RU2767938C2 - Integrated complex of on-board equipment of unmanned aerial vehicle - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to the field of aviation technology, namely to aircraft control systems. An integrated complex of on-board equipment of an unmanned aerial vehicle contains systems interconnected via a multiplex channel of information exchange and via an information exchange channel: a complex of flight navigation equipment, a complex of communication means, an information control system, an aircraft responder of air traffic control with an antenna system, a complex system of automatic traffic control, a system for monitoring and recording flight parameters and operation of on-board equipment, aerobatic aerometric equipment.

EFFECT: increase in the autonomy and automation of the on-board equipment complex, increase in the reliability and efficiency of the use of an unmanned aerial vehicle.

1 cl, 1 dwg

Description

The invention relates to the field of aviation technology, namely to control complexes for information and executive systems of on-board equipment, general aircraft equipment and an aircraft.

A list of designations and abbreviations that will be used in the future when characterizing the developed technical solution.

In addition, the following terms will be used:

The signal is an executive information parameter having a "smooth character".

A command is a discrete binary message to perform a specific action (assigning or changing a mode, turning a device on/off).

A sign is a feedback message that characterizes the fact that a command is executed or a signal is in a certain area.

A technical solution is known (RU, 2174485, publ. 10.10.2001) related to control systems for training and combat training aircraft, in which the onboard equipment is combined into a single integrated complex through a multiplex information exchange system consisting of three information exchange channels.

The disadvantages of this technical solution include the following:

- low reliability, since in the event of a failure of the onboard digital computer system, the entire complex of onboard equipment fails due to the lack of a backup information exchange channel, which leads to the impossibility of performing the tasks of onboard radio-electronic equipment;

- the impossibility of automatic flight control in case of failure of the onboard computer system due to the lack of a backup computer in which the solution of navigation problems is implemented, and due to the lack of a backup channel for information exchange of navigation information.

Known (RU, 2488775, publ. 27.07.2013) is an integrated complex of on-board equipment of a multifunctional aircraft, containing the following systems interconnected via the information exchange channel, listed in general: , general aircraft equipment, a complex of flight and navigation equipment, a system for monitoring and recording flight parameters, a set of weapons, an integrated control system, an integrated radio engineering system, an integrated optical-electronic system, an information management system with an onboard computer system.

In this technical solution, the onboard equipment complex and the information and control system, inclusive, function only with constant interaction with the crew, which leads to the following disadvantages: the presence of information and control field systems, crew life support systems, etc. increases the weight of the electronic equipment complex, which leads to deterioration characteristics of the aircraft (reduction of payload, flight duration, maneuverability); lack of autonomy of operation (the need to involve the crew in control) leads to an increase in the load on the crew, which reduces the reliability and speed of the onboard equipment complex; implementation of backup control in case of failure of the central computer system with the participation of the crew leads to the need for manual piloting for return and landing; the need to ensure the comfort of the crew.

The technical problem solved by means of the developed complex is to create an integrated complex of onboard equipment for an unmanned aerial vehicle.

The technical result achieved by the implementation of the developed complex consists in expanding the functionality, increasing the autonomy and automation of the onboard equipment complex, increasing the reliability of the onboard equipment complex and, accordingly, increasing the efficiency of the use of an unmanned aerial vehicle by excluding the information and control field from the composition of the OBE and for due to the absence of the need for decision-making by the crew and constant participation in the control of the aircraft.

To achieve the specified technical result, it is proposed to use the developed integrated complex of on-board equipment of an unmanned aerial vehicle. It contains the following systems interconnected via the multiplex information exchange channel (MIC) and the information exchange channel (ICC):

- a complex of flight and navigation equipment (CPNO), which consists of systems integrated into the complex:

a) antenna system of space navigation systems (AS SNS);

b) inertial navigation system (INS);

c) radio navigation and landing system (RTSNP);

d) satellite navigation and landing system (SSNT);

e) radio altitude measurement systems (SRV);

- a complex of communication means (CSS), which consists of radio channels of various wavelengths integrated into the complex (the use of a separate wavelength range for each radio channel provides an increase in the reliability of pairing the integrated on-board equipment complex with a ground control point via CCC radio channels):

a) the first information and command radio link (IKRL-1), which consists of a control and interface unit (BUS), a radio station (PC), an antenna system (AS) and a video system (VS);

b) the second information-command radio link (IKRL-2), which consists of the BUS, the radio station (PC), the AC, the aircraft and the video signal processing unit (BOVS);

c) a command radio channel, which consists of a BUS, a radio station (PC) and an AU;

- information management system (IMS), which consists of the following systems:

a) on-board digital computer (BTsVM);

b) block-switching signals (BCS);

c) external storage device (VZU);

- air traffic control transponder (ATC);

- antenna system (AS);

- general aircraft equipment (OSO);

- integrated management system (CMS);

- system of control and registration of parameters (SKRP);

- flight aerometric equipment (PAO);

and providing:

- formation of automatic control signals in the ICS and their transmission to the control system via four independent channels, which is provided by:

a) integration of the IMS (two on-board computers) and the KSU using a multiplex information exchange channel (two MCIO lines)

b) integration of the IMS (two on-board computers) and KSU using an information exchange channel (two lines of a bipolar serial code according to GOST 18977-79);

- backup automatic control in case of failure of the onboard computer, which is provided by:

a) a backup channel for information exchange of navigation information;

b) automatic control of the CCS in case of failure of the onboard computer using navigation information;

- automatic decision-making on changing the purpose of the flight, which is provided by:

a) autonomous automatic decision-making in the IMS based on information from all systems of the integrated complex of on-board equipment, which comes via MCIO and CIO;

- remote manual control of flight and systems, which is provided by:

a) three radio channels of different wavelengths;

b) integration of KSS and ICS using MCIO and CIO;

c) remote piloting information exchange channel;

d) MKIO, KIO for indication support of the ground monitoring and control station;

e) a backup channel for information exchange for indicating support for a ground monitoring and control station in the event of an onboard computer failure;

- automatic landing on information about deviations from the landing path using three different physical principles:

a) radio technical glide path (deviations are formed in RTSNP);

b) satellite glide path (deviations are formed in the SSNS according to the signals of the GLONASS/GPS satellite systems using differential corrections from the ground local-correcting station);

c) estimated landing trajectory (deviations are formed in the onboard computer based on information about the current navigation parameters of the unmanned aerial vehicle).

- a set of communication facilities is integrated into the OBE, which is ensured by:

a) the use of three channels of different wave ranges, the integration of which is carried out at the expense of the information exchange channel of the KSS (KIOKSS) and at the expense of control and interface units;

b) use in the onboard computer of a block of a complex of means of exchange (CSO) to ensure the collection and transmission to the CCC of all the necessary information for monitoring and controlling the OBE and the block of input-output and exchange control;

c) the use of a remote pilot information exchange channel (KIODP) for the possibility of interfacing the KSS and the integrated control system, which provides the possibility for the crew of the ground control and management station to intervene in flight control;

d) the use of a backup information exchange channel for interfacing the OSO, BCS and other systems, which allows the crew to indicate the status of the systems and flight parameters;

- a set of flight equipment is integrated into the OBE, which is ensured by:

a) the use of a block of navigation calculations in the onboard computer to solve navigation problems;

b) the use of MCIO for the integration of KINO systems with the help of an input-output unit and exchange control;

c) using three deviations from the landing path based on different physical principles;

d) the use of a backup channel for information exchange of navigation information for the integration of KPNO and KSU in case of failure of the onboard computer;

e) the use of a backup information exchange channel for the integration of KPNO and KSS in case of failure of the onboard computer for the purpose of backup control of navigation systems;

f) use of GLONASS/GPS satellite signals;

- the information and control system is the central information and control element, which is ensured by:

a) OBE integration using MCIO and KIO from the ICS;

b) OBE integration using BCS and standby KIO in case of onboard computer failure;

c) integration of onboard computer blocks using the internal information exchange channel (VKIO);

d) the presence in the onboard computer of a mode control unit (MCU) for the coordinated control of all OBE systems and for making decisions on changing the control goal, including in case of failures of the OBE systems, as well as for autonomous automatic control in the absence of interaction with the crew;

e) the presence in the onboard computer of the block of navigation calculations (HP) for automatic flight control and for the integration of KPNO;

f) the presence in the on-board computer of the block of the concentrator of signals of exchange (CSO) for collecting and processing information that must be transferred to the ground control and management station;

g) the presence in the onboard computer of a control unit for general aircraft equipment (UOSO);

h) the presence in the on-board computer of the flight task database (BDPZ) to provide the flight task for the ICBO systems;

i) the presence in the on-board computer of an input-output and exchange control unit (VVOU) for the integration of ICBO systems for MCIO and CIO;

- an integrated management system that provides:

a) automatic control in case of failure of the onboard computer, which is ensured by integration with the KPNO via the backup KION;

b) remote piloting, which is provided by integration with the KSS on KIODP;

c) solving navigational problems in the CSS to increase the automation and autonomy of the ICBO.

The integration of the systems of the on-board equipment complex of an unmanned aerial vehicle was achieved through the formation of an integrated complex of means of communication with radio stations of various wavelengths, a complex of flight and navigation equipment, an air traffic control transponder, an integrated control system, general aircraft equipment, a control and registration system for parameters, flight aerometric equipment , as well as the functional integration of these systems in the computational logic blocks of the onboard digital computer, which is integrated into a single information and control system.

Also, due to the unmanned specifics of the aircraft, the ICBO does not have systems for the information and control field of the crew and life support systems for the crew.

The invention is illustrated with graphic material, where figure 1 shows a block diagram of the integrated complex of onboard equipment of an unmanned aerial vehicle. At the same time, the following designations are used in the figure: complex 1 of communications equipment (KSS) with radio stations of various wavelengths, consisting of:

a) the first information and command radio link 2 (IKRL-1), which consists of: AU 3 to provide radio communication with the ground control and management station, PC 4, which provides exchange between the ICSD and the ground monitoring and control station of command information, information about the state of the ICSD , information about the flight parameters and video information, BUS 5, which provides interface PC 4 with other channels of the KSS via KIOKSS 46, as well as interface with IUS 27, OSO 19, KSU 20, KPNO 21 and SKRP 40 via KIO 42, backup KIO 43 and KIODP 47, processing and transmission to the PC 4 video from the video system 6, which provides the formation of a video image and its transmission to the BUS 5;

b) the second information and command radio link 7 (IKRL-2), which consists of: AS 8 for providing radio communication with the ground control and management station, PC 9, which provides exchange between the ICSD and the ground monitoring and control station of command information, information about the state of the ICSD , information about flight parameters and video information, control and interface unit 10, which provides interface PC 4 with other channels of the KSS via KIOKSS 46, as well as interface with IUS 27, OSO 19, KSU 20, KPNO 21 and SKRP 40 via KIO 42, backup KIO 43 and KIODP 47, video system 11, which provides the formation of a video image and its transmission to the video signal processing unit (BOVS) 12, which provides processing and transmission to the PC 9 of the video image from the aircraft 11;

c) command radio channel 13, which consists of: AS 14 for providing radio communication with the ground control and management station, PC 15, which provides exchange between the ECCS and the ground control and management station of command information, information on the status of the CCBO, information on flight parameters, BUS 16 , which provides pairing of PC 4 with other channels of KSS 1 via KIOKSS 46, as well as pairing with IUS 27, OSO 19, KSU 20, KPNO 21 and SKRP 40 via MKIO 41, KIO 42, backup KIO 43 and KIODP 47;

air traffic control transponder (ATC) 17, which provides air traffic management services with information about the characteristics and position of the aircraft using AS 18, which ensures the interaction of the ICBO with ground-based navigation radio beacons, ground-based local control and correction station, ground-based air traffic management services ; general aircraft equipment (OSO) 19, which includes the following systems: power supply, fuel, fire, hydraulic system, pneumatic system, interfaced with BKS 28 according to MKIO 41 and KIO 42 and interfaced with KSS according to backup KIO 43; an integrated control system (CSU) 20, including an aircraft control system, a remote control system, a flight limit limiter, a navigation calculation unit, control system actuators; a complex of flight and navigation equipment (KPNO) 21 consisting of:

a) Antenna System for Space Navigation Systems (AS SNS) 22, which provides the KPNO systems with GLONASS/GPS satellite signals;

b) inertial navigation system (INS) 23, which generates information about the angular and spatial position of the aircraft, as well as information about the speed parameters and is interfaced via MKIO 41 with onboard computer 30, and with KSU 20, with which it is also interfaced via backup KION 44;

c) radio navigation and landing system (RTSNP) 24, which generates the navigation information of radio beacons, including during landing, and interfaces with the onboard computer 30 via KIO 42 and with KSU 20, with which it also interfaces via the backup KION 44;

d) satellite navigation and landing system (SSNP) 25, which generates information about the location, deviation from the landing trajectory by satellite signals, ensures the elimination of pseudo-range measurement errors using corrective signals (differential corrections) that are generated in the LKKS and is interfaced with the onboard computer 30 by KIO 42 and with KSU 20, which also interfaces with the backup KION 44;

e) radio altitude measurement system (SRV) 26, which generates the current radio altitude and interfaces with the onboard computer 30 via MKIO 41 and with the KSU via MKIO 41 and via the backup KION 44;

information management system (IMS) 27 consisting of:

a) signal concentrator unit 28, which is a device for receiving analog and discrete signals according to GOST 18977-79 from aircraft systems, receiving signals in digital form and outputting them in analog form to actuators and connected by inputs / outputs via MKIO 41 with BTsVM 30, as well as for the reserve KIO 43 with KSS 1 and KPNO 21;

b) an external storage device (VSD) 29, which is a device that provides input of information through a removable media from the ground training complex, its storage and issuance in the onboard computer 30 by KIO 42;

c) an onboard digital computer 30, containing: a mode control unit (BUR) 31, which provides autonomous automatic decision-making and coordinated automatic control of the ICBO systems, a navigation calculation unit (HP) 32, which provides the solution of navigation problems, a general aircraft equipment control unit (UOSO) 33, the flight mission database (BDPZ) 34, which provides information reception from the VZU, storage and distribution to consumers, the exchange signal concentrator unit (CSO) 35, which ensures the collection, processing and issuance of information packets for indication support in the CCC, and also provides multi-channel interface KSS and on-board computer, maintenance unit (TECHO) 36, which provides ground control of onboard equipment, control and status indication unit (KIS) 37, which provides flight control of onboard equipment, control unit for recording on the means of objective control (UZSOK) 38, input-output unit and exchange management (VVOU) 39, providing and information exchange on MKIO 41 and KIO 42, internal channel of information exchange (VKIO) 48, providing information interaction between blocks of onboard computer; system for monitoring and recording parameters (SCRP) 40, which provides registration of parameters from on-board systems; flight aerometric equipment (PAO) 45, which provides the formation of flight parameters and interface with IUS 27 and KSU 20 according to KIO 42.

The multiplex information exchange channel (MCIO) 41 provides the interface of the ICBO systems with the onboard computer, and the information exchange channel (CIO) 42 provides the interface of the ICBO systems with the onboard computer. The use of MKIO 41 and KIO 42 is necessary to improve the reliability of pairing of ISBO systems by using two different types of interfaces (MKIO is a network interface using a common bus, and KIO is a point-to-point interface), as well as to redundant pairing of ISBO systems in case of failure MKIO 41 (pairing is duplicated by KIO 42).

Reserve channel of information exchange (res. KIO) 43, provides interfacing of systems with KSS 1 in case of failure of onboard computer 30, reserve channel of information exchange of navigation information (res. KION) 44, provides interfacing of KPNO 21 with KSU 20 in case of failure of onboard computer 30, channel of information exchange remote control (KIODP) 47 provides interfacing KSS 1 with KSU 20 for remote control of the aircraft using ground control and management.

The integrated complex of onboard equipment functions as follows:

The communication facility 1 provides interface of the integrated on-board equipment complex with the ground monitoring and control station via radio channels of the first information and command radio line 2, the second information and command radio line 7 and the command radio channel 13. This interface is necessary for the ground station crew to perform the functions of monitoring and controlling an unmanned aerial vehicle device and ensures the transmission of the following parameters from the ICBO to the ground monitoring and control station:

- parameters of operation and parameters for monitoring the status of the integrated complex of onboard equipment, general aircraft equipment 19 and the integrated control system 20;

- navigation and flight parameters of the unmanned aerial vehicle;

- signs of execution of control commands received from the ground control and management station;

- video information from video systems 6 and 11.

Also, this interface provides transmission from the ground monitoring and control station to the OBE and KSU 19 signals and commands to control the flight of an unmanned aerial vehicle and OBE systems, which are formed by the crew. Wherein:

KSS 1 provides pairing via radio channels as follows:

The control and interface units 5, 10, 16 in each of the channels ensure the interface of the OBE, OSO 19 and KSU 20 systems with KSS 1 according to MKIO 41, KIO 42, Res. KIO 43 and KIODP 47 for broadcasting parameters from systems to radio stations 4, 9, 15, where these parameters are converted into a high-frequency signal that is emitted through antenna systems 3, 8, 14 for transmission to a ground monitoring and control station.

- Reception of radio signals from the ground monitoring and control station is carried out in the reverse order: AS 3, 8, 14 receive radio signals and transmit them in high-frequency form to radio stations 4, 9, 15, where they are converted and broadcast through the BUS 5, 10, 16 in systems ICBO, OSO 19 and KSU 20 according to MKIO 41, KIO 42, Res. KIO 43 and KIODP 47.

Also, the channels IKRL-1 2 and IKRL-2 7 provide the formation and transmission of video information to the ground monitoring and control station. In the IKRL-1 channel, the video system 6 generates video information and transmits it to the BUS 5 for further processing and transmission to PC 4. In the IKRL-2 channel, the VS 11 generates video information and transmits it to the video signal processing unit 12 for processing and transmission to PC 9.

Improving the reliability of the functioning of the KSS 1 is ensured through the use of three radio channels: IKRL-1 2, IKRL-2 7, command radio channel 13. These radio channels operate independently, internal KIOKSS 46 is used for internal exchange of parameters between the radio channels and status monitoring. Also, the reliability of the functioning of the KSS 1 increases due to the use of radio channels 2, 7, 13 of different wavelengths. In the exemplary embodiment of the invention, this is represented as: IKRL-1 uses PC 4 centimeter wavelengths, IKRL-2 integrates PC 9 decimeter wavelengths, and CR 13 uses PC 15 meter wavelengths. The transmission of remote piloting signals from the KSS 1 directly to the KSU 20 is carried out via KIODP 47.

The complex of flight and navigation equipment 21 provides the formation of flight and navigation parameters and their transfer to the KSU 20 and onboard computer 30 for traffic control and for navigation calculations according to MKIO 41, KIO 42 and Res. KION 44.

The antenna system of space navigation systems 22 provides for the reception and transmission of navigation signals from satellites to the navigation systems.

The inertial navigation system 23 provides the determination of navigation and flight parameters (information about the angular and spatial position of the aircraft).

The radio navigation and landing system 24 provides determination of directions to radio beacons, as well as determination of deviations from the landing trajectory according to information from radio ground systems. Information from radio ground systems is received by AS 18 and broadcast to RTSNP 24.

The satellite navigation and landing system 25 provides the formation of deviations from the landing trajectory according to information from satellite navigation systems and taking into account corrections from ground corrective stations. Corrections from ground correction stations are broadcast to SSNP 25 via AS 18.

The radio altitude measurement system 26 determines the flight altitude relative to the earth's surface.

The KPNO 21 systems are interfaced with the onboard computer 30 according to MKIO 41 and KIO 42. To provide the KSU 20 with navigation and flight information in case of failure of the onboard computer 30, the interface of the KPNO 21 systems with the KSU 20 according to Res. KION 44. Res. KIO 43 from KSS 1.

The air traffic control transponder 17 provides air traffic management services with information about the characteristics and position of the aircraft using AC 18, which provides transmission of signals from ATC 17 to ground services via a radio channel.

The system for monitoring and recording parameters 40 ensures the registration of the parameters of the operation of on-board complexes and individual systems, the actions of the crew for their use, as well as the preservation of information about the flight parameters and the operability of the aircraft systems. Information for registration and recording is transmitted to SKRP 40 via MKIO 41 and via KIO 42.

Flight-aerometric equipment 45 provides the formation of flight-aerometric parameters (true angles of attack and slip, absolute and relative height, instrumental and true speed, vertical baro-inertial speed). These parameters are transmitted via KIO 42 to the KSU 20 and are used to control the movement of the aircraft.

General aircraft equipment 19 includes power supply systems, a fuel system, a hydraulic system, power plant systems that perform general aircraft functions of providing power, hydraulic power for steering gears, aircraft engine operation, etc. OSO 19 interfaces with IUS 27 for monitoring and control of MKIO 41 and KIO 42, as well as to provide backup monitoring and control in case of failure of the on-board computer 30 with KSS 1 according to Res. KIO 43.

The integrated control system 20 provides control of the movement of the aircraft by signals from the on-board computer 30 (aircraft control system function) or by remote piloting signals from the crew (remote control function) by generating and transmitting control signals to the actuators of the control system. Traffic control is carried out taking into account the limitations of the limiting flight modes and navigation calculations. To improve the reliability of traffic control in KSU 20, a block of navigation calculations is partially implemented (to solve the navigation problem in case of failure of the onboard computer), which is provided with navigation information from KPNO 21 according to Res. KION 44. Also, motion control is provided by the HP 32 unit in the onboard computer 30, the parameters from which are transmitted to the KSU 20 via the MKIO 41 and KIO 42. KSS 1 is carried out according to KIODP 47.

Information and control system 27 is designed for functional, logical information and software linkage of OBE and OSO systems into a single integrated system.

The signal concentrator 28 from the IMS 27 provides the conversion of information received from the onboard equipment: analog to digital format, digital to analog format, and also for converting digital information into power electrical signals. BCS 28 is used to convert to the required form (conversion from analog to digital) and broadcast signals from onboard systems to onboard computer 30 to ensure its operation, as well as to control onboard systems using power control commands (conversion of digital control commands to analog signals) . Pairing of BCS 28 with onboard computer 30 is provided by MKIO 41, pairing of BCS 28 with on-board systems is provided by KIO 42.

VZU 29 provides the input of the flight mission database into the onboard computer 30 using a memory module that is connected to the VZU 29.

The onboard digital computer 30 is the main computing core of the integrated complex of onboard equipment and ensures the integration of OBE systems into a single complex through the use of BUR 31, HP 32, UOSO 33, BDPS 34, KSO 35, TECHO 36, KIS 37, UZSOK 38, VVOU 39 The interfacing of blocks 31-39 is provided by means of an internal communication channel 48 for their functional integration.

BUR 31 is designed for the coordinated performance of the current task by all ISCS systems by assigning operating modes for the onboard equipment complex, as well as for automatic decision-making on the management of ISCS. To perform these tasks, the BUR 31 receives the necessary information about the flight parameters from HP 32, about the state of the onboard systems from the CIS 37 and TECHO 36 using the VKIO 48. Also, the current mode of operation of the ICBO and its changes are transmitted to the onboard systems through the VVOU 39.

The navigation calculations unit 32 is designed to control the CPNO 21 systems (integration of navigation systems) and to provide traffic control in accordance with navigation information and in accordance with the flight task, as well as to generate processed navigation information for the crew of the ground control and management station. Flight mission parameters are transmitted from BDPZ 34, navigation parameters are transmitted from KPNO 21 through VVOU 39 and the parameters that provide traffic control are transmitted to KSU 20 through VVOU 39. The processed navigation information is transmitted to KSS 1 through KSO 35. Also, the functions of the HP block 32 are partially redundant in KSU 20 for traffic control in case of failure of on-board computer 30, this redundancy is provided by pairing KSU 20 and KSP 21 via backup KION 44 (providing KSU 20 with navigation information from KPU 21) and by pairing KSU 20 and KSS 1 via backup KIO 43 ( providing the crew of the ground station for monitoring and managing the processed navigation information).

The general aircraft equipment control unit 33 provides control of the OSO 19 systems, taking into account the navigation parameters from HP 32 and taking into account the state of the OSO systems from KIS 37 and TECHO 36.

The flight task database 34 provides for the reception of the flight task from the VZU 29, its storage and issuance to consumers for work. The flight task is used to provide traffic control in HP 32 and in KSU 20, as well as to set up OBE systems in KSS 1, KPNO 21 and SO ATC 17.

KSO 35 provides collection from BUR 31, HP 32, TECHO 36, KIS 37, from OBE, OSO 19 systems, processing and transmission to KSS 1 of information packets to ensure the formation of an indication to the crew at the ground control and management station. Also, KSO 35 provides multi-channel interfacing between KSS 1 and onboard computer 30, which allows you to reserve the transmission of information from the ground control and management station and the processing of information received from KSS 1.

The TEXO 36 block provides extended ground control of the UAV onboard systems by assigning a control mode in a separate system with subsequent collection and processing of the control results in TEXO 36. TEXO 36 sends commands to onboard systems and receives control results through VVOU 39. For the coordinated execution of the TEXO control task 36 interacts with BUR 31.

Block CIS 37 collects information about the state of on-board systems through VVOU 39 (flight control parameters), analyzes information about the state of on-board systems and transfers the results of the analysis to KSO 35 for subsequent indication at the ground control and management station. Also, the results of the analysis of the state of the onboard systems are transmitted to the BUR 31 to ensure the management of the ICBO depending on the state of the onboard equipment.

Block UZSOK 38 collects the parameters of the onboard computer 30, including the parameters of the blocks 31-37 and 39, for their further transmission to the SCRP 40 for registration and recording.

VVOU 39 provides for the organization of the exchange between on-board systems via MKIO 41, and also provides for the reception of information from on-board systems and the transmission of information from on-board computer 30 to on-board systems via KIO 42.

Qualitative improvements of the on-board equipment complex in comparison with analogues are provided due to:

- increasing the level of integration and automation in the onboard computer 30 and the implementation of the remote piloting channel KIODP 47, which makes it possible to exclude the information and control field systems from the OBE and the crew life support system;

- redundancy of the functions of the navigation calculation unit in the onboard computer 27 and KSU 20, which makes it possible to implement backup automatic control in case of failure of the onboard computer 27 without the need for crew intervention, but with the preservation of control functions through the use of Res. KIO 43 and Res. KION 44;

- the use of landing systems based on different physical principles (for example, the deviation from the landing trajectory is formed using signals from ground-based radio systems in RTSNP 24 and using signals from satellite navigation systems in SSNP 25), which improves the accuracy and reliability of the formation of navigation information .

Claims (1)

An integrated complex of on-board equipment of an unmanned aerial vehicle, characterized in that it contains systems interconnected via a multiplex information exchange channel and an information exchange channel (IEC): a complex of flight and navigation equipment as part of an antenna system of space navigation systems, an inertial navigation system, a radio navigation system and landing, satellite navigation and landing system and radio altitude measurement system; a complex of means of communication with radio channels of various wavelength ranges as part of the first information and command radio link, including the first control and interface unit, a radio station, the first antenna system and the first video system, the second information and command radio link, including the second control and interface unit, a radio station, a second antenna a system, a second video system and a video signal processing unit, and a command radio channel including a third control and interface unit, a radio station and a third antenna system; an information management system including an onboard digital computer (OCVM), a block signal switch and an external storage device; general aircraft equipment; integrated system of automatic traffic control; a system for monitoring and recording flight parameters and the operation of onboard equipment; and also contains interconnected, complexes and on-board computers for CIO, flight aerometric equipment and an aircraft air traffic control transponder with an antenna system that provides interaction with air traffic control bodies, reception of differential correction data from a ground station, measurement of deviations from the center of the equisignal zone of the spatial radio field .

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