passes to the input other blocks.

The UKOSO 9 unit receives information on the status of the BWC, CCA, and SU systems from the BCS 4 and directly from the KIO 6 systems through the WSIS 7, as well as the orientation and location parameters of the aircraft from FPNP 10, taking into account the control actions of the pilot from IUP 3 through KIO 6 through WSIS 7 and BWC then BUR 18 modes, UKOSO 9 unit generates and issues according to VKIO 19 information about the state of the CCA and control systems to the input of the FVIDIPUV 8 block, as well as commands to control the CCA and control systems to the BCS 4 input and CCA and control systems for KIO 6 through WSIS 7.

The UEP block 11 receives information on the presence of a direct or potential threat to the aircraft from the REP, RTR, OEP means, the status of the HC, ALTs, TSA and the command from the group commander through WSIS 7 according to KIO 6, the position of the aircraft from FPNP 10 and automatically or it is automated according to the pilot’s commands coming to the entrance on VKIO 19 from FVIDIPUV 8, generates control actions on VKIO 19 for the radar, RTR, REP, UV, ALTs and ASA systems through VVUO 7 to KIO 6.

OMVP 13 receives information on the orientation and location parameters of the aircraft from FPNP 10, information on the current control parameters of the aircraft from the ULA 15 block, on the specified characteristics of the route, and, if any, a digital terrain map (BSC) from the BDPS 12. Considering the terrain at this point and the entire region as a whole, OMVP 13 forms the parameters of the aircraft control to ensure low-altitude flight and transmits them to VKIO 19 in ULA 15 and for indication to FVIDIPUV 8.

The OGSV block 14 receives information on the orientation and location of the aircraft from the FPNP 10 at the entrance to VKIO 19, on the current control parameters of the aircraft from the ULA 15 block, on the specified characteristics of the route and the parameters of the GSV from the BDPS 12 and group combat use from the OBPiUO 17, command information from a complex of communications equipment (KSS, not shown in the figure), the location of other aircraft relative to that given from the RSBN (not shown in the figure) by KIO 6 through the WSIS 19. Based on the received information, the OGSV 14 generates and transmits control signals via VKIO 19 to the input of ULA 15 WHO Procedure for the aircraft and pilot information for the input FVIDIPUV 8, group combat use input OBPiUO 17 and into interacting LA through VVUO 7 ECC 6 via CMP.

The ULA 15 block receives information on the orientation and location parameters of the aircraft from FPNP 10, information about the specified characteristics of the route from the BDPS 12, the relative position of interacting objects from the OGSV 14, and the current value of the control parameters of the self-propelled guns through the WSIS 7 through KIO 6. On Based on the information received, taking into account data from OMVP 15 and the modes from BUR 18, it generates signals for automatic, manual and director control of the aircraft to complete the task and prevent collisions with the ground, interacting aircraft or fragments. Control parameters are transmitted via WKIO 19 to the input and through WSIS 7 through KIO 6 to the input of the self-propelled guns.

The UZSOK 16 block receives the parameters of inter-block exchange from the computing and logic blocks of the BCVS 5 and from the BWC, OSO and SU, ASP systems through the WSWO 7 to the KIO 6 at the input through the WKSD 19 list, and already formed into sets. From the parameters that have come in separately from the computing and logical units of BCVS 5 and from the BWC, OSO and SU systems, the ASP UZSOK 16 forms sets that are queued and transmitted via VKIO 19 through WSIS 7 through KIO 6 to the registration means.

The OBPiUO 17 block receives information on the orientation and location parameters of the aircraft from FPNP 10 at the entrance to WKIO 19, about the specified characteristics of the combat use from the BDPZ 12, about the restrictions imposed on the combat use from the UEP 11 and OMVP 13, about the control parameters of the aircraft from ULA 15 and through WSIS 7 to KIO 6, on the actions of the aircraft in the group from the KSS and the presence and condition of the TSA from the TSA and the weapon control system (MSA, not shown) Automatically, automatically, or by commands from the pilot received from FVIDIPUV 8, taking into account the modes from BUR 18, forms target designations for the TSA and the command for combat use and issues VKIO 19 through the WSIS 7 to KIO 6 in the TSA, SUO, radar, optical-location station (OLS, not shown in the figure) and a complex of communications.

The BUR unit receives information on navigation modes from FPNP 10 at the entrance to VKIO 19, about a given route from BDPZ 12, about compression of the chassis from UKOSO 9, about combat use modes from OBPiUO 17, requests for low-altitude flight from OMVP 13 and issues the generated mode work to all interested consumers, such as FVIDIPUV 8, FPNP 10, UEP 11, OGSV 14, OBPiUO 17 and others.

Claims (4)

1. Aircraft information and control system, comprising an information and control field, an on-board digital computer system, including an input / output and exchange control unit interacting via an information exchange computer channel, an aerodynamic-navigation parameters unit, flight task database, characterized in that it is equipped with a signal concentrator unit and included on-board digital computer of a new system by a data generation and integration unit for indicating and receiving control actions, a control and monitoring unit for general aircraft equipment, an electronic countermeasure control unit, a low-altitude flight support unit, a group navigation support unit, an objective control recording unit, and a mode control unit. 2. The system according to claim 1, characterized in that it contains an external storage device interconnected by inputs / outputs with an information exchange channel. 3. The system according to claim 1, characterized in that it contains a unit for converting television signals interconnected by inputs / outputs with an information exchange channel. 4. The system according to claim 1, characterized in that it contains the control unit of the aircraft introduced into the on-board digital computer system.

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