RU2249543C1 - Flying vehicle weapon control system - Google Patents

Abstract

FIELD: aircraft equipment for combat flying vehicles.

SUBSTANCE: program part of system may be used for selection of destruction weapon, forming of target designation signals, flight mission for destruction weapon, cyclogram for connection of aircraft power supply unit to destruction weapon, delivery of information to integrated complex of onboard equipment for display on multi-functional indicator of display system and transmission of control commands to actuating units from information control field of cabin. Equipment part of system includes matching and logic unit for solving destruction weapon control algorithms, informational interaction with onboard computer and conversion of target designation signals. Jettisoning unit is used for dropping destruction weapon from all points of suspension. Information conversion unit is used for compilation of information from matching and logic unit for digital destruction weapon, conversion code-to-analog-to-code target designation signals and transmission of destruction weapon control signals. First group of actuating units is used for informational interaction of destruction weapon with matching and logic unit in energy channel and second group is used for energy channel only.

EFFECT: enhanced efficiency.

4 cl, 2 dwg

Description

The invention relates to aircraft equipment and is intended for use on combat aircraft of new and existing structures.

Known weapons control system (SLA), which checks the status of aircraft weapons (ASA) at all points of the suspension (TP) and contains, in particular, an indication system and a weapon control panel in the cockpit, as well as a communication device with an object of weapons and a device for reception and transmission of information (US 3803974 A, F 41 F 3/06, 04.16.1974).

The disadvantages of the known system are associated with a limited scope, due to the imperfection of layout solutions, and with low operational reliability caused by a low level of integration of composite elements.

Closest to the proposed one is the LMS, designed to control the preparation and use of all types of weapons used on the aircraft, and consisting of a command unit with time interval nodes, a one-time command unit, a control unit for the built-in gun installation and a control unit for unguided weapons and remote units, each of which includes a switching unit and a signal conversion unit with TP (RU 2146835 C1, G 06 F 17/00, 03/20/2000).

The specified MSA is characterized by reduced weight due to the reduction of wired communication lines and provides an increase in the number of suspension points and types of weapons without significant modifications to the equipment. However, its disadvantages lie in the low efficiency of the intended use of the aircraft due to the use of ground-based control systems for OMS in preparation for flights, the inability to use both unguided weapons, guided weapons and high-precision weapons on the aircraft, and the inability to improve the system for indicating the state of weapons and governing bodies during the development of the information-control field, the lack of the possibility of further building up on the aircraft app rate nomenclature weapons without increasing the number of TP and the lack of opportunities to increase the designated lifetime of the JMA.

The objective of the invention is the creation of the MSA, which can significantly increase the efficiency of the aircraft.

To solve this problem, an aircraft control system has been proposed, containing a software part, which is configured to select aviation weapons (ASA) for use, select application modes, and formations. Targeting signals from sighting systems and a flight task for the TSA, the formation of a cyclogram for connecting aircraft power supply to the TSA, the formation of information in an integrated complex of on-board equipment for display on the multi-function display of the display system, as well as transmission to executive units of control commands from the information control field of the cabin, and hardware part, which includes a matching unit and logic, which provides the solution of ASP control algorithms, information link interaction with the on-board digital computer of the upper level and conversion of target designation signals, emergency unloading unit providing emergency reset of the TSA from all suspension points (TP), information conversion unit providing transmission from the matching unit and logic of target designation signals for digital TSA, code-analog-code conversion target designation signals for all weapons placed on the aircraft and transmission of ASP control signals in the form of one-time commands, the first group of executive units providing information the interaction of the TSA with the matching unit and logic through the energy channel and the transmission of one-time commands for all weapons used, the second group of executive units that ensure the interaction of the TSA with the matching unit and logic only through the energy channel.

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

The proposed control system is a modularly distributed, composable system in which the matching and logic unit and the emergency unloading unit are located in the fuselage on the mounting frame, the information conversion units are in the pylons of the first and second TP, the executive units of the first group are in the pylons of the first, second, third and the fourth TP, the executive units of the second group are in the pylons of the fifth and sixth TP.

In the proposed LMS, an information channel is used for communication with the ASP, which provides the transmission of target designation signals for homing heads, flight tasks in the form of one-time commands, target parameters and altitude and speed parameters of the carrier from the onboard digital computer of the upper level through the matching and logic unit and the information conversion block on the ASP depending on the selected type of TSA for use, an information channel that provides information on the type of TSA on the TP, the availability of TSA on the TP, the TSA's readiness for use from the coordination unit and logic to the on-board computer, the energy channel, which provides for connecting to the ASP power supply voltages of +27 V, alternating current with a frequency of 400 Hz and single-phase and three-phase voltages, respectively, 115 V and 200 V, alternating current with a frequency of 400 Hz and 1000 Hz and 36 V voltage, an analog information exchange channel that provides transmission to and reception of TS signals from the actuators through the executive units of the first group in the form of “+27 V”, “case”, “open”, characterizing the presence and type of TSA on the TP, TP number , commands and status signals and otovnosti TSA actuating commands, commands for branch TSA and blocking signals, the television channel providing the transfer of the television image on the television homing multifunctional lamp through the channel control unit.

The proposed FCS is coupled with an onboard power supply system, aiming systems, navigation, a control field of a cabin, recording parameters, as well as an anti-surge system through an onboard digital computer of the upper level, an emergency mode console via wired communication through an emergency unloading unit, with TSA located on the TP, with built-in cannon installation through the emergency unloading unit, with a remote control system through the on-board computer of the upper level and the on-board automated control system.

Figure 1 shows the functioning of the proposed SLA on the aircraft, and figure 2 shows the structural diagram of the SLA.

In this technical solution, the deep integration of the MSA 1 (Fig. 1) with the on-board electronic equipment (avionics) of the aircraft was performed, and a multifunction digital indicator (MFCI) 2 and an indication control panel (ISP) 3 were used to indicate and control weapons.

When placing the executive units and the information conversion unit (BRI) in the pylons 4 for TP 5, 6, 7, 8, 9, 10, 11, 12 arms without transitional beam holders, the separation of the OMS blocks into executive, power and information blocks is carried out.

For use on the aircraft of various types of weapons at the same time implement the hardware channels 13 for communication of the MSA with weapons 14.

To ensure verification of the LMS in flight and at the stages of preparation for flights without the use of ground-based control facilities (remotes, HACK mobile systems), the LMS provides hardware-based implementation of the integrated control system.

To ensure the possibility to set the life of the MSA for 30 years, the appropriate construction scheme and element base are used.

To ensure the possibility of reducing the weight of the aircraft, instead of a feeder electronic circuit, blocks with new design solutions, special placement and communication channels 13 are used.

To provide the possibility of weapons control actions for the purpose of training, the LMS can be equipped with a device for simulating real weapons.

Figure 2 shows the mounting frame 15 (RM), matching and logic unit (BSL) 16, emergency unloading unit (BAR) 17, information conversion units (BRPI) 18.1, 18.2, power supply system (SES) 19, executive units (BI ) 20.1, 20.2, 20.3, 20.4 of the first group, executive units (BI) 21.1, 21.2 of the second group, uncontrolled cannon mount system (SNPU) 22, guided air-to-air missiles (UR B-V) 23.1, 23.2, 23.3, 23.4, guided air-to-ground missiles (UR V-3) 24.1, 24.2, 24.3, 24.4, rockets (PC) 25.1 25.2, 25.3, 25.4, bombs 26.1, 26.2, 26.3, 26.4, fuel tank suspensions (PTB) 27.1, 27.2 and intersystems first traffic channel (MKIO) MSA 28.

The MSA is intended for the preparation and combat use of TSA deployed on an aircraft.

In preparing the ASP for the application of the OMS solves the following tasks:

carries out, together with the integrated complex of on-board equipment (IKBO), the choice of ASP for use;

makes preparation and launch (discharge) of the selected weapon in accordance with the required time sequence;

transmits to ICBO information on the type, availability and readiness for use of TSA located on the TP;

forms the necessary locks to ensure safety during operation and combat use of TSA;

provides integrated control of the system and the training regime, in terms of weapons, together with IKBO;

provides power from on-board sources to the ASP;

Converts and transfers from the onboard digital computer the upper level of target designation signals to the TSA.

The LMS consists of software and hardware.

The software part provides an algorithmic solution to the following tasks:

- choice of TSA for use;

- selection of application modes;

- the formation (conversion) of target designation signals from sighting systems and flight tasks for TSA;

- formation of a cyclogram for connecting aircraft power supply to ASP;

- the formation of information in IKBO (type of TSA on TP, the presence of TSA, the availability of TSA, etc.) to display on the MFI display systems;

- transfer to executive blocks of control commands from the information control field of the cabin (IUP);

- management of built-in control.

The hardware includes the following blocks:

- BSL 16, which provides the solution of ASP control algorithms, information interaction with the upper-level on-board computer (according to GOST 26765.52-87) and with peripheral control units (according to GOST 18977-79), target signal conversion from GOST 26765.52-87 to GOST 18977-79 ;

- BAR 17, providing emergency reset (start) of the TSA from all TSs, connecting emergency power to the TSA, control of cannon weapons (PV);

- BRPI 18.1, 18.2, providing the broadcasting of target designation signals (according to GOST 18977-79) from BSL 16 for digital ASPs, the conversion of target designation signals (code - analog - code) for all weapons placed on the aircraft and transmission of signals to executive units 20.1-20.4 ASP control in the form of one-time commands;

- executive units 20.1-20.4, providing informational interaction between TSA and BSL 16 through the energy channel (according to GOST 18977-79) and the transmission of one-time signal commands for all used weapons;

- executive blocks 20.1, 20.2, ensuring the interaction of TSA with BSL 16 only through the energy channel.

BSL 16 and BAR 17 are located in the fuselage on the mounting frame of the PM 15. Information interaction of the BSL 16 with the upper-level onboard computer is in accordance with GOST 26765.52-87.

BRPI 18.1, 18.2 are placed in the pylons of the first 5 and second 6 TP. The information interaction of the blocks on target designation channels for controlled TSAs is carried out according to GOST 18977-79. Each block provides information interaction with four TP 6-12 and 5-11.

BI 20.1-20.4 are located respectively in the pylons of TP 5-8 and provide informational interaction with TSAs placed on these TPs. Communication of BI 20.1-20.4 with BSL 16 through the energy channel is performed according to GOST 18977-79, and with BRPI 18.1,18.2 via discrete one-time signals.

BI 21.1, 21.2 are placed in the pylons of TP 9, 10 and provide control over the energy channel of missiles placed on TP 10, 12 and 9, 11, respectively.

The structure of the LMS is, as already indicated, a distributed modular (block) composable control system. Placing the system blocks in the pylons reduces the number of wire connections of the central control unit to the TP and reduces the number of blocks placed in the fuselage.

The MSA is interfaced with the following on-board systems:

with an onboard power supply system;

with aiming systems, navigation, IUP system;

with a registration system (EBN, ZBN and SOK-B) parameters;

anti-surge system - through the on-board digital computer of the upper level (according to GOST 26765.52-87);

emergency control panel via wired communication through BAR 17;

- with TSA placed on TP;

- with integrated cannon mount through BAR 17;

- the system of CDS through the on-board computer of the upper level;

- the system of OMS CO;

- BASK system.

The ASP is interfaced with the OMS and the on-board equipment complex via the following information communication channels:

- an information channel in which target designation signals for GPS heads, flight mission in the form of one-time commands, target parameters are transmitted to the TSA from the on-board digital computer of the upper level via BSL 16 with subsequent necessary conversion to BRPI 18.1, 18.2 high-speed parameters of the carrier. To ensure the conditions for the use of TSA from the on-board computer of the upper level on BSL 16 information is transmitted DR, the results of the built-in control (VSK) TSA;

- an information channel in which information on the type of TSA on the TP, the availability of TSA on the TP, the readiness of the TSA for use is transmitted from the BSL to the on-board computer;

- an energy channel that provides the connection to the AAS of supply voltage of a DC voltage of +27 V, alternating current with a frequency of 400 Hz and single-phase and three-phase voltages of 115 V and 200 V, respectively, of alternating current with a frequency of 400 Hz and 1000 Hz and a voltage of 36 V;

- the analogue information exchange channel ASP-SUO, which provides, through the BI 20.1-20.4 blocks, the transmission and reception of signals and commands from TP;

- a television (TV) channel that provides transmission of television images from television GOS (in accordance with GOST 7845-92) to the IFI through BKTV.

The formation of control signals for connecting the supply voltage to the TS ACP is carried out by the BSL 16 block in accordance with the sequence diagram. The signal to turn on the power generated in BSL 16 takes into account the inadmissibility of overloading the aircraft's power system at the time of peak loads when connecting the ASP. Power supply connection is carried out only on condition of availability of TSA on TS.

Signals and commands in the analogue information exchange channel ASP-MSA characterize:

a) the presence and type of TSA on TP;

b) suspension point number;

c) commands and signals about the status and readiness of TSA;

d) starting commands;

e) teams for the separation of TSA (tactical and emergency);

e) blocking signals.

The information transmitted through the communication channels of the SUO-BTsVM and SUO-ASP, provides the TSA with a complete set of commands and signals necessary for using the TSA in accordance with their specified technical characteristics in the modes established for the TSA.

In the process of preparing and using the TSA, the airborne complex, together with the MSA, implements the following TSA application modes:

_ц, ω, размер, угловые координаты цели и т.д.);full instrumentation mode (TSS), when a complete set of signals and commands is generated for the TSA taking into account information about the medium and the target (D, D ',

_q , ω, size, angular coordinates of the target, etc.);

a mode with incomplete instrumentation (NPO), when some information about the target (D, D ', ω _c , etc.) may be missing;

emergency mode (AR).

In the software mode, the preparation of the TSA for launch (reset) is carried out with a lock on readiness and permission to start (for zones) - DR.

In the NGO mode, the OMS eliminates blockages on permitted zones due to lack of information on D, D ’. In the NGO mode, the BSL block 16 gives permission to start (reset) in accordance with the decision of special algorithms.

In the AR mode, the FCS provides, according to a certain program, the unloading of TP from existing TSA. In the event of an emergency reset (start), the TSA is reset to NOT EXPLOSION.

The OMS provides the specified technical characteristics in combat use:

- practical ceiling;

- maximum speed near the ground;

- maximum speed at maximum height;

- maximum operational overload.

The depth of the built-in control (VSK) is 0.95.

Each unit that is part of the OMS is a structurally complete unit, which includes:

terminal device as part of BSL 16, providing information interaction with the upper-level onboard computer;

computer hardware (CBT), providing the solution of given algorithms;

information receivers and transmitters according to GOST 18977-79; secondary power supplies (PSUs) providing power - CBT elements;

executive devices that provide the formation of current executive commands on the DC and AC circuits.

The mass and size characteristics of the LMS units are primarily determined by the circuitry of the executive devices (BI) - current switches up to 20 A, electromechanical impulse distributors of the ПУС type.

The development and application of specialized switches and pulse distributors with specified characteristics will significantly reduce the overall dimensions of the actuator units and the overall LMS.

The LMS and the interference emission system are integrated into a single system (LMS-13P), which has additional functions:

- shooting interference in predetermined modes (automatic from REP);

- semi-automatic according to the REP program at the command of the pilot;

- manual - at the choice and command of the pilot; safety locks during operation of the emission system;

- transfer of information to the ICBO about the presence, type, consumption of interference cartridges;

- built-in control.

Pre-flight control of the OMS is carried out at the pre-flight preparation stage in two modes:

1. Ground check of the LMS before installing the TSA.

2. Operational check of the OMS with the TSA installed on the TP.

Verification in the first mode provides an assessment of the functioning of the LMS taking into account the pairing with the on-board equipment for a given version of loading the TP in all modes of application of ASP.

Verification is carried out using specialized test equipment (KPA-ASP) that allows you to simulate TSA on the TP using all communication channels (except microwave channels) and combat electrical circuits.

On KPA-ASP, the option of loading ASP is specified. From the board, all the necessary signals are issued to the KPA-TSA in accordance with the protocol of interaction with the TSA.

In the LMS at the program level (LMS and BCVS), the “LMS ground verification” mode is organized, which interacts with the on-board automated control system BASK.

During control in the cockpit

- turn on the system power;

- control information from the TSA on the MFI indicator (availability, type, availability, etc.);

- click on the “PR” command battle button;

- click on the choice of the gun trigger;

- press the “ABAR. START ”,“ EMERGENCY RESET ”;

- control the simulation of gathering (reset) TSA.

The results of the bailout are displayed on the IFI in the form of a “FIXED” signal and are documented on the “Carat” repeater (EBN).

In the event of a malfunction, the MFI displays information about where the failure occurred during the verification process (block, circuit, etc.).

Board inspection with TSA installed on the TP (pre-flight control) is carried out in the VSK mode.

The check is carried out on all channels, except for combat electrical circuits, which provide launch, reset, and firing from SPV.

The VSK mode is formed at the program level of the LMS and the upper-level BCWS.

The monitoring results are displayed on the MFI in the form of a “CORRECT-B” signal.

In safety circuits in the VEK-B mode, control is carried out using mechanical and electrical locks of the combat chains (start, reset).

Claims (4)

1. The weapon control system of the aircraft, containing hardware, characterized in that the hardware is made of a matching unit and logic, which provides the solution to the algorithms for controlling airborne weapons (AAS), converting target designation signals, an emergency unloading unit, providing an emergency reset of the AAS from all suspension points (TP), information conversion units, providing translation from the matching unit and logic of target designation signals for digital TSA, code conversion - analog - code of targeting signals for all weapons placed on the aircraft and transmitting ASP control signals in the form of one-time commands, the first group of actuating units providing informational interaction of the ASP with the coordination and logic block along the energy channel and transmitting one-time commands for all used weapons, the second group of executive blocks that ensure the interaction of the TSA with the matching unit and logic only through the energy channel, and the matching unit and logic is connected to the on-board computer top level of the intersystem channel of information exchange for the choice of aircraft weapons for use, the choice of application modes, the formation of targeting signals from sighting systems and flight tasks for the TSA, the formation of a cyclogram for connecting aircraft power supply to the TSA, the formation of information signals in an integrated complex of onboard equipment for display on multifunctional indicator of the display system, as well as transmission to the executive blocks of signals of control coma d from the information field of the control cabin. 2. The system according to claim 1, characterized in that it is made modularly distributed and composable, while the matching and logic unit and the emergency unloading unit are located in the fuselage on the mounting frame, the information conversion units are in the pylons of the first and second TP, the executive units of the first groups - in the pylons of the first, second, third and fourth TP, executive units of the second group - in the pylons of the fifth and sixth TP. 3. The system according to claim 1, characterized in that for communication with the TSA an information channel is used that provides the transmission of targeting signals for homing heads, flight tasks in the form of one-time commands, target parameters and altitude-speed parameters of the carrier from the onboard digital computer of the upper level through the unit coordination and logic, and a block for converting information to TSA depending on the selected type of TSA for use, an information channel that provides information on the type of TSA on TP, availability of TSA on TP, readiness of TSA for use from bl matching and logic into the on-board digital computer, the energy channel, which provides connection to the ASP of supply voltage of direct current voltage of +27 V, alternating current with a frequency of 400 Hz and single-phase and three-phase voltages of 115 and 200 V, respectively, of alternating current with a frequency of 400 and 1000 Hz and 36 V voltage, an analog information exchange channel that provides transmission to and reception of TS signals from the executive units of the first group in the form of "+27 V", "case", "open", characterizing the presence and type of TSA on the TP, TP number , commands and status signals Britain and readiness HSA starting team, the team at the Department of HSA and blocking signals, a television channel providing the transmission of television image from TV homing on the multifunction display via the control unit of the channel. 4. The system according to claim 1, characterized in that the matching and logic unit is connected to an intersystem information exchange channel for interfacing through a top-level digital computer with aiming systems, navigation, a control field of a cabin, registration of parameters, remote control, and also with an anti-surge system, emergency unloading unit is connected via wired communication with the emergency panel.

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