CN211041964U

CN211041964U - Rocket-borne integrated electronic system

Info

Publication number: CN211041964U
Application number: CN201921889381.8U
Authority: CN
Inventors: 江良伟; 漆光平; 石翔; 赵也倪; 曹扬
Original assignee: Beijing Interstellar Glory Space Technology Co Ltd
Current assignee: Beijing Star Glory Space Technology Co Ltd
Priority date: 2019-07-08
Filing date: 2019-11-04
Publication date: 2020-07-17
Anticipated expiration: 2029-11-04

Abstract

The utility model relates to an electrical system designs technical field on arrow (bullet), concretely relates to arrow carries synthesizes electronic system. The system comprises at least one functional module; the functional module comprises at least one of a power supply module, a power distribution module, a time sequence module, an inertial navigation module and a satellite navigation module; the main control module is connected with each functional module; the main control module is used for receiving the data of each functional module and processing the data to form a corresponding control signal so as to control the object to be controlled. The main control module is matched with each functional module to form a system capable of meeting different requirements, the module division mode improves the integration level of the system, meanwhile, the weight and the complexity of the electrical system are reduced, the weight of the whole machine is reduced, the integrated design reduces the interconnection cable network among the single machines, the reliability of the whole electrical system is finally improved, and the requirement of flight control of an object to be controlled is met.

Description

Rocket-borne integrated electronic system

Technical Field

The utility model relates to an electrical system designs technical field on arrow (bullet), concretely relates to arrow carries synthesizes electronic system.

Background

The rocket-borne integrated electronic system is an important core single machine of a carrier rocket (or missile weapon) electrical system, can realize the functions of guidance control, attitude control, combined navigation, inertial navigation, satellite navigation, power supply and distribution control, time sequence control, autonomous safety control and the like of the carrier rocket, and realizes arrow testing and launching flow control under the cooperation of a ground test and launch control system.

The concept of integrated electronic systems comes from the complex electronic systems of the aerospace field, which are then increasingly adopted. The method is firstly adopted on the satellite, so that the reliability and the integration of the satellite are further improved, and the method is gradually popularized and used in the field of carrier rockets at present.

The rocket-borne integrated electronic system is called as a rocket (missile) borne single machine in the traditional carrier rocket (or missile weapons), belongs to a distributed structure, consists of a plurality of single machines, and generally comprises a rocket-borne computer, an integrated controller, a time schedule controller, a power distributor, an inertial navigation device, a satellite navigation receiver and other equipment. Each single machine has independent and complete functions, the interior of each single machine comprises a structural part, a plurality of printed boards and application software, and the single machines carry out instruction control and data communication through a system bus.

However, in the electrical system adopting the distributed single machine structure, because there are many single machines in the distributed structure, the probability of the failure of the whole electrical system is increased, and the reliability of the system is affected.

SUMMERY OF THE UTILITY MODEL

In view of this, the embodiment of the present invention provides an arrow-mounted integrated electronic system to solve the problem of low reliability of the existing electrical system.

According to a first aspect, the embodiment of the utility model provides an arrow carries synthesizes electronic system includes:

at least one functional module; the functional module comprises at least one of a power supply module, a power distribution module, a time sequence module, an inertial navigation module and a satellite navigation module;

the main control module is connected with each functional module; the main control module is used for receiving the data of each functional module and processing the data to form a corresponding control signal so as to control the object to be controlled.

The embodiment of the utility model provides an arrow carries integrated electronic system, adopts the form of module to carry out the division to arrow carries integrated electronic system's function; the main control module is matched with each functional module to form a system capable of meeting different requirements, the module division mode improves the integration level of the system, meanwhile, the weight and the complexity of the electric system are reduced, the weight of the whole machine is reduced, the integrated design reduces the interconnection cable network among the single machines, the reliability of the whole electric system is finally improved, and the requirement of flight control of the object to be controlled is met.

With reference to the first aspect, in a first implementation manner of the first aspect, the master control module includes a system on chip.

The embodiment of the utility model provides an arrow carries integrated electronic system adopts the SOC as host system's core circuit, perhaps also can understand for adopting the core processor and the real-time operating system of full programmable SOC, breaks the mode that the tradition adopted CPU and FPGA logic operation, for operation artificial intelligence algorithm provides the software and hardware environment, has improved the debugging scheme, has improved work efficiency greatly.

With reference to the first aspect, in a second implementation manner of the first aspect, the power supply module includes:

the input end of the filtering unit is connected with an external power supply;

the power supply unit is provided with at least one power supply subunit, and the power supply subunits are connected in parallel and used for outputting different voltages; the input end of the power supply unit is connected with the output end of the filtering unit, and the output end of the power supply unit is connected with the rest of the functional modules.

The rocket-borne integrated electronic system provided by the embodiment of the utility model can filter the external power supply through the filtering unit, so that the electric signal output by the power supply module can meet the isolation requirement; meanwhile, at least one power supply subunit is integrated in the power supply unit, so that the power supply module can convert an external power supply into a plurality of paths of power supply outputs with different voltages and powers.

With reference to the second implementation manner of the first aspect, in a third implementation manner of the first aspect, the filtering unit includes an electromagnetic compatibility filter, a first diode, and a low-pass filter, which are sequentially connected in series; wherein the first diode is used for suppressing transient voltage.

The embodiment of the utility model provides an electronic system is synthesized to arrow-borne adopts first diode to prevent that higher voltage from appearing in the generating line, damages components and parts to the reliability of this system has been guaranteed.

With reference to the first aspect, in a fourth implementation manner of the first aspect, the power distribution module includes:

the input end of the power unit is connected with a bus of the object to be controlled; the power unit is provided with a power distribution switching circuit which is used for outputting at least one controllable power distribution source;

the input end of the control unit is connected with the internal bus and used for receiving a control command of the main control module; the control unit is provided with a switch driving circuit, and the switch driving circuit is used for driving the action of the power distribution switch circuit.

With reference to the fourth implementation manner of the first aspect, in the fifth implementation manner of the first aspect, the power unit includes:

the first branch and the second branch are connected in parallel; the first branch circuit comprises an anti-reverse-filling circuit, a bus switch circuit and the power distribution switch circuit which are sequentially connected in series; the second branch comprises a transient suppression circuit; the reverse-flow prevention circuit comprises a second diode and a first switching device and is used for preventing the current of the bus from flowing backwards; the bus switching circuit includes a second switching device and the distribution switching circuit includes a third switching device;

the control unit includes: a first controller and the switch driving circuit; the input end of the first controller is connected with the internal bus, the output end of the first controller is connected with the switch driving circuit, and the first controller is used for outputting a pulse width modulation signal based on the control command of the main control module so that the switch driving circuit outputs a level signal; the level signal is used to drive the second switching device and the third switching device.

The embodiment of the utility model provides an electronic system is synthesized to arrow-borne adopts the cooperation of switching device and controller, realizes high-power miniaturized intelligent power distribution technique, reduces former bulky unit distribution and becomes the module formula integration inside synthesizing electronic system, has reduced entire system's volume.

With reference to the fifth embodiment of the first aspect, in the sixth embodiment of the first aspect, the control unit further includes: a sampling circuit; the sampling circuit is used for collecting feedback signals of all circuits in the power unit and transmitting the feedback signals back to the first controller; the feedback signal includes voltage, current, and temperature.

With reference to the first aspect, in a seventh implementation manner of the first aspect, the timing module includes a second controller, a driver, and a fourth switching device, which are sequentially connected in series;

the input end of the second controller is connected with an internal bus of the object to be controlled and used for forming a level signal based on a flight control time sequence instruction output by the internal bus so as to enable the driver to output the level signal;

the level signal output by the driver is used for driving the action of the fourth switching device;

the fourth switching device is to output a timing based on the level signal.

The rocket-borne integrated electronic system provided by the embodiment of the utility model has the advantages that the size of the adopted switch device is very small, but the flowing current is very large, dozens of or even hundreds of circuits of initiating explosive devices can be integrated on one printing plate, and the size of an electronic instrument is greatly reduced; meanwhile, because the internal resistance of the switching device is very small, the flowing large current basically cannot generate heat, and the workload of the heat dissipation design of the instrument is reduced.

With reference to the seventh implementation manner of the first aspect, in an eighth implementation manner of the first aspect, the timing module further includes a timing extraction unit, configured to feed back the timing output by the fourth switching device to the second controller; and the second controller sends the received time sequence to the main control module so that an interpreter can determine whether the time sequence module normally sends out a time sequence signal.

With reference to the first aspect, in a ninth implementation of the first aspect, the inertial navigation module includes:

the gyroscope unit is provided with at least three independent fiber optic gyroscopes which are respectively used for measuring angles in three directions;

the accelerometer unit is provided with at least three independent accelerometers which are respectively used for measuring the accelerations in three directions;

and the interface circuit is respectively connected with the gyro unit and the meter adding unit, is used for forming an inertia measurement result based on the angles in the three directions and the acceleration in the three directions, and outputs the inertia measurement result to the main control module.

With reference to the first aspect, in a tenth implementation of the first aspect, the satellite navigation module includes:

the radio frequency unit is provided with at least 2 radio frequency signal receiving channels;

the baseband processing unit is connected with the output end of the radio frequency unit and is used for performing baseband processing on the radio frequency signal;

and the information processing unit is connected with the baseband processing unit and used for carrying out PVT (virtual basic test) calculation on the data processed by the baseband and outputting PVT calculation results to the main control module.

With reference to the first aspect, or any one of the first to tenth embodiments of the first aspect, in an eleventh embodiment of the first aspect, the main control module is connected to the power distribution module and the timing module through a first bus respectively; the main control module is respectively connected with the inertial navigation module and the satellite navigation module through a second bus; wherein a communication rate of the first bus is greater than a communication rate of the second bus.

The embodiment of the utility model provides an arrow carries synthesizes electronic system adopts the integration of high-speed bus and low-speed bus, has both considered big data transfer, compromises the design interface of traditional module again, based on operating system and Ethernet's debugging technique application, has improved the debugging scheme, has improved work efficiency greatly.

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 embodiments or the technical solutions in 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 for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 is a schematic structural diagram of an rocket-borne integrated electronic system according to an embodiment of the present invention;

fig. 2 is a schematic structural diagram of a system bus according to an embodiment of the present invention;

fig. 3 is a functional block diagram of a master control module according to an embodiment of the present invention;

fig. 4 is a schematic structural diagram of a power module according to an embodiment of the present invention;

fig. 5 is a functional block diagram of a power module according to an embodiment of the present invention;

fig. 6 is a schematic structural diagram of a power distribution module according to an embodiment of the present invention;

fig. 7 is a functional block diagram of a power distribution module according to an embodiment of the present invention;

fig. 8 is a schematic structural diagram of a timing module according to an embodiment of the present invention;

fig. 9 is a functional block diagram of a timing module according to an embodiment of the present invention;

fig. 10 is a functional block diagram of an inertial navigation module according to an embodiment of the present invention;

fig. 11 is a functional block diagram of a satellite navigation module 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 embodiments of the present invention will be clearly and completely described below with reference to the accompanying 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. Based on the embodiments in the present invention, all other embodiments obtained by the skilled in the art without creative work belong to the protection scope of the present invention.

It should be noted that the rocket-borne integrated electronic system according to the embodiments of the present invention may be applied to an electrical system of a launch vehicle or a missile weapon, or may be applied to other space vehicles (such as satellites), aircraft integrated electronic systems, and highly reliable electronic devices. Accordingly, the object to be controlled according to the embodiment of the present invention may be a launch vehicle, a missile weapon, or other spacecraft, etc.

Fig. 1 shows a schematic structural diagram of an rocket-borne integrated electronic system in an embodiment of the present invention. As shown in fig. 1, the system includes a main control module 10, and at least one functional module. The main control module 10 is connected to each functional module, and is configured to receive output data of each functional module, process the data, and output a corresponding control signal, so as to control an object to be controlled.

The functional module can be at least one of a power supply module, a power distribution module, a time sequence module, an inertial navigation module and a satellite navigation module, and each object to be controlled can be matched with different functional modules according to respective functional requirements, namely, different functions are realized through the combination of the functional modules.

The core part of the main control module 10 may adopt a programmable chip, such as a single chip, an FPGA, etc.; other chips, such as a system on a chip, etc., may also be employed. The main control module is the core of the whole rocket-borne integrated electronic system and is used for realizing the control of the whole system. Alternatively, other CPUs and other operating systems may be used in the main control module 10.

The power module 20 is used to convert an external input power into a power required for the operation of each module in the system, for example, the external input power is 28V dc, and the power required for the operation of the modules in the system is 5V, 15V, etc., so that the power module 20 is required to convert the input 28V dc into 5V, 15V voltages, etc., respectively. Alternatively, the power module 20 may be a highly reliable power module, or a discrete component, and the specific structural details of the power module 20 are not limited, so long as the power module 20 can perform the above-mentioned functions.

The power distribution module 30 adopts an intelligent power distribution scheme, and is used for realizing the functions of power distribution, power conversion, power outage, priming system ignition and the like of electronic equipment on an arrow (bullet). Specifically, the power distribution module 30 implements that after power-on, 1 path of power supply (e.g., + B1) is output to directly supply power to the power module 20 of the rocket-borne integrated electronic system, and receives the instruction of the main control module as the receiving station (NT) of the internal bus (e.g., FC-AE-1553), thereby completing unified power supply and distribution control of the rocket-borne electrical devices, implementing output of 3 paths of controllable power distribution power supplies (e.g., + B2, + B3, + BF), and simultaneously performing real-time test on the power supply voltage and current of the power distribution path, and feeding the result back to the main control module 10.

The time sequence module 40 is a direct driver of various actions of the carrier rocket in the whole flight process, and can be divided into a time sequence module i and a time sequence module ii according to different loads (initiating explosive devices and electromagnetic valves), for example, and the time sequence module i executes instructions sent by the main control module according to the flight control time sequence of the whole flight trajectory of the carrier rocket.

The inertial navigation module 50 outputs information such as acceleration and angle to the main control module 10 to complete the integrated navigation function. The satellite navigation module 60 completes the acquisition and tracking of signals, the solving of original observed quantity and the satellite selection, then completes the PVT solution, outputs the information of the position, the speed, the time and the like of the carrier, and sends the information to the main control module 10 to complete the integrated navigation function.

Details regarding the specific structure of each of the above-described modules will be described in detail below.

According to the rocket-borne integrated electronic system provided by the embodiment, functions of the rocket-borne integrated electronic system are divided in a module form; the main control module is matched with each functional module to form a system capable of meeting different requirements, the module division mode improves the integration level of the system, meanwhile, the weight and the complexity of the electric system are reduced, the weight of the whole machine is reduced, the integrated design reduces the interconnection cable network among the single machines, the reliability of the whole electric system is finally improved, and the requirement of flight control of the object to be controlled is met.

Specifically, the main control module 10 is connected to each functional module through a system bus. The main control module 10 is respectively connected with the power distribution module 30 and the timing module 40 through a first bus; the main control module 10 is respectively connected with the inertial navigation module 50 and the satellite navigation module 60 through a second bus; wherein the communication rate of the first bus is greater than the communication rate of the second bus. In the following description, the first bus is referred to as a high-speed bus, and the second bus is referred to as a low-speed bus. The rocket-borne integrated electronic system is based on the fusion of low-speed bus and high-speed bus technologies, and is used for connecting each module in the system and communicating with a single machine outside the system. The high-speed bus comprises FC-AE-1553 and Ethernet, the low-speed bus comprises RS422 and CAN, and the connection schematic diagram of each bus is shown in figure 2. The interconnection of the modules may also adopt other bus forms, such as Glink, 1553B and the like. Here, the specific bus is not limited at all, and it is only necessary to ensure that the main control module 10 is connected to the corresponding module through the high-speed bus and the low-speed bus, respectively.

As shown in fig. 2, the rest of the modules inside the rocket-borne integrated electronic system, except for the power module 20, are interconnected through a bus. For example, the main control module 10, as a main control station (NC), may communicate with the power distribution module 30, the timing module i, and the timing module ii, as a receiving station (NT), in an FC-AE-1553 bus form; the main control module 10 communicates with the inertial navigation module 50 and the satellite navigation module 60 through the RS 422; the communication between the rocket-borne integrated electronic system and the single machine outside the system is realized through Ethernet and CAN. The main control module 10 communicates with the ground test and launch control system through Ethernet and communicates with the central programmer of the measurement system through the CAN bus.

The rocket-borne integrated electronic system adopts the fusion of the high-speed bus and the low-speed bus, not only considers the big data transmission, but also considers the design interface of the traditional module, and the debugging technology based on the operating system and the Ethernet is applied, so that the debugging scheme is improved, and the working efficiency is greatly improved.

Further, the main control module 10 may include a system on chip, as shown in fig. 3, the main control module 10 may receive information such as acceleration and angle output by the inertial navigation module 50 through the RS422, and use the information for inertial navigation calculation; GPS information of the satellite navigation module 60 is received through the RS422, combined navigation calculation is realized together with inertial navigation information, and calculation of guidance and attitude control equations is completed in real time; outputting an attitude control instruction in real time, and outputting a switch state control instruction of the timing sequence module 40 in real time; when the attitude out of control exceeds a specified range in the rocket flying process, the safety self-destruction information on the rocket is given, and the autonomous safety control is realized; the main control station (NC) serving as an FC-AE-1553 bus realizes control and data acquisition of the power distribution module 30, the time sequence module I and the time sequence module II; the control of the on-off input interface, the CAN bus interface, the Ethernet interface and the initiating explosive device low-voltage test interface of the module CAN be realized.

For example, the CPU chip of the main control module 10 adopts Xilinx fully programmable SOC (i.e., ZYNQ) with a model of XC7Z045, runs a real-time embedded operating system, and each interface of the system is reasonably divided according to the respective characteristics of PS (ARM) and P L (FPGA) of XC7Z045 processors, DDR3 dynamic memory RAM, EEPROM, eMMC flash memory, SPI configuration memory, CAN bus interface, Ethernet interface, etc. are connected to PS (ARM) of XC7Z045 processors, FC-AE-1553 interface, isolated RS422 serial port, switching input/output interface, sampling monitoring circuit, etc. are implemented by P L (FPGA) of XC7Z045 processors.

Further optionally, the DDR3 memory is implemented by using an MT41K256M16 dynamic DDR3DRAM chip of Micron company, 2 chips are connected in parallel, the total bit width is 32bit, and the capacity is 1G, the EMMC F L ASH data memory is implemented by using an MTFC16GAAAADV large-capacity EMMC flash memory of Micron company, the QSPI F L ASH is implemented by using S25F L256 of Cypress company, the EEPROM is generated by using AT24C256C of ATME L company, a plurality of power supply tracks of 1.0V, 1.2V, 1.5V, 1.8V, 3.3V, 5V and the like are needed on the main control module 10, the SIT5156 type temperature compensation crystal oscillator of Sicompany is used for generating crystal oscillator, the index requirement of 5ppm is met, and the RS232 level conversion is achieved by using a Mod26 TC 2CDE of L inear company.

The CAN bus interface is realized by adopting a CAN bus IP core at the PS end of an XC7Z045 processor and an external CAN transceiver chip, the CAN transceiver adopts a TJA1040T interface chip of NXP company, the realization of double Ethernet interfaces is realized by ETH0 and ETH1 interfaces at the PS end of the XC7Z045 processor, the two controllers respectively correspond to 88E1518 of two MARVA L companies, and the transformer adopts H5007N L of SE of PU L company.

The RS422 serial port is realized by adopting an ADI (advanced digital interface) 2682 isolated serial port transceiver of ADI (advanced digital interface) company, the ADM2682 serial port transceiver has an isolation function, FC-AE-1553 bus communication is realized by combining a protocol layer IP (Internet protocol) mode through a high-speed GTX (GTX) interface at the P L end, a 100MHz differential crystal oscillator is adopted, the impedance of a transmission line needs to be controlled during circuit design, the quantity of via holes needs to be controlled, the connecting lines need to be kept equal in length, the forms and parameter selections of switching value input interface circuits are the same, the input voltage is 28.5 +/-4V, and the positive lines and the negative lines of all switching value input signals are.

The operating system mainly completes the following work of carrying out power-on self-loading of the operating system and preparation of an operating state of application software, controlling input and output information of peripheral equipment of an rocket integrated electronic system (the following system) through an FC-AE-1553 bus, controlling input and output information of the peripheral equipment of the system through an RS422 bus, controlling input and output information of the peripheral equipment of the system through an Ethernet bus, controlling input and output information of the peripheral equipment of the system through a CAN bus, carrying out AD data acquisition, carrying out IO input and output control, receiving level signals of the peripheral equipment, carrying out interrupt triggering and processing, providing a stable, reliable and standard basic network application protocol interface, providing a hanging and access interface of system hardware storage equipment, providing a system FPGA general access interface, and providing a system F L ASH reading and programming management and control interface.

The main control module 10 adopts a core processor and a real-time operating system of a fully programmable SOC (system on chip), breaks through the traditional mode of adopting a CPU bare computer to run, and provides software and hardware environment for calculating an artificial intelligent control algorithm. Based on the operating system and the application of the debugging technology of Ethernet, the debugging scheme is improved, and the working efficiency is greatly improved.

Fig. 4 shows a schematic diagram of a power supply module 20, which includes a filtering unit 21 and a power supply unit 22 connected in series as shown in fig. 4. The filtering unit 21 is connected to an external power supply, and is configured to filter an electrical signal of the external power supply, and may use an electromagnetic compatibility filter, a low-pass filter, or a combination of the two. The power supply unit 22 comprises at least one parallel power supply subunit, each for outputting a different voltage. For example, the power supply unit 22 includes a power supply subunit 1, a power supply subunit 2, …, and a power supply subunit n. The number of the power supply subunits can be specifically set according to actual conditions, and is not limited in any way. Wherein, the input end of the power supply unit 22 is connected with the output end of the filtering unit 21, and the output end of the power supply unit 22 is connected with the other functional modules. For example, there are 5 types of power supplies required for operating each module in the rocket-borne integrated electronic system, which are +5V, +5V1, +5V2, + 15V3 and +5V3, respectively, and then 5 power supply sub-units connected in parallel are required in the corresponding power supply unit 22 to output corresponding voltages respectively.

The filtering unit 21 is used for filtering the external power supply, so that the electric signal output by the power supply module 20 can meet the isolation requirement; meanwhile, at least one power supply subunit is integrated in the power supply unit 22, so that the power supply module 20 can convert an external power supply into a plurality of power supply outputs of different voltages and powers.

Further, fig. 5 shows a specific structural diagram of the power module 20. As shown in fig. 5, the filtering unit 21 includes an electromagnetic compatibility filter 211 (i.e., an EMC filter), a first diode 212, and a low-pass filter 213 (i.e., an EMI filter) connected in series in this order. The first diode 212 is used to suppress the transient voltage, and the first diode 212 may also be referred to as a transient voltage suppression diode.

The power module 20 functions to convert the primary DC voltage into multiple DC outputs of different voltages and powers via DC/DC conversion, and to meet isolation requirements. The output of the power module 20 is used to supply the power voltages required by the main control module 10, the power distribution module 30, the timing module 40, the inertial navigation module 50, the satellite navigation module 60, and the test (wherein the main control module 10, the power distribution module 30, the timing module 40 use +5V, the inertial navigation module 50 use +5V1, the satellite navigation module 60 use +5V2, and the test power supply is ± 15V3, +5V 3). Therefore, the division of the power supply unit 22 into different power supply sub-units takes into full account the reliability, safety and electromagnetic compatibility of the product at the time of design.

The power supply module 20 is mainly composed of an input EMC filter 211, an EMI filter 213, and a power supply unit 22 connected in series. The external +28V power supply input is filtered by an EMC filter 211 formed by a capacitor and an inductor, and a transient voltage suppression diode 212 is added to prevent the bus from generating higher voltage and damaging components. The input power is supplied to the power supply unit 22 through the EMI filter 213 for voltage conversion and electrical isolation.

Fig. 6 shows a schematic structural diagram of the power distribution module 30. As shown in fig. 6, the power distribution module 30 includes a power unit 31 and a control unit 32. Wherein, the input end of the power unit 31 is connected with the bus of the object to be controlled, and the power unit 31 has a distribution switch circuit 311; the power distribution switch circuit 311 is used to output at least one controllable power distribution source. For example, the power distribution switch circuit 311 may be a switch circuit formed by a switching device (e.g., a MOS transistor), or may be a switch circuit formed by other components, and only needs to be ensured to output at least one controllable power distribution source under the driving of the control unit 32.

The input end of the control unit 32 is connected to the internal bus and is configured to receive a control command from the main control module. The control unit includes a switch driving circuit 321, and the switch driving circuit 321 drives the operation of the distribution switch circuit 311.

Specifically, referring to fig. 7, the power unit 31 includes a first branch and a second branch connected in parallel. The first branch circuit comprises an anti-reverse-flow circuit 312, a bus switch circuit 313 and a power distribution switch circuit 311 which are sequentially connected in series. The second branch includes a transient suppression circuit 314. The reverse-flow prevention circuit 312 includes a second diode and a first switching device, and is configured to prevent the current of the bus from flowing backwards; the bus switching circuit 313 includes a second switching device and the distribution switching circuit 311 includes a third switching device.

The control unit 32 includes a first controller 322 and a switch driving circuit 321, an input end of the first controller 322 is connected to the internal bus, and an output end is connected to the switch driving circuit 321; the first controller 322 is configured to output a Pulse Width Modulation (PWM) signal based on a main control module control command, so that the switch driving circuit 321 outputs a level signal; the level signal is used to drive the second switching device and the third switching device.

As an optional implementation manner of this embodiment, the control unit 32 further includes a sampling circuit 323. The sampling circuit 323 is used to collect feedback signals of various circuits in the power unit 31 and transmit the feedback signals back to the first controller 322. Wherein the feedback signal comprises at least one of voltage, current and temperature.

As a specific application example of the power distribution module 30, please refer to fig. 7, the power unit 31 includes an anti-reverse-flow circuit 312, a bus switch circuit 313, a power distribution switch circuit 311, and a transient suppression circuit 314, and the control unit 32 includes a main control circuit FPGA, a switch driving circuit, and a sampling circuit.

In the power unit 31 module, the bus current enters a reverse-flow prevention circuit 312 for preventing reverse flow of the high-voltage power supply, enters a bus switch circuit 313 for controlling the working posture of the aircraft through the reverse-flow prevention circuit 312, enters a power distribution switch circuit 311 for controlling the working state of aircraft equipment through the bus switch circuit 313, and prevents spike voltage from being generated and protects the power distributor through a transient suppression circuit 314. In the control unit 32 module, a main control module control command enters the first controller 322 (i.e., a main control circuit FPGA) through an internal bus, the main control circuit FPGA converts an external timing control command into a PWM signal, and sends the PWM signal to the switch driving circuit 321, the switch driving circuit 321 converts the PWM signal into a level signal and controls the on/off of the bus switch circuit 313 and the distribution switch circuit 311, and the sampling circuit 323 acquires voltage, current and temperature parameters generated by each part of the power unit 31 module, and sends the acquired parameters to the main control circuit FPGA to perform information interaction with the main control module through the internal bus.

Further, the anti-reverse-flow circuit 312 includes a second diode and a first switching device, wherein the first switching device may adopt a power MOS transistor, for example, IPB017N10N5 from Infineon, the withstand voltage of the power MOS transistor is 100V, the maximum operating current is 180A, and the maximum junction resistance is 1.7m Ω, the second diode may adopt L tc4357 from L INEAR, the power MOS transistors selected by the bus switching circuit 313 and the distribution switching circuit 311 are also IPB017n10n5 from Infineon, because the distribution current is large and long-time operation, the distribution switches all adopt a redundant design, and share the current by a plurality of MOS transistors to reduce the total heat generation amount, the transient suppression circuit 314 mainly uses a TSV, and protects the distribution circuit by installing the input end and the output end of the power unit 31, thereby preventing the generation of a spike voltage due to an excessively high input voltage, and the TVS transistor selects SY5645A from 873 factory.

The first controller 322 may employ a control FPGA, for example, an FPGA chip A3P1000-PQ208I selected from Actel, an IP core integrated with a high-speed bus FC-AE-1553(NT), a signal filtering IP, and the like. The FPGA is a control center of the power distribution module 30, receives a bus control command, performs operation processing, sends the bus control command to the switch driving circuit 321 to output an MOS switch control signal, and receives a sampling circuit 323 signal, performs processing, and sends the signal to the main control module through a bus. The switch driving circuit 321 receives the PWM signal excitation pulse sent from the control FPGA, and rectifies and filters the PWM signal to output a level signal to drive the MOS transistor to operate. The sampling circuit 323 receives the voltage, current and temperature information from the circuits of the power unit 31, collects the information and transmits the information back to the control FPGA.

The power distribution module 30 is applied to a high-power miniaturized intelligent power distribution technology, and integrates the original large-volume single-machine power distribution into a module form in an integrated electronic system by adopting the cooperation of digital control and MOS (metal oxide semiconductor) tubes.

Fig. 8 is a schematic structural diagram of the timing module 40, and as shown in fig. 8, the timing module 40 includes a second controller 41, a driver 42, and a fourth switching device 43 connected in series in sequence. Wherein, the input end of the second controller 41 is connected with the internal bus of the object to be controlled, and is used for forming a level signal based on the flight control timing command output by the internal bus, so that the driver 42 outputs the level signal; the level signal outputted from the driver 42 is used to drive the fourth switching device 43 to implement timing control. Alternatively, the fourth switching device 43 may be a MOS transistor, that is, the MOS transistor is driven by a level signal, and the timing control is realized by turning on or off the MOS transistor.

Optionally, the timing module 40 further includes a timing extraction unit 44, configured to feed back the timing output by the fourth switching device 43 to the second controller 41, and the second controller 41 sends the received timing to the main control module, so as to tell an interpreter whether the timing module 40 sends a timing signal normally through the main control module. Further optionally, the timing extraction unit 44 includes a light coupling circuit 441 and a shaping circuit 442 connected in series.

As a specific application example of the timing module 40, please refer to fig. 9, the timing module functions as a receiving station (NT) of the FC-AE-1553 in the device to receive the instruction of the main control module, complete the control and driving of the corresponding timing output, output the initiating explosive device timing, the electromagnetic valve timing, the motor forward and reverse rotation control timing, and implement the back detection of the timing output signal.

The second controller 41 in the timing module 40 may be an FPGA, and the fourth switching device 43 may be an MOS transistor, specifically, the FPGA is A3P1000-PQ208I from Actel, the IP core of the high-speed bus FC-AE-1553(NT) is integrated, the signal filtering IP is integrated, and the like, the L T4363 from L T is used as the driver 42, and the driver 42 controls the on/off of the MOS switch through a control form of a charge pump, and the driver 42 and the MOS transistor are partially described below.

To reduce the printed board area, the timing module 40 uses BSC035N10NS5 from Infineon, the main parameters of which are as follows. The working temperature is reduced to-55-175 ℃; the withstand voltage is 100V; the maximum working current is 100A; the maximum junction resistance was 3.5m Ω. The MOS tube of the time sequence module adopts a redundancy design, each path of output uses two MOS tubes, and the current is shared by 2 MOS tubes so as to reduce the total heat productivity.

The MOS tube adopted by the fourth switching device 43 of the timing module 40 has a small volume, but the flowing current is large, dozens of or even hundreds of initiating explosive devices or solenoid valve timing circuits can be integrated on one printed board, and the volume of an electronic instrument is greatly reduced; the MOS tube adopted has small internal resistance, and the flowing large current basically does not generate heat, thereby reducing the workload of heat dissipation design of the instrument; the MOS tube adopted has high switching speed, sensitive reflection, no sensitive direction and convenient installation, and reduces the design difficulty of layout and wiring; the MOS tube driving circuit is simple in design, an integrated chip with a charge pump function is adopted, too much hardware is not added on the original circuit, and the circuit design is simple and reliable.

It should be noted that the switching devices in the power distribution module 30 and the timing module 40 may be MOS transistors, or may also be electromagnetic relays or solid state relays. The switching devices in the power distribution module 30 and the timing module 40 switch different output signals through turning on or off, so as to implement corresponding functions.

Fig. 10 shows a block diagram of the inertial navigation module 50, and as shown in fig. 10, the inertial navigation module 50 includes a gyro unit 51, a meter unit 52, and an interface circuit 53. The gyro unit 51 has at least three independent fiber optic gyros for measuring angles in three directions; for example, there are 3 independent fiber optic gyroscopes for measuring X, Y and the angle in the Z direction, respectively. The adding unit 52 has at least three independent accelerometers for measuring accelerations in three directions, respectively; for example, there are 3 separate accelerometers for measuring X, Y and acceleration in the Z direction, respectively. The interface circuit forms an inertial measurement structure based on the angles and accelerations in the 3 directions and outputs the inertial measurement structure to the main control module 10.

Specifically, the inertial navigation module 50 outputs information such as acceleration and angle to the main control module 10 to complete the integrated navigation function. For example, the inertial navigation module 50 includes 3 independent fiber optic gyroscopes, 3 independent accelerometers, a power circuit, an interface circuit, and a structural body, among others.

The inertial navigation module 50 includes a housing, an end plate, a sensitive element frame, a vibration damper assembly, and the like, and mainly performs the following functions:

(1) ensuring the installation precision of installing the gyroscope and the accelerometer along the inertial set coordinate system and ensuring the installation stability;

(2) good thermal and mechanical environment is provided for instruments inside the inertial measurement unit;

(3) the installation requirements of an external mechanical interface and an electrical interface are met;

(4) installing and fixing a circuit assembly to meet the design requirement of electromagnetic compatibility;

(5) has sufficient rigidity and reliability.

The structural design needs to ensure that the whole body for installing the gyroscope and the accelerometer has enough rigidity, and the optimization design is carried out on the basis. The main material is an aluminum alloy material with high elastic modulus/density ratio, high yield strength/density ratio and good thermal conductivity, and is processed according to the processing technology requirements of precision parts, so that the long-term stability of the precision and the size of the parts can meet the design requirements.

Fig. 11 shows a schematic block diagram of a satellite navigation module, and as shown in fig. 11, the satellite navigation module 60 includes a radio frequency unit 61, a baseband processing unit 62, and an information processing unit 63. The rf unit 61 has at least two rf signal receiving channels for receiving at least two rf signals. The baseband processing unit 62 is connected to an output end of the rf unit 61, and is configured to perform baseband processing on the rf signal. The information processing unit 63 is connected to the baseband processing unit 62, and is configured to perform PVT calculation on the data processed by the baseband, and output a PVT calculation result to the main control module 10. The baseband processing unit 62 may include a plurality of GPS signal processing channels therein.

Specifically, the satellite navigation module 60 has two radio frequency signal receiving channels, that is, a binary diversity receiving mode is adopted, and double-antenna input is adopted to receive navigation satellite signals of GPS-L1 and BDS-B1 frequency points, complete signal capturing, tracking, original observed quantity solving, and satellite selection, then complete PVT solution, output information of position, speed, time and the like of a carrier, and send the information to the main control module 10 to complete a combined navigation function.

The radio frequency unit 61 includes a power synthesizer, a radio frequency amplifier, a power divider, a radio frequency filter, a radio frequency amplifier, a mixer, an intermediate frequency filter, an intermediate frequency amplifier, a gain controller, and a low pass filter, and converts the received radio frequency signal into an intermediate frequency signal by down-conversion once, and sends the intermediate frequency signal to the data processing unit.

The information processing unit 63 includes an analog-to-digital conversion circuit, a clock driving circuit, a signal processing circuit and an external interface circuit, and mainly implements despreading demodulation of satellite navigation signals, acquisition of navigation messages, measurement of measurement information such as pseudo-range and doppler, etc., resolving information such as position, speed and time of a carrier, and sending second pulse signals and various data frames to the system.

Receiving radio signals transmitted by a GPS satellite in a space segment through an antenna; the GPS radio frequency signal completes the demodulation of the signal and the real-time extraction of the observed quantity through the radio frequency unit 61 and the baseband processing unit 62, and the de-format of the navigation message is realized; then, the satellite information and the observation information are transmitted to the information processing unit 63 to complete the calculation of the position information, the speed information and the timekeeping information of the current observation time; and, for the diversity receiver, the receiver is required to select to receive two paths of GPS signals at the same time, and the signals are delivered to the application information processing unit 63, so as to implement the multi-constellation preferred positioning scheme.

The rocket-borne integrated electronic system solution provided by the embodiment can meet the flight control requirements of the electric system of the carrier rocket (or missile weapon), the circuit design is safe and reliable, the system integration is high, the system intelligentization degree is improved, and the designed circuit is subjected to environmental tests and system test checks.

Although the embodiments of the present invention have been described with reference to 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

1. An rocket-borne integrated electronic system, comprising:

2. The system of claim 1, wherein the master module comprises a system on a chip.

3. The system of claim 1, wherein the power module comprises:

the input end of the filtering unit is connected with an external power supply;

4. The system of claim 3, wherein the filtering unit comprises an electromagnetic compatibility filter, a first diode and a low-pass filter connected in series in sequence; wherein the first diode is used for suppressing transient voltage.

5. The system of claim 1, wherein the power distribution module comprises:

6. The system of claim 5, wherein the power unit comprises:

7. The system of claim 6, wherein the control unit further comprises: a sampling circuit; the sampling circuit is used for collecting feedback signals of all circuits in the power unit and transmitting the feedback signals back to the first controller; the feedback signal includes at least one of a voltage, a current, and a temperature.

8. The system of claim 1, wherein the timing module comprises a second controller, a driver, and a fourth switching device connected in series;

the fourth switching device is to output a timing based on the level signal.

9. The system of claim 8, wherein the timing module further comprises a timing extraction unit for feeding back the timing outputted by the fourth switching device to the second controller; and the second controller sends the received time sequence to the main control module so that an interpreter can determine whether the time sequence module normally sends out a time sequence signal.

10. The system of claim 1, wherein the inertial navigation module comprises:

the accelerometer unit is provided with at least three independent accelerometers which are respectively used for measuring the acceleration in three directions;

11. The system of claim 1, wherein the satellite navigation module comprises:

12. The system according to any one of claims 1-11, wherein the master control module is connected to the power distribution module and the timing module via a first bus, respectively; the main control module is respectively connected with the inertial navigation module and the satellite navigation module through a second bus; wherein a communication rate of the first bus is greater than a communication rate of the second bus.