CN111025967A - Guide control assembly and guide control system - Google Patents
Guide control assembly and guide control system Download PDFInfo
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- CN111025967A CN111025967A CN201911220816.4A CN201911220816A CN111025967A CN 111025967 A CN111025967 A CN 111025967A CN 201911220816 A CN201911220816 A CN 201911220816A CN 111025967 A CN111025967 A CN 111025967A
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0423—Input/output
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/24—Pc safety
- G05B2219/24215—Scada supervisory control and data acquisition
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Abstract
The invention relates to the technical field of airborne weapon control systems, in particular to a guide control assembly and a guide control system, wherein the assembly comprises a plurality of stacked single-plate structural bodies; the cavity formed by two adjacent single-plate structural bodies is used for arranging a functional module, and the functional module comprises a basic module and an inertia measurement module; the wiring channel is arranged on the single board structure body; and the wiring channel is used for arranging wiring for connecting each functional module. By adopting a stacked structural design, the cavity formed by two adjacent single-board structural bodies is used for arranging the functional module, and the functional module is subsequently stacked in series board by board to form a complete machine after the functional module is arranged, so that the integrated arrangement of the guide and control system is realized.
Description
Technical Field
The invention relates to the technical field of airborne weapon control systems, in particular to a guidance control assembly and a guidance control system.
Background
The microminiaturization and integration of the flight control system are important means for realizing the miniaturization of the aircraft in developed countries such as Europe and America. Currently, the design of a flight control system in foreign countries is developing towards user-defined direction, and attempts are made to break through the mode of using general system components, so that with the rapid development of the system-on-chip technology, the integrated technology of designing a micro flight control system becomes possible.
Disclosure of Invention
In view of this, the embodiment of the present invention provides a guidance and control assembly and a guidance and control system, so as to solve the problem of integrated configuration of the guidance and control system.
According to a first aspect, an embodiment of the present invention provides a guidance and control assembly, including:
a plurality of stacked single plate structures; the cavity formed by two adjacent single-plate structural bodies is used for arranging a functional module, and the functional module comprises a basic module and an inertia measurement module;
the wiring channel is arranged on the single board structure body; and the wiring channel is used for arranging wiring for connecting each functional module.
The guide control assembly provided by the embodiment of the invention adopts a stacked structural design, the cavity formed by two adjacent single-board structural bodies is used for arranging the functional module, and the functional modules are sequentially stacked in series board by board to form a complete machine after being arranged, so that the integrated arrangement of the guide control system is realized.
With reference to the first aspect, in a first embodiment of the first aspect, the single plate structural body includes:
the bearing surface is used for arranging the functional module;
and the connecting component is arranged around the bearing surface, and is provided with a connecting part which is used for connecting the adjacent veneer structural bodies.
According to the guide control assembly provided by the embodiment of the invention, the functional modules are arranged on the bearing surface, and the wiring connection of the modules is realized on the connecting assembly, so that the wiring structure can be simplified.
With reference to the first embodiment of the first aspect, in a second embodiment of the first aspect, the single board structures correspond to the functional modules one to one.
The guide control assembly provided by the embodiment of the invention can be used for installing the single-board structural body according to actual conditions, is convenient for realizing the combination of the functional modules, and is simple to assemble and easy to realize.
According to a second aspect, an embodiment of the present invention further provides a guidance and control system, including:
the first aspect of the present invention, or the guidance and control assembly described in the first embodiment or the second embodiment of the first aspect;
the function module is arranged in a cavity formed by two adjacent single-board structural bodies of the guide control assembly; the functional modules comprise a basic module and an inertia measurement module, the functional modules are connected through routing wires, and the routing wires are arranged in routing channels on the single board structure.
According to the guidance and control system provided by the embodiment of the invention, each functional module is arranged in the cavity formed by two adjacent single-board structural bodies, the single-board structures adopt a stacked structural design, and after the functional modules are arranged, the functional modules are connected in series one by one to form a whole machine, so that the integrated arrangement of the guidance and control system is realized.
With reference to the second aspect, in a first embodiment of the second aspect, the base module includes:
the interface board is used for acquiring data from the target body and sending the data to the computer board;
the computer board is connected with the interface board and used for forming a system control instruction based on the data sent by the interface board and sending the control instruction to the power board;
the power board is connected with the computer board and used for realizing steering engine control, time sequence power distribution and power management of the target body based on the control instruction;
and the external connector printed board is connected with the interface board, the computer board and the power board and is used for providing an electrical interface for the outside.
With reference to the first embodiment of the second aspect, in the second embodiment of the second aspect, each of the base modules is disposed in one-to-one correspondence with the single board structure.
The guidance control system provided by the embodiment of the invention can be used for installing the single-board structural body according to actual conditions, is convenient for realizing the combination of the functional modules, and is simple to assemble and easy to realize.
With reference to the first embodiment or the second embodiment of the second aspect, in a third embodiment of the second aspect, the interface board includes:
the interface conversion circuit is connected with the main control circuit of the computer board; the interface conversion circuit comprises a preset interface conversion chip and is used for realizing conversion and level conversion of an external communication interface;
the satellite positioning circuit is connected with the main control circuit of the interface board; the satellite positioning circuit is used for receiving positioning data of the target body and providing a resolving result of the positioning data to the main control circuit;
and the secondary power supply conversion circuit is connected with the primary power supply combination of the power board and is used for converting the output voltage of the primary power supply combination into the working voltage of the interface board.
With reference to the first embodiment or the second embodiment of the second aspect, in a fourth embodiment of the second aspect, the computer board includes:
the main control circuit is provided with a processing system port and a programmable logic unit port; the processing system port is used for hooking a memory, a bus interface and a network interface; the port of the programmable logic unit is connected with a preset interface conversion chip of the interface board and used for realizing data interaction;
the ADC circuit is used for realizing AD sampling of data;
and the secondary power supply conversion circuit is connected with the primary power supply combination of the power board and is used for converting the output voltage of the primary power supply combination into the working voltage of the computer board.
With reference to the first embodiment or the second embodiment of the second aspect, in a fifth embodiment of the second aspect, the power board includes:
the primary power supply combiner is used for combining all input power supplies so as to provide power for the guidance and control system; each input power supply is provided with a reverse protection circuit;
the steering engine control circuit is provided with a plurality of first controllable switches and is used for receiving switch control signals of the computer board and converting the switch control signals into pulse width modulation signals through the first controllable switches so as to realize the steering engine control of the target body;
and the time sequence power distribution circuit is provided with a plurality of second controllable switches and is used for receiving the time sequence switch control signals of the computer board and realizing the time sequence power distribution of the target body through the second controllable switches.
With reference to the second aspect, in a sixth embodiment of the second aspect, the inertial measurement module includes an inertial measurement board and an inertial meter; wherein, inertia measurement board includes:
the instrument information acquisition conditioning circuit is connected with the inertial instrument; the instrument information acquisition conditioning circuit is used for processing the output signal of the inertial instrument and outputting the processed output signal to a computer board in the basic module;
and the secondary power supply conversion circuit is connected with a primary power supply combination of a power board in the basic module and is used for converting the output voltage of the primary power supply combination into the working voltage of the inertia measurement module.
With reference to the second aspect, in a seventh implementation manner of the second aspect, the system further includes an expansion module, where the expansion module includes a data link board and a wireless fire control printed board.
With reference to the seventh embodiment of the second aspect, in an eighth embodiment of the second aspect, the data link plate includes:
the measurement and control receiving and transmitting unit is connected with the receiving and transmitting antenna of the target body;
the frame coding unit is connected with the computing board in the basic module and used for coding the output data of the computing board and then sending the coded data to the receiving and sending antenna of the target body through the measurement and control receiving and sending unit;
and the demodulation and decoding unit receives the data of the transmitting and receiving antenna of the target body through the measurement and control transmitting and receiving unit, demodulates and decodes the data and then sends the demodulated and decoded data to the computing board.
With reference to the seventh embodiment or the eighth embodiment of the second aspect, in a ninth embodiment of the second aspect, the wireless fire control printed board includes:
a carrier end unit and a missile upper end unit; the carrier end unit is arranged in a cavity formed by two adjacent single-plate structural bodies;
the carrier end unit comprises a first processor, a first wireless communication node and a power supply which are connected; the carrier end unit is used for information processing and wireless communication;
the pop-up end unit comprises a second processor and a second wireless communication node which are connected.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic structural diagram of a guidance assembly according to an embodiment of the invention;
FIG. 2 is a schematic structural diagram of a guidance assembly according to an embodiment of the invention;
FIG. 3 is a functional block diagram of various modules of a guidance system according to an embodiment of the present invention;
FIG. 4 is a functional block diagram of various modules of a guidance system according to an embodiment of the present invention;
FIG. 5 is a block diagram of information interaction of a data link chain according to an embodiment of the present invention;
FIG. 6 is an information interaction block diagram of a wireless fire control printed board according to an embodiment of the invention;
FIG. 7 is a schematic diagram of the connection of various modules according to an embodiment of the invention;
fig. 8 is a schematic diagram of the connection of various modules according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The embodiment of the invention provides a guide control assembly, which is used for realizing the installation of each functional module and an inertial instrument of a target body and the connection of the functional module and the inertial instrument with the outside. The target body may be a launch vehicle, a missile or other devices, and the like, and the application field of the guidance and control assembly is not limited at all.
As shown in fig. 1, the guidance and control assembly includes a plurality of stacked single-plate structural bodies 10 and routing channels disposed on the single-plate structural bodies 10. The number of the single-plate structural bodies 10 may be specifically set according to the control requirement of the target body, and is not limited herein.
Specifically, a functional module for disposing a target body is provided in a cavity formed by two adjacent single plate structural bodies 10. The functional modules include a basic module and an inertial measurement module, and the basic module is a module necessary for realizing the control requirement of the target body, such as a computing board, an interface board and the like. The basic module can be specifically configured according to actual situations, and is not limited herein. The inertia measurement module comprises an inertia instrument and an inertia measurement plate corresponding to the inertia instrument and is used for processing the measurement result of the inertia instrument and then sending the processed measurement result to a calculation plate in the basic module for calculation to form a control instruction.
Fig. 1 shows a schematic diagram of the complete machine of the guidance and control assembly after assembly, in fig. 1, the single board structure body on the uppermost layer of the guidance and control assembly is used to provide interfaces between each module in the guidance and control assembly and the outside, the number of the specific single board structure bodies may be specifically set according to the number of the functional modules, and due to the adoption of the structural arrangement of stacking arrangement, each single board structure body may be variously combined as required to be applied to different guidance and control systems.
Each single board structure in the guiding and controlling assembly is also provided with a wiring channel for arranging wiring for connecting each functional module. For example, the routing channels may be disposed at the edges of the monolithic structure body to facilitate wiring; or the single board structure can be arranged at the middle position of the single board structure so as to save the wiring quantity. The specific setting can be carried out according to the actual situation.
As an alternative embodiment of this embodiment, as shown in fig. 2, the veneer structure 10 includes a bearing surface 11 and a connecting assembly 12. The bearing surface 11 is used for arranging functional modules; the connecting assembly 12 is disposed around the carrying surface, and a connecting portion for connecting with an adjacent veneer structure is disposed on the connecting assembly 12.
The functional modules may be directly mounted on the bearing surface 11, or may be fixed on the bearing surface 11 by a special mounting structure, and so on. The connecting portion of the connecting assembly 12 is used to connect two adjacent single-plate structural bodies, and optionally, a routing channel may be further disposed on the connecting assembly 12 for routing. The functional modules are arranged on the bearing surface, and the wiring structure can be simplified by realizing wiring connection of the modules on the connecting assembly.
As another optional implementation manner of this embodiment, the single board structural bodies 10 in the guidance and control assembly correspond to the respective function modules one to one, that is, only one function module is disposed on one single board structural body 10. The arrangement mode can be used for installing the veneer structure body according to actual conditions, is convenient for realizing the combination of the functional modules, and is simple and easy to assemble.
The embodiment of the invention also provides a guidance and control system, which comprises the guidance and control assembly and the functional module in the embodiment shown in fig. 1-2. The functional module is arranged in a cavity formed by two adjacent single-plate structural bodies 10 of the guide and control assembly. As shown in fig. 2, the functional modules include a base module 20 and an inertia measurement module 30, and the functional modules are connected by a wire, where the wire is disposed in a wire channel on the single board structure.
In the guidance and control system provided by this embodiment, each functional module is disposed in a cavity formed by two adjacent single board structures, and the single board structures adopt stacked structural designs, and after the functional modules are disposed, the functional modules are stacked in series board by board to form a complete machine, so as to achieve integrated disposition of the guidance and control system.
Specifically, the functional modules include a base module 20 and an inertial measurement module 30. Optionally, an expansion module 40 may be further included, and the guidance and control system adopts a modular design, and can be flexibly configured according to the actual needs of the target.
The base module 20 includes an interface board, a computer board, a power board, and an external connector printed board 21, which is connected to the interface board, the computer board, and the power board, for providing an electrical interface to the outside. As shown in fig. 2, a pair of external connector printed boards 21 may be provided on the single plate structure body 10 on the uppermost layer of the pilot assembly. Please refer to fig. 3 for the functions of the interface board, the computer board, the power board, and the inertia measurement board.
As shown in fig. 3, the interface board is used to acquire data from the target and send the data to the computer board for processing. Specifically, the interface board can complete interface conversion, provide an external data communication interface, and realize communication information interaction with an external system. Optionally, a satellite positioning circuit combining and receiving circuit for expanding the navigation module may be reserved on the interface.
The computer board is connected with the interface board and used for forming a system control instruction based on the data sent by the interface board and sending the control instruction to the power board. Specifically, the computer board performs system data processing, fire control, navigation/guidance algorithm operation, control command production, and system flight control.
And the power board is connected with the computer board and used for realizing the steering engine control, time sequence power distribution and power management of the target body based on the control instruction. Specifically, the function of the power board can be divided into three parts: the steering engine control part is used for realizing the driving and the control of the steering engine; the time sequence power distribution part is used for realizing time sequence power distribution control of the whole system, providing multi-path controllable power distribution output and finishing the configuration requirements of functions of missile wing/control surface unfolding, thermal battery activation, engine ignition, fuse relief and the like; and the power supply management part is used for completing the functions of combining and conditioning the primary power supply of the system.
The inertia measurement module is used for measuring the three-axis angular velocity and the three-axis acceleration of the missile and sending the three-axis angular velocity and the three-axis acceleration to the computer board. Optionally, the inertial measurement module is connected to the computer board via SPI (serial peripheral interface). The inertial measurement module comprises a gyroscope, an accelerometer and a processing circuit, and can be formed into four types according to different matching, specifically, as shown in the following table:
TABLE 1 Combined types of inertial measurement modules
| Serial number | Combination of | Type selection of top | Accelerometer model selection |
| 1 | Combination 1 | MEMS type | MEMS type |
| 2 | Combination 2 | Optical fiber type | Quartz type |
| 3 | Combination 3 | Hemispherical resonant mode | Quartz type |
| 4 | Combination 4 | Hemispherical resonant mode | MEMS type |
In particular, the interface board, the computer board, the power board, and the inertial measurement module are described in detail in the following description, respectively.
Referring to fig. 3, the interface board includes an interface conversion circuit, a satellite positioning circuit, and a secondary power conversion circuit. The interface conversion circuit is connected with a main control circuit of the computer board and mainly comprises a conversion chip with a preset interface, and the conversion chip is used for realizing conversion of an external communication interface and level conversion. The interface type of the conversion chip of the preset interface CAN be specifically set according to actual conditions, and for example, the conversion chip CAN include a CAN bus interface, a gigabit ethernet interface, an RS422 serial port, an RS232 serial port, a 1M/4M compatible 1553B interface, an LVDS bus interface, a PAL video input interface and an output interface.
The satellite positioning circuit (also called as GNSS module) is connected to the main control circuit of the interface board, and the satellite positioning circuit is used for receiving the positioning data of the target body and providing the calculation result of the positioning data to the main control circuit. Specifically, as shown in fig. 3, an input end of the GNSS module is connected to the launch platform antenna and the pop-up antenna, respectively, and an output end of the GNSS module is connected to the main control circuit of the computer board, and is configured to resolve the received positioning data and send a result of the resolution to the main control circuit of the computer board. Namely, the GNSS module can receive and resolve GPS and Beidou radio frequency signals and provide resolved assembly speed and three-dimensional position information for a main control circuit of the computer. The data content mainly comprises Beidou positioning information, GPS positioning information, Beidou and GPS mixed positioning information and satellite state data. The GNSS module circuit and the main control circuit of the computing board adopt Uart communication.
The secondary power supply conversion circuit of the interface board is connected with the primary power supply combination of the power board and is used for converting the output voltage of the primary power supply combination into the working voltage of the interface board. For example, the output voltage of the primary power supply combination of the power board is 28V, the secondary power supply conversion circuit converts the 28V power supply to +5V, +3.3V, +1.8V, +1.2V, +1.0V power supply voltage, and the secondary power supply for the interface board is provided.
Referring to fig. 3, the computer board includes a main control circuit, an ADC circuit, and a secondary power conversion circuit. The main control circuit is provided with a processing system port and a programmable logic unit port. The processing system port is used for hooking a memory, a bus interface and a network interface; the port of the programmable logic unit is connected with a preset interface conversion chip of the interface board and used for realizing data interaction. The main control circuit CPU chip can consider the high-speed interaction requirements of a processing part and a logic part, an XC7Z030 chip of Xilinx company is selected to replace a traditional DSP + FPGA framework, the chip is internally packaged based on a ZYNQSoC system structure and comprises a processing system (PS end) and a programmable logic unit (PL end), a calculation task can be flexibly and rapidly configured between the two parts according to actual conditions, the processing part and the logic part can fully exert respective advantages, the resource utilization rate is effectively improved, meanwhile, the circuit space can be saved, and the system power consumption is reduced. DDR3 dynamic memory RAM, EEPROM memory, CAN bus interface and gigabit Ethernet interface are realized by hanging PS end; an information interaction channel of each communication interface chip of the interface board is built through a PL (field programmable gate array) end (FPGA), and the information interaction channel mainly comprises 6 paths of RS422 serial ports, 2 paths of RS232 serial ports, 1M/4M compatible 1553B interfaces, LVDS bus interfaces, photoelectric isolation input (RT addresses), SPI interfaces and other interfaces and functions. The main control circuit mainly completes the calculation functions of guidance control, combined navigation, missile management and the like and the information interaction processing of all modules, and can generate a steering engine PWM (pulse width modulation) switch control signal and a time sequence switch control signal.
The ADC circuit is used for realizing AD sampling of data, and can comprise 8 paths including 4 paths of steering engine potentiometer feedback signals, external V2 voltage, allowed throwing signals, thermal battery voltage and combined power supply voltage.
And the secondary power supply conversion circuit of the computer board is connected with the primary power supply combination of the power board and is used for converting the output voltage of the primary power supply combination into the working voltage of the computer board. For example, the output voltage of the primary power supply combination of the power board is 28V, and the secondary power supply conversion circuit converts the 28V power supply to +5V, +3.3V, +1.8V, +1.2V, +1.0V power supply voltage, and supplies power to the secondary power supply for the computer board. Wherein the +5V power supply is used as a power supply for the steering engine potentiometer at the same time; and the +3.3V power supply is simultaneously used as a power supply for the power board isolation driving chip.
The computer board shown in fig. 3 further includes a steering engine driving interface and a timing distribution control, wherein the steering engine driving interface is used for providing a driving signal to the steering engine control circuit of the power board, and the timing distribution control is used for providing a timing signal to the timing distribution circuit of the power board.
Referring to fig. 3, the power board includes a primary power combiner, a steering engine control circuit, and a timing distribution circuit. And the combination of the primary power supplies is used for the combination of each input power supply so as to provide power for the control system. Each input power supply is provided with a reverse protection circuit, and the reverse protection circuit can be realized by adopting an isolation driving chip. For example, the output voltage of the primary power supply combination is 28V, the combination part completes the combination function of an input power supply of an external system and an input power supply of a thermal battery on the bomb, each power supply is provided with diode reverse protection before combination, and 28V direct current bus power supply is provided for components and other single units on the bomb.
The steering engine control circuit is provided with a plurality of first controllable switches and is used for receiving switch control signals of the computer board and converting the switch control signals into pulse width modulation signals through the first controllable switches so as to realize the steering engine control of the target body. For example, the steering engine control circuit mainly comprises 4 groups of 'H bridge' motor control circuits, comprises a 16-path power MOS (metal oxide semiconductor) tube on-off isolation drive circuit, receives an on-off control signal from a computer board, and realizes the drive and control of the steering engine through PWM (pulse width modulation).
The time sequence power distribution circuit is connected with the time sequence power distribution control interface of the computer board and used for receiving a time sequence switch control signal of the computer board. The time sequence power distribution circuit is provided with a plurality of second controllable switches, and the time sequence power distribution of the target body is realized through the second controllable switches. For example, the time sequence power distribution part comprises 10 power MOS tube switches and an isolation drive circuit, receives a time sequence switch control signal from a computer board, realizes the time sequence power distribution control of the whole system, provides multi-path controllable power distribution output, can meet the configuration requirements of functions such as missile wing expansion, control surface expansion, thermal battery activation, primary engine ignition, secondary engine ignition, fuse power supply, fuse primary solution protection, fuse secondary solution protection, seeker power supply and the like, and can be flexibly configured according to different requirements. As shown in fig. 3, the time sequence distribution circuit of the power board is used for providing 28V voltage for wing unfolding, control surface unfolding, thermal battery activation, primary engine ignition, secondary engine ignition, fuse power supply, fuse primary protection, fuse secondary protection and a seeker; the steering engine control circuit is used for providing PWM signals for the steering engine.
Referring to fig. 3, the inertial measurement module includes an inertial measurement board and an inertial meter, where the inertial meter may be a gyro and an accelerometer; the inertia measurement board comprises an instrument information acquisition conditioning circuit and a secondary power supply conversion circuit.
The types of the gyro and accelerometer instruments can be seen in the table 1, and if the MEMS instrument is selected, the gyro and accelerometer instrument is directly installed on a printed circuit board; if the hemispherical resonant gyroscope, the fiber-optic gyroscope and the quartz accelerometer are selected, a special installation structure for the instrument is required to be configured independently so as to form a main body part of the instrument.
The instrument information acquisition conditioning circuit is connected with an inertial instrument (hereinafter, a gyroscope and an accelerometer are taken as examples) and is used for processing output signals of the gyroscope and the accelerometer and outputting the processed output signals to a computer board in the base module. Specifically, IV conversion is carried out on a current output signal of the quartz accelerometer, AD conversion is carried out after voltage signal conditioning is carried out, and finally a digital signal of an acceleration measurement value is obtained; the spartan6 series FPGA is configured on the board, and the measuring information transmitted by each instrument through the serial port and the SPI is sorted, packaged and sent to the main control circuit of the computer board.
And the secondary power supply conversion circuit of the inertia measurement module is connected with the primary power supply of the power board in a combined way and is used for converting the output voltage of the primary power supply combined way into the working voltage of the inertia measurement module. For example, the output voltage of the primary power supply combination of the power board is 28V, and the secondary power supply conversion circuit converts the 28V power supply to +5V, +3.3V and power supply voltage, and supplies the power supply voltage to the inertia measurement module to supply power by using the secondary power supply.
Referring to fig. 4, the guidance and control system further includes an extension module, and the extension module includes a data link board and a wireless fire control printed board.
The data chain plate comprises a measurement and control transceiving unit, a coding and frame coding unit and a demodulation and decoding unit. The data chain plate is used for establishing wireless links between the bullets and the operating platform and between the bullets, transmitting a target image, telemetering data and the working state of the bullets, which are acquired by the bullet-loaded equipment, to the operating platform end equipment in real time, displaying the target image on a display screen, and returning locking information to the bullet-loaded equipment after an operator analyzes and locks the target; target information sharing can be completed between the bullets, tasks are automatically planned and distributed, and cooperative combat is realized.
The data chain function module mainly completes the functions of image acquisition and compression, framing, coding, modulation and transmission of telemetering data, image data and working state data of the bomb, receiving and demodulation of remote control signals and the like. The guidance control system completes the video acquisition, conversion and fusion to the computing board through an integrated technology; the data chain plate is used for carrying out frame coding, modulation and transmission of telemetering data, receiving, de-spreading, demodulation, decoding and instruction processing of remote control data.
As shown in fig. 5, the measurement and control transceiver unit is connected to the transceiver antenna of the target; the frame coding unit is connected with the computing board in the basic module and used for coding the output data of the computing board and then sending the coded data to the receiving and sending antenna of the target body through the measurement and control receiving and sending unit; and the demodulation and decoding unit receives the data of the transmitting and receiving antenna of the target body through the measurement and control transmitting and receiving unit, demodulates and decodes the data and then sends the demodulated and decoded data to the computer board.
The computer board sends the collected video image information, the on-missile telemetering data and the on-missile state information to a framing coding module of the data chain plate to complete framing and coding of data, generates a baseband telemetering signal, directly carries out frequency conversion on the signal through a transmitting channel of the measurement and control transceiver module, outputs the signal to an external video front end to be sent to an on-missile transceiver antenna, and transmits the signal. The on-missile data chain antenna receives the remote control signal outside the missile, the remote control signal passes through the radio frequency front end and is directly converted into a baseband signal by a receiving channel of the measurement and control transceiver module, the baseband signal is sent to the remote control demodulation decoding module to be converted into a baseband data stream, and the baseband data stream is sent to the computer board after being processed to complete a corresponding instruction task.
Referring to fig. 4, the extension module in the guidance and control system further includes a wireless fire control printed board, where the wireless fire control printed board includes: a carrier end unit and a missile upper end unit; the carrier end unit is arranged in a cavity formed by two adjacent single-plate structural bodies. As shown in fig. 6, the carrier end unit includes a first processor MCU1, a first wireless communication node 1 and a power supply connected, and is used for information processing and wireless communication, and includes a second processor MCU2 and a second wireless communication node 2 connected.
The wireless fire control printed board is specially used for a shaped aircraft carrying platform which cannot be adaptively modified, the problem of fire control information interaction between weapon load and the platform is solved, information such as aircraft downloading, bullet feedback and fire control flow is realized in a wireless transmission mode, and an operator can complete a series of operations such as monitoring, activating, binding and throwing of the state of a bullet. The mounting and putting of the platform on the bomb without electric cross-linking can be realized, and the adaptability of the mounting platform of the bomb is greatly improved.
The wireless fire control printed board consists of a carrier end and a bullet upper end, the bullet upper end is integrated in the guide control integrated assembly as an expansion module, and information interaction is shown in the following figure 6. The wireless fire control printed board mainly comprises an MCU module, a wireless communication node and a power supply, and is respectively responsible for information processing and wireless communication.
As an optional implementation manner of this embodiment, the guidance and control system may only include a base module and an inertial measurement module (including an inertial measurement board and an inertial meter), and then the routing structures between the base module and the inertial measurement module refer to fig. 7, and the inertial meter is disposed on the single board structure at the lowest layer of the guidance and control assembly.
As another optional implementation manner of this embodiment, the guidance and control system may include a base module, an inertia measurement module, and an extension module, and the routing structure between the modules is shown in fig. 8.
The modules are connected through inter-board connectors and inter-board cables (not shown in the figure), so that transmission of interactive signals such as an internal serial bus, a control signal and a power supply is realized. The top layer of the whole machine is provided with an external connector printed board, an external electrical interface is provided, and the interaction of the assembly and various external information is completed.
The guidance and control system provided by the embodiment of the invention has the advantages of high integration, small volume and light weight, adopts the latest software and hardware optimization design, selects the current latest main device with high cost performance from the device selection, and uses the design idea of foreign high-integration miniaturized products for reference in the design concept. The system has strong processing capacity, adopts a new generation of high-performance and low-power-consumption SOC processor, adopts a dual-core Arm9+ FPGA structure and an ARM processor dominant frequency of 800MHz/1GHz, can realize data processing and hardware acceleration, and also highly integrates functions of a CPU, a DSP, an ASSP and a mixed signal on a single device, so that the assembly can support combined navigation, Kalman filtering, image identification processing and the like; according to the specific requirements of component performance and cost, the same series of chips XC7Z030, XC7Z015 or XC7Z012S which can be replaced in situ can be selected to form a high-performance, medium-performance and low-performance computer board. Abundant interface resources, abundant peripheral interfaces, support the connection of various peripherals, have strong expandability and meet the expansion requirements of various peripherals. The IMU has good expansibility, and the inertial instrument supports an MEMS type, a fiber optic gyroscope and a hemispherical resonant gyroscope; the accelerometer supports MEMS type, quartz type. Different types of guidance systems are supported, and the use requirements of the satellite/laser semi-active/uncooled infrared image/millimeter wave radar/anti-radiation radar guidance weapon are met. The expansion type with the wireless communication module supports a wireless fire control launching mode, and normal use of a weapon system can be realized through a wireless fire control scheme under the condition that a loader fire control system is not changed. The expansion type with the data link module supports the target hitting mode of cooperation among weapons and human-in-loop.
Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations fall within the scope defined by the appended claims.
Claims (13)
1. A pilot assembly, comprising:
a plurality of stacked single plate structures; the cavity formed by two adjacent single-plate structural bodies is used for arranging a functional module, and the functional module comprises a basic module and an inertia measurement module;
the wiring channel is arranged on the single board structure body; and the wiring channel is used for arranging wiring for connecting each functional module.
2. The pilot assembly of claim 1, wherein the single-plate structure comprises:
the bearing surface is used for arranging the functional module;
and the connecting component is arranged around the bearing surface, and is provided with a connecting part which is used for connecting the adjacent veneer structural bodies.
3. The guidance and control assembly according to claim 2, wherein the single board structures correspond to the functional modules one to one.
4. A guidance and control system, comprising:
the pilot assembly of any one of claims 1-3;
the function module is arranged in a cavity formed by two adjacent single-board structural bodies of the guide control assembly; the functional modules comprise a basic module and an inertia measurement module, the functional modules are connected through routing wires, and the routing wires are arranged in routing channels on the single board structure.
5. The system of claim 4, wherein the base module comprises:
the interface board is used for acquiring data from the target body and sending the data to the computer board;
the computer board is connected with the interface board and used for forming a system control instruction based on the data sent by the interface board and sending the control instruction to the power board;
the power board is connected with the computer board and used for realizing steering engine control, time sequence power distribution and power management of the target body based on the control instruction;
and the external connector printed board is connected with the interface board, the computer board and the power board and is used for providing an electrical interface for the outside.
6. The system of claim 5, wherein each of the base modules is disposed in one-to-one correspondence with the veneer structure.
7. The system according to claim 5 or 6, wherein the interface board comprises:
the interface conversion circuit is connected with the main control circuit of the computer board; the interface conversion circuit comprises a preset interface conversion chip and is used for realizing conversion and level conversion of an external communication interface;
the satellite positioning circuit is connected with the main control circuit of the interface board; the satellite positioning circuit is used for receiving positioning data of the target body and providing a resolving result of the positioning data to the main control circuit;
and the secondary power supply conversion circuit is connected with the primary power supply combination of the power board and is used for converting the output voltage of the primary power supply combination into the working voltage of the interface board.
8. The system of claim 5 or 6, wherein the computer board comprises:
the main control circuit is provided with a processing system port and a programmable logic unit port; the processing system port is used for hooking a memory, a bus interface and a network interface; the port of the programmable logic unit is connected with a preset interface conversion chip of the interface board and used for realizing data interaction;
the ADC circuit is used for realizing AD sampling of data;
and the secondary power supply conversion circuit is connected with the primary power supply combination of the power board and is used for converting the output voltage of the primary power supply combination into the working voltage of the computer board.
9. The system of claim 5 or 6, wherein the power board comprises:
the primary power supply combiner is used for combining all input power supplies so as to provide power for the guidance and control system; each input power supply is provided with a reverse protection circuit;
the steering engine control circuit is provided with a plurality of first controllable switches and is used for receiving switch control signals of the computer board and converting the switch control signals into pulse width modulation signals through the first controllable switches so as to realize the steering engine control of the target body;
and the time sequence power distribution circuit is provided with a plurality of second controllable switches and is used for receiving the time sequence switch control signals of the computer board and realizing the time sequence power distribution of the target body through the second controllable switches.
10. The system of claim 4, wherein the inertial measurement module comprises an inertial measurement board and an inertial meter; wherein, inertia measurement board includes:
the instrument information acquisition conditioning circuit is connected with the inertial instrument; the instrument information acquisition conditioning circuit is used for processing the output signal of the inertial instrument and outputting the processed output signal to a computer board in the basic module;
and the secondary power supply conversion circuit is connected with a primary power supply combination of a power board in the basic module and is used for converting the output voltage of the primary power supply combination into the working voltage of the inertia measurement module.
11. The system of claim 4, further comprising an expansion module comprising a data link board and a wireless fire control printed board.
12. The system of claim 11, wherein the data link chain comprises:
the measurement and control receiving and transmitting unit is connected with the receiving and transmitting antenna of the target body;
the frame coding unit is connected with the computing board in the basic module and used for coding the output data of the computing board and then sending the coded data to the receiving and sending antenna of the target body through the measurement and control receiving and sending unit;
and the demodulation and decoding unit receives the data of the transmitting and receiving antenna of the target body through the measurement and control transmitting and receiving unit, demodulates and decodes the data and then sends the demodulated and decoded data to the computing board.
13. The system of claim 11 or 12, wherein the wireless fire control printed board comprises:
a carrier end unit and a missile upper end unit; the carrier end unit is arranged in a cavity formed by two adjacent single-plate structural bodies;
the carrier end unit comprises a first processor, a first wireless communication node and a power supply which are connected; the carrier end unit is used for information processing and wireless communication;
the pop-up end unit comprises a second processor and a second wireless communication node which are connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911220816.4A CN111025967A (en) | 2019-12-03 | 2019-12-03 | Guide control assembly and guide control system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911220816.4A CN111025967A (en) | 2019-12-03 | 2019-12-03 | Guide control assembly and guide control system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114018102A (en) * | 2021-08-12 | 2022-02-08 | 北京星途探索科技有限公司 | Combined missile main controller |
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2019
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114018102A (en) * | 2021-08-12 | 2022-02-08 | 北京星途探索科技有限公司 | Combined missile main controller |
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Address after: 100045 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Applicant after: Beijing Star glory Space Technology Co.,Ltd. Applicant after: Beijing Star glory Technology Co.,Ltd. Applicant after: Shaanxi star glory Space Technology Co.,Ltd. Address before: 329, floor 3, building 1, No. 9, Desheng South Street, Daxing Economic and Technological Development Zone, Beijing 100176 Applicant before: BEIJING XINGJIRONGYAO SPACE TECHNOLOGY Co.,Ltd. Applicant before: Beijing Star glory Technology Co.,Ltd. Applicant before: Shaanxi star glory Space Technology Co.,Ltd. |