RU2205441C1 - Test complex for check of on-board systems of unmanned flying vehile - Google Patents

Test complex for check of on-board systems of unmanned flying vehile Download PDF

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RU2205441C1
RU2205441C1 RU2001135655/09A RU2001135655A RU2205441C1 RU 2205441 C1 RU2205441 C1 RU 2205441C1 RU 2001135655/09 A RU2001135655/09 A RU 2001135655/09A RU 2001135655 A RU2001135655 A RU 2001135655A RU 2205441 C1 RU2205441 C1 RU 2205441C1
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Russia
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control
device
input
connected
output
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RU2001135655/09A
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Russian (ru)
Inventor
В.А. Никольцев
Г.А. Коржавин
И.В. Симановский
Ю.Ф. Подоплёкин
Е.А. Войнов
Е.А. Горбачев
Л.Ю. Григорьев
Д.И. Буравлев
Ю.Ф. Парамонов
В.А. Пеклер
Г.А. Ефремов
В.П. Царев
А.И. Бурганский
А.Г. Леонов
С.Н. Зимин
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Федеральное государственное унитарное предприятие "Центральный научно-исследовательский институт "Гранит"
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Abstract

FIELD: complex monitoring and test systems; ground monitoring of on-board systems of unmanned flying vehicles. SUBSTANCE: proposed complex includes target simulator, check antenna connected with antenna of radar sight of unmanned flying vehicle, switch gear, control system monitoring unit, electrical equipment monitoring unit, self-check unit, local net concentrator, control console and guaranteed power supply source. EFFECT: extended functional capabilities; enhanced reliability of tests. 9 dwg

Description

 The invention relates to integrated test systems, and in particular to systems for ground monitoring of the health of onboard systems of unmanned aerial vehicles equipped with an autonomous control system based on computing facilities and a radar sighting device.

 A device for ground monitoring of radar control systems [1], including a radar control system connected through a device to the registration device, a group of simulators reproducing a probing signal, a leading signal, an aiming signal, a multiple signal and a noise signal, as well as calculators of control signals, signals executive devices and navigation signals, control and switching unit and control unit.

 A disadvantage of the known device is the limited functionality that does not allow the device to be used for comprehensive verification of all on-board systems of an unmanned aerial vehicle.

 The closest in execution analogue, adopted as a prototype of the invention, is a modeling complex for ground testing of the control system of an unmanned aerial vehicle (UAV) [2]. The complex contains real UAV control system equipment as part of a radar sighting device, angle and speed sensors, steering mechanisms and a control signal generation device, as well as simulation equipment including a target simulator with a control antenna connected via a radio channel to a radar sighting antenna and a control panel equipped with a calculator and an information display device.

 The disadvantage of the prototype complex is the lack of control equipment for the electrical equipment and the UAV telemetry system and the limited capabilities of one computer used in the control panel, in terms of increasing the volume of control and testing and test programs, which does not allow for a comprehensive check of the health of all UAV systems.

 The objective of the utility model is to expand the functionality while ensuring high reliability of the results of a comprehensive check of unmanned aerial vehicle systems in automatic mode.

 To achieve the claimed technical result, a device has been introduced into the complex for checking on-board systems of an unmanned aerial vehicle (UAV), which contains a target simulator with a control antenna connected via a radio channel to an antenna of a UAV radar sighting radar and a control panel configured to set up a verification program and display information guaranteed power supply, a switching device including a switch for control points, a command switch and a signal switch, as well as integrated e to a local area network with a control panel through interface lines of information exchange and a hub of a local network, a control system control device, an electrical equipment control device and a self-control device, each of which contains a secondary power supply connected to the output of the guaranteed power supply device and an electronic computer (computer ), to the system input-output of which a monitoring device, adapter is connected via the system interface line a local network connected to the corresponding interface highway of information exchange, a discrete input-output device connected to the input with the output of the galvanic isolation device, and the first output to the input of the command transmitter, the outputs of the monitoring devices of the control system control system, electrical control devices and self-monitoring devices are connected to the input of the serial interface of the interface conversion device, which is part of the control panel and connected to the central The first computer, to which the keyboard, documentation device and external storage device are also connected, the corresponding interface bus of the information exchange is connected to the network input-output of the central computer, and the system interface bus to which the discrete input-output device is connected, connected to the panel input control, and the output - with an indicator board, in addition to the multiplex channel adapter connected to the system interface line of the control device of the control system, Through which there is an information exchange with the computing devices of the UAV control system, and an analog-to-digital conversion device, the input and control output of which is connected respectively to the output and the address of the information channel of the multiplexer, to the input of which signals from the UAV telemetry device are supplied, to the second output of the discrete device the input / output of the control device of the control system is connected to the target simulator switching unit, connected by the output to the control input of the target simulator, op The input of which serves to receive the reference frequency signal from the UAV radar sighting device, in addition to the aforementioned electrical control device, contains a control point switch, the control input of which is connected to the second output of the discrete input-output device of the electrical control device, and the output to the input of the resistance and potential measurement device the output of which is connected to the system interface bus of the electrical control device, except for the aforementioned device Amocontrol contains a multiplex channel adapter connected to its system interface bus, which in self-monitoring mode connects to the input-output of the multiplex channel adapter of the control system control device, as well as a potential simulator and message simulator connected to a crossover device, the output of which is connected to the second input of the control switch points, the first input of which is used to connect the connecting circuits from the control points of the UAV electrical equipment, and the output is connected about the input of the switchboard of control points of the control device of electrical equipment, the outputs of the command transmitters of the control device of electrical equipment and the control system of the control system are connected to the input of the command switch, the second output of which is connected to the input of the galvanic isolation of the self-control device, the output of the transmitter of the commands of the self-control device is connected to the second input of the signal switch, to the output of which the inputs of galvanic isolation devices of the electrical control device are connected control devices, control system, the second output of the discrete input-output device of the self-control device is connected to the control inputs of the control point switch, command switch and signal switch, while signals are generated at the first output of the command switch that control the relay devices of the UAV onboard systems, and the response the signals of the corresponding actuators onboard UAV systems are transmitted to the first input of the signal switch.

The invention is illustrated by drawings, on which:
figure 1 - structural diagram of the complex,
figure 2 is a generalized structural diagram of the on-board systems of an unmanned aerial vehicle,
figure 3 is a structural diagram of a switching device,
4 is a structural diagram of a target simulator,
5 is a structural diagram of a control device of a control system,
6 is a structural diagram of a control device for electrical equipment,
Fig.7 is a structural diagram of a device for self-control,
Fig. 8 is a block diagram of a guaranteed power supply device,
Fig.9 is a structural diagram of a control panel.

In FIG. 1 structural diagram of the complex for testing onboard UAV systems adopted the following notation:
1 - control antenna
2 - object of verification (UAV),
3 - switching device,
4 - target simulator
5 - control system control system,
6 - control device for electrical equipment,
7 - self-monitoring device,
8 - guaranteed power supply device,
9 - a LAN hub,
10 - remote control
11, 12, 13, 14 - interface communication lines made in the form of Ethernet lines,
15 - interface highway multiplex channel information exchange (Manchester),
16, 17, 18 - interface highway serial data channel (RS 485),
19 - cable relay channel communication with the telemetry device,
20 - cable connecting circuits for connecting to control points of electrical equipment,
21 - cable transmitting relay channel
22 - cable receiving relay channel.

 According to FIG. 1 control antenna 1, structurally integrated with the target simulator 4, is connected by a radio channel to UAVs 2, namely, to the antenna of the radar sight of the UAV control system. The first input, the first and second outputs of the UAV 2 are structurally designed as an onboard connector, to which are connected: cable 21 of the relay relay channel connected to the first output of switching device 3, cable 20 of connecting circuits for connecting to control points of electrical equipment connected to the first input of device 3 switching, and a cable 22 of the receiving relay channel connected to the second input of the switching device 3, respectively.

 The third output of the UAV 2, from which the reference frequency signal of the radar sight is transmitted, is connected to the reference (Op) input of the target simulator 4, the fourth input-output is connected to the third input-output of the control system control device 5 via the interface highway 15 of the multiplex information exchange channel, and the fifth output through the cable 19 of the relay channel of communication with the telemetry device is connected to the second input of the control device 5 of the control system.

 The input of the guaranteed power supply device 8 is connected to a source of mains voltage (network), and the output to the power inputs (Pit) of devices 5, 6, control systems and electrical equipment, self-monitoring device 7 and control panel 10.

 The input of the serial interface of the control panel 10 is connected via interface lines 16, 17 and 18 of serial channels to the outputs of the serial interface of the control system control device 5, electrical equipment control device 6 and self-control device 7, connected to the control panel 10 by means of interface lines 11, 12, 13 and 14 of information exchange connected in a hub 9 of the local network according to the "star" scheme.

 The second output of the control system control device 5 is connected to the control input (U) of the target simulator 4, and its first output and the output of the electrical control device 6 are connected to the third input of the switching device 3, the second output of which is connected to the second input of the electrical control device 6, and the third - with the first inputs of devices 5 and 6 of the control system control and electrical equipment.

 The first, second and third outputs of the self-monitoring device 7 are connected respectively to the fourth input, the control input (U) and the fifth input of the switching device 3, the fourth output of which is connected to the first input of the self-monitoring device 7. The fourth input-output of the device 7 self-monitoring is the input-output of the multiplex channel of information exchange.

In FIG. 2 generalized structural diagram of the onboard UAV systems adopted the following notation:
23 - antenna radar sight,
24 - control system, including a radar sight, angular velocity sensor, inertial unit and a device for generating control signals based on an onboard computer,
25 is a telemetry device,
26 - electrical equipment UAV (hereinafter - electrical equipment),
27 is a crossover device made in the form of a set of terminal boards with mounting jumpers,
28 - steering units.

 According to figure 2, the antenna 23 is connected to the control system 24, namely with a radar sighting device, the output of which on the reference frequency signal forms the third output of the UAV 2. The input-output of the on-board computer of the control system 24 forms the fourth input-output of the UAV 2, and the output of the generating device control signals of the control system 24 is connected to the input of the steering units 28. The inputs of the telemetry device 25 according to the signals of the controlled parameters are connected to the outputs of the electrical equipment 26 and the control system 24, and its output forms the fifth output of the UAV 2.

 The chains from the control points of the electrical equipment, as well as the input and output signal circuits of the relay devices of the control system 24, electrical equipment 26 and steering units 28 are connected to the corresponding terminals of the crossover device 27, the three external outputs of which form the first and second outputs and the first input of the UAV 2 airborne connector.

 The switching device 3 comprises a switch 29 of the control points, a switch 30 of the commands and a switch 31 of the signals, made in the form of the same relay blocks, controlled by a parallel on-off code, supplied to the control inputs of the switches 29, 30 and 31 through the control input of the switching device 3. An example of the implementation of switches 29, 30, 31 is the Advantech PCLD-785 relay switching board.

 The first and second inputs of the switch 29 of the control points are connected respectively to the first and fifth inputs of the device 3 switching, and its output forms the second output of the device 3 switching, the third output of which is the output of the switch 31 of the signals.

 The first and second inputs of the signal switch 31 form respectively the second and fourth inputs of the switching device 3. The third input of the switching device 3 is the input of the command switch 30, the first and second outputs of which form the first and fourth outputs of the switching device 3, respectively.

 The control inputs (Upr) of the switches 29, 30 and 31 are connected to the control input (U) of the switching unit 3.

In figure 4 of the structural diagram of the simulator 4 goals are indicated:
32 - circulator
33 - the first frequency Converter,
34 - the first intermediate frequency amplifier (IFA),
35 - delay line
36 - the second UPCH,
37 is a second frequency converter.

 The first arm of the circulator 32 is connected to the control antenna 1, the second to the signal input of the first frequency converter 33, and the third to the output of the second frequency converter 37, the reference input of which and the reference input of the first frequency converter 33 are connected to the reference input of the target simulator 4. The output of the first frequency converter 33 through a series-connected first converter 34, a delay line 35 and a second converter 36 are connected to the signal input of the second frequency converter 37. The inputs of the reference voltage supply UPC 34 and 36 are connected to the control input of the simulator 4 of the target.

In FIG. 5 structural diagrams of the device 5 control control system are indicated:
38 - block enable the simulator of the target, made, for example, in the form of a relay switching board PCLD-885 from Advantech,
39 - multiplex channel adapter,
40 - multiplexer, made, for example, in the form of a signal switch PCLD-788 from Advantech,
41 - transmitter commands, made, for example, in the form of a relay switching module 5610 firm OCTAGON SYSTEMS,
42 - discrete input-output device, made, for example, in the form of a board type PCI-1753 company Advantech,
43 - galvanic isolation device, made, for example, in the form of a discrete input module 70L-IDC company Grayhill,
44 - a computer made on the basis of the processor board RSA-6168E firm Advantech,
45 - monitoring device (PCL-752 board), including a processor, built-in watchdog timer for monitoring the computer processor, galvanic isolation device, redundant power supply, RS-485 serial port and an audible alarm indicator,
46 - LAN adapter,
47 - a secondary power source, for example, type RPS 300 company Advantech,
48 - system interface highway (SIM),
49 is a device for analog-to-digital conversion (ADC), for example, type PCL-818HG.

 According to FIG. 5, computer 44 is connected to SIM 48, a LAN adapter 46 connected to the data exchange interface line 11, a monitoring device 45 connected to the serial line interface line 16, a multiplex channel adapter 39 connected to the data exchange multiplex channel interface line 15, device 49 ADC and discrete input / output device 42.

 The input of the galvanic isolation device 43 is the first input of the control system control device 5, and its output is connected to the input of the discrete input-output device 42, to the first and second outputs of which are connected a command transmitter 41 and a target simulator switching unit 38, the outputs of which form the first and the second outputs of the device 5 control control system.

 The information input of the multiplexer 40 forms the second input of the control system control device 5, and its output and the input of the information channel address (A) are connected respectively to the input and control output of the ADC device 49.

 The secondary power source 47 is connected to a power input of the control device 5 of the control system. The power distribution diagram is not shown for simplicity.

In FIG. 6 structural diagrams of the device 6 control electrical equipment indicated:
50 - transmitter commands
51 - device discrete input-output,
52 - device galvanic isolation,
53 - computer
54 is a monitoring device,
55 - LAN adapter,
56 - source of secondary power,
57 - system interface highway,
58 - switch point control, made in the form of a PCLD-788 card company Advantech,
59 - a device for measuring resistances and potentials,
60 - resistance to DC voltage converter (hereinafter referred to as the converter),
61 is a block of analog normalizers, made in the form of a module 56M5V41 company DATA FORTH,
62 - input switch (PCLD-785 card from Advantech),
63 - analog signal analyzer (PCL-1800 board from Advantech).

 According to FIG. 6, a computer 53, an analog signal analyzer 63, a local area network adapter 55 connected to the data exchange interface line 12, a monitoring device 54 connected to the serial line interface line 17, and a digital input / output device 51 are connected to SIM 57.

 The input of the device 52 galvanic isolation is the first input of the device 6 control of electrical equipment, and its output is connected to the input of the device 51 discrete input-output, to the first and second outputs of which are connected respectively the input of the transmitter 50 commands and the control input of the switch 58 control points. The output of the transmitter 50 teams and the input of the switch 58 control points form, respectively, the output and second input of the device 6 control electrical equipment. The outputs of the switch 58 of the control points are connected to the inputs of the Converter 60 and the block 61 of the analog normalizers, the outputs of which through the switch 62 are connected to the signal input of the analyzer 63 of the analog signals, the control output of which is connected to the control input (U) of the switch 62, and the information output is connected to SIM 57 .

 A secondary power source 56 is connected to a power input of the electrical equipment control device 6.

In Fig.7 structural diagrams of the device 7 self-control indicated:
64 - discrete input-output device,
65 - transmitter commands
66 - galvanic isolation device,
67 - computer
68 - LAN adapter,
69 is a monitoring device,
70 - multiplex channel adapter,
71 - a source of secondary power,
72 - potential simulator (DC source), made, for example, in the form of an NLP25 module from ARTESYN Technology,
73 - message simulator, made in the form of a circuit board with a set of jumpers to simulate connections between control points,
74 - crossover device,
75 is a system interface bus.

 According to FIG. 7, a computer 67, a local area network adapter 68 connected to the data exchange interface highway 13, a monitoring device 69 connected to the serial communication interface line 18, a multiplex channel adapter 70, the input-output of which forms the fourth input-output of the self-monitoring device 7, are connected to SIM 75; , and discrete input / output device 64.

 The input of the isolation device 66 is the first input of the self-monitoring device 7, and its output is connected to the input of the discrete input-output device 64, the first output of which is connected to a command transmitter 65, the output of which is the first output of the self-monitoring device 7. The second output of the self-monitoring device 7 is the second output of the discrete input-output device 64, and the third is the output of the crossover device 74, to which a potential simulator 72 and a message simulator 73 are connected.

 The secondary power source 71 is connected to a power input of the self-monitoring device 7.

On Fig device 8 guaranteed power indicated:
76 1 , ..., 76 n + 1 - uninterruptible power supplies,
77 - control panel,
78 - controller
79 - phase synchronizer.

The guaranteed power supply device 8 is made in the form of a module (based on the constituent elements of the US 9001 system of RK Electronics), including a set of n + 1 uninterruptible power supply sources (UPS) 76, where n is the minimum number of sources corresponding to power consumption. The first inputs of the sources 76 are connected to the primary network, and the outputs are connected to the corresponding inputs from the first to the (n + 1) th phase synchronizer 79, which ensures the parallel operation of the sources 76 for the total load. The third inputs of the corresponding sources 76 1 , ..., 76 n + 1 are connected to the corresponding outputs from the first to the (n + 1) th controller 78, under the control of which the backup source 76 n + 1 is replaced instead of the failed one. The control panel 77, containing manual control buttons and indicators, is connected by the corresponding outputs from the first to (n + 1) th with the second inputs of the sources 76 1 , ..., 76 n + 1 .

In Fig.9 structural diagram of the remote control 10 are indicated:
80 - a central computer, made in the form of a panel computer with a built-in display, for example, type IPPC-9150T company Advantech,
81 - keyboard
82 - external drive,
83 - documenting device,
84 - a device for converting interfaces RS 485/232, for example, type ADAM4520 company Advantech,
85 - discrete input-output device,
86 - system interface highway,
87 - control panel, made in the form of a front panel with buttons for manually entering control commands,
88 - indicator board,
89 - a source of secondary power supply.

 According to FIG. 9, a keyboard 81, an external storage device 82, a documenting device 83 and an interface conversion device 84 are connected to the corresponding inputs of the central computer 80, the serial interface input of which is connected to the interface channels 16, 17, 18 of the serial channels. An information exchange interface line 14 is connected to the network computer input 80, and a discrete input-output device 85 is connected to the system via SIM 86 and connected to the control panel 87 by the input and output from the indicator board 88. The secondary power supply 89 is connected to the console power input 10 controls.

 The complex for checking on-board systems of an unmanned aerial vehicle operates as follows.

 Checked unmanned aerial vehicle 2 is located near the equipment of the complex at a distance determined by the length of the connecting cables. Directly on the UAV case, in front of the antenna 23 of the radar sight, a control antenna 1 is mounted structurally integrated with the target simulator 4. The cable 20 of the connecting circuits and the cables 21 and 22 of the transmitting and receiving relay channels are connected through the UAV 2 side connector to its cross-linking device 27, the data exchange multiplex channel cable 15 is connected to the corresponding connector of the control system 24, the cable 19 is connected to the output connector of the telemetry device 25, and the reference input of the target simulator 4 is connected to the corresponding connector of the radar sight of the control system 24.

The device 8 guaranteed power is supplied from existing at the place of operation of the complex of primary sources of electricity. In this case, the device 8 provides stable values of the output parameters regardless of the presence of noise and voltage surges of the input network. In the event of failure of any of the sources 76 1 , ..., 76 n, its operational replacement is automatically ensured by the backup source 76 n + 1 . The presence of 76 batteries in the sources guarantees the power supply of the equipment of the complex even when the primary network is completely disconnected for a time sufficient to save the files and correctly turn off the computers.

By means of the remote control 10, the following operations are performed:
manual turning on of the equipment by the operator using the buttons of the control panel 87, after which the keyboard 81, the computer display 80, and the documenting device 83 provide the possibility of using standard operating system tools for effective interaction with the operator in each of the provided complex operation modes;
initial testing of the central computer 80 and computer 44, 53, 67 of devices 5, 6 and 7;
initial loading of basic and technological software from external drive 82 (hereinafter, the external drive can be used to adjust the software and mathematics when changes occur during operation of the complex).

 The equipment of the control panel 10 provides control of the control process, coordination of the operation of all equipment of the complex, visual display of the control process, its intermediate and final results, documentation of the results of the control, emergency power outage, work as an expert system.

 The software and mathematics are located on flash disks of computers 44, 53, 67. Coordination of the devices 5, 6 for controlling the control system and electrical equipment and devices 7 for self-monitoring is provided by the central computer 80, which is connected by an interface highway 14 to a hub 9 of the local network connected via interface highways 11, 12, 13 and adapters 46, 55, 68, respectively, with computers 44, 53 and 67. Continuous monitoring of the state of the computing systems of devices 5, 6 and 7 is carried out by monitoring devices 45, 54 and 69, connected on the basis of RS-485 interface with a central computer 80.

 The structure of the devices that ensure during the UAV test 2 the issuance of control commands to the relay devices of the on-board systems and the reception of response signals from the actuators is identical and is represented by relay transmitters 41, 50 and 65 of the commands and devices 43, 52 and 66 of galvanic isolation, which interact through the devices 42, 51 and 64 of discrete input-output with computers 44, 53 and 67.

 During the test, the operator sets one of the main operating modes with the buttons of the control panel 87: regular monitoring of the UAV on-board systems or self-monitoring of the complex. Each mode can be performed in full or with restrictions. After selecting the mode from the keyboard 81, the initial data corresponding to the characteristics of the equipment under test are entered.

When operating in the standard control mode, there is no control signal at the control input of the switching device 3, and the switches 29, 30, 31 are set to the first position in which:
the first input of the switch 29 of the control points is connected to its output, providing a connection of the first output of the UAV 2 with the input of the switch 58 of the control points of the device 6 control electrical equipment;
the input of the command switch 30 is connected to its first output, providing the connection of the outputs of the transmitter 41 commands of the control device 5 of the control system and the transmitter 50 commands of the device 6 control of electrical equipment with the first input of the UAV 2;
the first input of the signal switch 31 is connected to its output, providing a connection to the second output of the UAV 2 with the input of the galvanic isolation device 43 of the control system control device 5 and the input of the galvanic isolation device 52 of the electrical control device 6.

 In the standard control mode, a check is first performed of the UAV electrical systems using the electrical control device 6. The health check of relay devices of electrical equipment 26 is carried out by issuing control commands, which are generated at the corresponding outputs of the transmitter 50 teams in the form of DC voltages and received through the switch 30 commands on the cable 21 of the transmitting relay channel to the crossover device 27, through which are distributed to the corresponding relay devices of electrical equipment 26 . The response signals of the respective actuators through crossover device 27 via cable 22 of the receiving relay channel enter the first input of the switch 31 signals, from the output of which are transmitted to the corresponding inputs of the device 52 galvanic isolation device 6 control electrical equipment.

 Using the device 59 for measuring resistances and potentials, the presence or absence of connections between the control points of the electrical equipment, as well as the potential values of the control points are monitored. The choice of a combination of the tested points for monitoring the resistances and measuring the potentials is made by a control signal supplied to the control input of the switch 58 of the control points from the second output of the discrete input-output device 51. Then, in the converter 60, the resistance values between the selected test points are converted to a DC voltage, which, if there is a corresponding control signal at the input of the switch 62, is fed to the information input of the analog signal analyzer 63. The selected control points at which potentials are to be measured are connected to the block of normalizers 61, which provide galvanic isolation of the circuits, and from it through the switch 62 they are connected to the analyzer 63. The analyzer 63 is a high-speed meter based on analog-to-digital converters and input signal comparators. In the case of the appearance of unacceptably high potentials at controlled points, a reaction of the comparators of the analyzer 63 occurs, which interrupts the computer processor 53 and, as a result, removes power from the on-board devices.

 The next stage of staff control is to check the health of the control system 24, which is performed by the control device 5 of the control system. In this case, the check of the relay devices of the control system 24 is carried out similarly to the check of the relay devices of the electric equipment 26 using the transmitter 41 connected via the command switch 30 to the cable 21 of the relay channel for transmitting commands, and for receiving response signals the galvanic isolation device 43 connected via the switch 31 signals with cable 22 of the receiving relay channel.

 Verification of on-board computing devices is carried out using the multiplex channel adapter 39 and the interface bus 15 of the multiplex information exchange channel.

 To check the radio devices in the course of the control task, a reference voltage is supplied to the intermediate frequency amplifiers 34, 36, including the target simulator 4, at the command from the output of the simulator switching unit 38, which is formed as a DC voltage. The simulator 4, receiving the probing signal emitted by the antenna 23 of the radar sighting device and received by the control antenna 1 at the first input of the circulator 32, transmits it to the input of the first frequency converter 33, which is added to the reference frequency signal of the radar sighting device. Further, the signal converted to an intermediate frequency is amplified in the amplifier 34, delayed by the delay line 35, amplified in the amplifier 36 and fed to the input of the second frequency converter 37, performing the inverse of the frequency conversion with respect to the converter 33. Next, the signal corresponding to the simulated target range, through the circulator 32 is supplied to the control antenna 1 and is radiated into the space in the direction of the antenna 23 of the radar sight.

 If necessary, determined by the initial control program, the control device 5 of the control system also analyzes the telemetry signals received at the input of the multiplexer 40 via the cable 19 of the relay communication channel with the telemetry device 25.

 Self-monitoring of the complex can be performed in two modes - operational, providing verification of the serviceability of devices and inter-instrument communications regardless of the connection to the on-board equipment, and self-monitoring with coverage of external communications.

 The online mode of self-monitoring is carried out by the device 7 of self-control, which at the beginning of the test by the control command from the second output of the discrete input-output device 64, supplied to the control inputs of the switches 29, 30, 31, sets them to the second position. The output of the switch 29 of the control points is switched with its second input connected to the output of the cross-linking device 74, the output of the switch 31 of the signals is switched with its second input connected to the output of the transmitter 65 teams, and the input of the switch 30 teams is switched with its second output, connected to the input of the galvanic isolation device 66.

 During self-control, the device 7, by analogy with the on-board equipment, receives control commands from the control device 5 of the control system and the electric equipment control device 6 and generates response signals. Simulation of possible situations that arise between the control points of electrical equipment is carried out using a simulator of 72 potentials and a simulator of 73 messages.

 When self-monitoring with external communications coverage, the cable lines 20, 21 and 22 are disconnected from the corresponding UAV connectors 2. Cable 20 connects the first and fifth inputs of switching device 3, cable 21 connects its first and fourth outputs, and cable 22 connects the second and fourth inputs, as shown by a dotted line in figures 1 and 3. In the future, verification is performed in the same way as in the operational mode of self-monitoring. The difference lies in the absence of a control signal at the control inputs of switches 29, 30, 31, due to which they are in their first state, as in the regular monitoring of onboard UAV systems 2.

 If necessary, check also the computing devices of the control system 24, which are exchanged via the multiplex channel, line 15 is disconnected from the output of the control system 24 and connected to the input-output of the adapter 70 of the multiplex channel of the device 7 self-monitoring, connecting it to the adapter 39 of the multiplex channel of the device 5 control system control. This creates the possibility of mutual functioning of the computer 44 and 67 to test the multiplex communication channel with the control system.

 Thus, the proposed complex for testing onboard UAV systems has wide functionality and increased reliability of test results due to the control coverage of radio systems, computer systems and electrical equipment, an increase in the number of monitored parameters and automation of the test process.

 The industrial applicability of the invention is determined by the fact that the proposed complex can be manufactured in accordance with the above description and drawings on the basis of well-known components and technological equipment and used for complex verification of onboard UAV systems.

List of references
1. RF patent 2174238, IPC G 01 S 7/40, G 09 B 9/00, 09/27/2001

 2. Shalygin A. S., Palagin Yu.I. Applied methods of statistical modeling. -L.: Mechanical Engineering (Len. Department), 1986.

Claims (1)

  1.  A complex for checking on-board systems of an unmanned aerial vehicle (UAV), comprising a target simulator with a control antenna connected via a radio channel to an antenna of a UAV radar sighting device, and a control panel configured to set up a program for checking and displaying information, characterized in that the device is introduced into it guaranteed power supply, a switching device including a switch for control points, a command switch and a signal switch, as well as integrated into a local network with a remote control ohm control through the interface lines of information exchange and the hub of the local network, a control system control device, an electrical equipment control device and a self-control device, each of which contains a secondary power supply connected to the output of the guaranteed power supply device, and an electronic computer connected to the system the interface line to which the monitoring device is connected, the LAN adapter connected to the corresponding interface data exchange, and a discrete input-output device connected to the input with the output of the galvanic isolation device, and the first output to the input of the command transmitter, the outputs of the monitoring devices of the control system of the control system, electrical control devices and self-monitoring devices connected to the input of the interface conversion device , which is part of the control panel and connected to the central computer, to which the keyboard is also connected, the device an external drive, the corresponding interface highway for information exchange and the system interface highway to which the discrete input-output device is connected, connected to the control panel by the input and the output to the indicator board, in addition to the control system control device mentioned above, the multiplex adapter is connected channel through which information is exchanged with computing devices of the UAV control system, and an analog-digital device conversion, the input and control output of which is connected respectively to the output and input of the information channel address of the multiplexer, to the input of which signals from the UAV telemetry device are supplied, the target simulator switching unit connected to the output with the control input of the target simulator, the reference input of which serves to receive the reference frequency signal from the UAV radar sight, in addition to the aforementioned The electric equipment field contains a device for measuring resistances and potentials, the output of which is connected to the system interface line of the electrical equipment control device, and the input is connected to the output of the control point switch, the control input of which is connected to the second output of the discrete input-output device of the electric equipment control device, in addition to the aforementioned self-monitoring device contains a multiplex channel adapter connected to its system interface backbone, which in self-mode The field is connected to the input / output of the multiplex channel adapter of the control system control device, as well as a potential simulator and a message simulator connected to a crossover device, the output of which is connected to the second input of the test point switch, the first input of which is used to connect the connecting circuits from the control points of the UAV electrical equipment and the output is connected to the input of the switch control points of the control device of electrical equipment, the outputs of the transmitters of the commands of the control device elek the equipment and control devices of the control system are connected to the input of the command switch, the second output of which is connected to the input of the galvanic isolation device of the self-monitoring device, the output of the transmitter of the commands of the self-monitoring device is connected to the second input of the signal switch, the output of which is connected to the inputs of the galvanic isolation of the electrical control device and control device control systems, the second output of the discrete input-output device of the self-monitoring device control points with the control inputs of the switch, the switch command signals and switch, wherein the first output switch command signals are generated, switching control relay devices on board UAV systems and response signals corresponding actuators onboard a UAV system are transmitted to the first input signal switch.
RU2001135655/09A 2001-12-13 2001-12-13 Test complex for check of on-board systems of unmanned flying vehile RU2205441C1 (en)

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2459219C1 (en) * 2011-01-11 2012-08-20 Открытое Акционерное Общество "Уральское проектно-конструкторское бюро "Деталь" System for built-in control and calibration of monopulse radar station
RU2499979C1 (en) * 2012-04-28 2013-11-27 Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации Method of rocket electric and info exchange test
CN105974222A (en) * 2016-04-27 2016-09-28 乐视控股(北京)有限公司 Unmanned aerial vehicle fault detection method, apparatus and system thereof
RU168143U1 (en) * 2016-06-23 2017-01-18 Публичное акционерное общество "Научно-производственное объединение "Алмаз" имени академика А.А. Расплетина" (ПАО "НПО "Алмаз") Device for pre-starting the readiness of aircraft
RU2677757C2 (en) * 2014-06-25 2019-01-21 Сафран Эркрафт Энджинз Method of monitoring degradation of device on board aircraft including determination of counting threshold
RU2693884C1 (en) * 2018-07-31 2019-07-05 Войсковая часть 13991 Device for control and switching of circuits ira (measuring relay apparatus)

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
ШАЛЫГИН А.С., ПАЛАГИН Ю.И. Прикладные методы статистического моделирования. - Л.: Машиностроение (Лен. отделение), 1986, с.292-294. *

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2459219C1 (en) * 2011-01-11 2012-08-20 Открытое Акционерное Общество "Уральское проектно-конструкторское бюро "Деталь" System for built-in control and calibration of monopulse radar station
RU2499979C1 (en) * 2012-04-28 2013-11-27 Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации Method of rocket electric and info exchange test
RU2677757C2 (en) * 2014-06-25 2019-01-21 Сафран Эркрафт Энджинз Method of monitoring degradation of device on board aircraft including determination of counting threshold
CN105974222A (en) * 2016-04-27 2016-09-28 乐视控股(北京)有限公司 Unmanned aerial vehicle fault detection method, apparatus and system thereof
RU168143U1 (en) * 2016-06-23 2017-01-18 Публичное акционерное общество "Научно-производственное объединение "Алмаз" имени академика А.А. Расплетина" (ПАО "НПО "Алмаз") Device for pre-starting the readiness of aircraft
RU2693884C1 (en) * 2018-07-31 2019-07-05 Войсковая часть 13991 Device for control and switching of circuits ira (measuring relay apparatus)

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