CN112783023A - Control system based on meteorological detection rocket - Google Patents
Control system based on meteorological detection rocket Download PDFInfo
- Publication number
- CN112783023A CN112783023A CN202011573417.9A CN202011573417A CN112783023A CN 112783023 A CN112783023 A CN 112783023A CN 202011573417 A CN202011573417 A CN 202011573417A CN 112783023 A CN112783023 A CN 112783023A
- Authority
- CN
- China
- Prior art keywords
- module
- control system
- circuit
- rocket
- bus
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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
-
- 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
- G05B2219/25—Pc structure of the system
- G05B2219/25257—Microcontroller
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Arrangements For Transmission Of Measured Signals (AREA)
Abstract
The invention relates to a control system based on a meteorological detection rocket.A hardware frame takes a DSP (digital signal processor) processor module as a core, and a peripheral circuit comprises a power circuit module, a CAN (controller area network) bus communication module, an RS-422 serial port communication module, an AD (analog-digital) acquisition circuit module and a switching value input and output circuit module. The communication between the electrical core and other related systems CAN adopt various forms, RS422, CAN and the like, the control system is required to have the capabilities of communication bus interfaces, driving and the like, the other CAN bus is used as reserved backup, the RS-422 serial port communication module is a three-channel serial port module, the first channel is used for communicating with a GNSS receiver, the second channel is used for communicating with a remote measuring system, and the third channel is used as a backup channel, so that the control system has backup according to the needs, and has good universality and compatibility.
Description
Technical Field
The invention belongs to the field of aircraft control, and particularly relates to a control system based on a meteorological detection rocket.
Background
The meteorological detection rocket can be used for detecting atmospheric environment, gravitational wave, geomagnetic field, cosmic ray, microgravity environment and the like from a boundary layer, a troposphere to the whole near space, can also directly develop artificial rainfall, lightning triggering and disaster reduction, ionosphere influence and other services, provides important support for near space atmospheric environment research, space launching and missile flight trajectory binding and correction, aircraft material and aerodynamic design research, typhoon disaster research, atmospheric waveguide, cloud data service and the like, and has wide application prospect in the fields of meteorological detection and research, space launching and recovery, near space aircraft design and flight test and the like.
The meteorological detection rocket is provided with an overhead meteorological induction instrument, mainly faces to the requirement of detecting various vertical profile meteorological parameters at different positions at the same time, and the meteorological detection rocket control system resolves the current position and state in real time and releases the overhead meteorological induction instrument according to specific requirements. Whether the high altitude meteorological induction instrument can be released at an accurate time point and an altitude point according to the time sequence requirement, and simultaneously, all parameters in the flight process are sent to a ground command system in a telemetering data mode, so that the method is one of important signs for judging a meteorological detection task.
The meteorological detection rocket control system is used as an important component of a meteorological detection rocket and mainly completes the work of communication, power supply, flight data calculation, time sequence signal output, recovery and the like of each single machine in the rocket.
Disclosure of Invention
In view of the defects and the improvement requirements of the prior art, the invention aims to provide a control system of a meteorological sounding rocket, which is used for solving the problems of universality and low cost of the control system of the meteorological sounding rocket.
In order to realize the aim, the invention provides a control system based on a meteorological detection rocket, a hardware frame takes a DSP processor module as a core, a peripheral circuit comprises a power circuit module, a CAN bus communication module, an RS-422 serial port communication module, an AD acquisition circuit module and a switching value input and output circuit module,
the CAN bus communication module is connected with the DSP processor module, and bidirectional serial signals are converted into CAN-H, CAN-L bus level signals by using an isolator and a transceiver and are connected with a ground measurement and control system;
the RS422 bus communication module is connected with the DSP processor module, and bidirectional serial signals of the serial port transceiver chip are converted into bidirectional differential level signals to be communicated with other systems;
the AD acquisition module is connected with the DSP processor module and is used for detecting power supply voltages of all paths of the rocket (4 paths in total, namely, power supply voltage of the rocket is supplied by the power generation and control system, actual power consumption voltage of the rocket control system and rocket initiating explosive device activation bus voltage are measured and controlled);
the switching value input and output module is connected with the DSP processor module and mainly has the functions of switching value input and switching value output;
inputting a switching value: various pulse signals collected are converted into digital level (3.3V) of an IO (input/output) of a DSP (digital signal processor) chip through an optical coupler and are input to an IO pin of a DSP module;
and (3) switching value output: converting the level of a 3.3V pulse digital signal output from an IO pin of a DSP module into a level (28V and 10A) for initiating explosive device activation;
the processor module is used as a main processor of the detection rocket control system and provides hardware resources for the detection rocket control system, and the processor DSP, the peripheral clock circuit and the JTAG circuit form the processor module and are mainly used for flight control operation, time sequence processing and switching value input and output;
the power circuit module is mainly used for isolating and filtering power supplied by a ground measurement and control system or a rocket thermal battery, and supplying power to the chip after isolating a conversion level through the DC/DC converter, so that system noise is effectively inhibited, and interference of a ground circuit is eliminated;
the CAN bus communication module is accessed to a CAN communication bus through a CAN isolator and a CAN transceiver, and communicates with a ground test and launch control system through one CAN bus to realize launch flow control;
the RS-422 serial port communication module is used for data exchange between the control system and other single machines in the rocket by using an RS422 bus;
the AD acquisition module is used for converting the analog quantity into digital quantity which can be identified by the DSP module and performing digital-to-analog conversion;
the switching value input and output circuit module comprises an output circuit module: sending out a corresponding time sequence control command through an I/O port of the main processor, driving a relay of a corresponding time sequence control board to act after isolation and amplification, and switching on a time sequence control loop; still include the input circuit module: the output signal and other state quantities are collected through the optical coupler. The collected signals are converted into digital switching values through the optical coupling circuit and sent back to the DSP processor for state detection.
Further, the peripheral clock circuit adopts an external clock 30MHz clock crystal oscillator.
Furthermore, another CAN bus is also included as a reserved backup.
Furthermore, the RS-422 serial port communication module is a three-channel serial port module, the first channel is used for communicating with the GNSS receiver, the second channel is used for communicating with the telemetry system, and the third channel is used as a backup channel.
Specifically, the AD acquisition module comprises twelve paths of voltage acquisition, wherein an input signal passes through an attenuation network, an analog signal is gated through a switch circuit, and the analog signal is finally input to a GPIO pin of the DSP.
Specifically, the switching value input circuit: the acquisition of twenty-four paths of signals is realized, and the acquisition signals are changed into digital switching values through the optical coupling circuit and are sent back to the DSP processor for state detection.
The switching value output circuit: the output of nineteen control signals is realized, and output signals meeting the driving requirements can be provided through a level conversion chip and a Darlington array.
Compared with the prior art, the technical scheme of the invention can obtain the following beneficial effects:
1. the control system based on the meteorological detection rocket as an electrical core CAN adopt various forms, RS422, CAN and the like for communication with other related systems, the control system is required to have the capabilities of communication bus interfaces, driving and the like, the other path of CAN bus is used as reserved backup, the RS-422 serial port communication module is a three-channel serial port module, the first path is used for communicating with a GNSS receiver, the second path is used for communicating with a telemetering system, and the third path is used as a backup channel, so backup is carried out as required;
2. specifically, to save I/O resources of the DSP, each control signal is to control the actions of four optocouplers (PVG612A) on the timing distribution board. Nineteen DSP control signals (figure 7-1) of the switching value output control signals; the output signal is converted into a level signal of 5V from a level signal of 3.3V through an electromagnetic isolation chip IL260-3, and meanwhile, the input signal and the output signal are isolated electromagnetically. The 5V level signal is amplified by the Darlington array ULQ2003AD, and can directly drive the sequential circuit to work after passing through the optical coupler (PVG 612A);
each optocoupler needs about 10mA of driving current, at most twenty-four optocouplers in the sequential circuit work will act simultaneously, the driving capability of the electromagnetic isolation chip IL260-3 is not enough to drive a plurality of optocouplers to work simultaneously, and therefore, a Darlington array ULQ2003AD is added between the electromagnetic isolation chip IL260-3 and the optocoupler (PVG612A) to improve the driving capability of signals. The Darlington array ULQ2003AD can provide 500mA driving current and can meet the driving requirement of a control signal;
saves resources and reduces system cost.
Drawings
FIG. 1 is a block diagram of a control system according to an embodiment of the present invention;
FIG. 2 is a functional block diagram of a control system according to an embodiment of the present invention;
FIG. 3 is a power circuit diagram of an embodiment of the present invention;
FIG. 3-1 is a power supply circuit of a power chip according to an embodiment of the invention;
FIG. 3-2 shows a DSP chip power supply circuit according to an embodiment of the invention;
FIG. 4 is a CAN bus circuit diagram of an embodiment of the present invention;
FIG. 5 is a circuit diagram of an RS-422 bus according to an embodiment of the invention;
FIG. 6 is a diagram of an AD acquisition circuit according to an embodiment of the present invention;
FIG. 6-1 is a schematic diagram of an AD conversion circuit according to an embodiment of the present invention;
FIG. 6-2 is a diagram of a gated isolation circuit according to an embodiment of the present invention;
FIGS. 6-3 are circuit diagrams of attenuation networks according to embodiments of the present invention;
FIG. 7 is a circuit diagram of an input/output module according to an embodiment of the present invention;
FIG. 7-1 is a circuit diagram of a switching value output circuit according to an embodiment of the present invention;
FIG. 7-2 is a circuit diagram of a switching value input circuit according to an embodiment of the present invention;
fig. 8 is a schematic diagram of signal flow directions according to an embodiment of the present invention.
Detailed Description
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 only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
The whole meteorological detection rocket system mainly comprises a control system, a remote measuring system, an open-cabin release system, an overhead meteorological induction instrument for releasing, an ignition system and a ground measurement and control system. The opening release system and the ignition system work by controlling the switching value output signal of the system, namely the control system sends out one, a plurality of or continuous pulses with specific time sequence, and the pulse signals are isolated and amplified by the optical coupler to directly drive the engine to ignite or the opening mechanism to start.
The switching value input signal refers to one, a plurality of or a plurality of continuous pulse signals sent by a ground test empty system or other systems, the control system needs to collect the signals, and the collected information can be used for triggering other control logics and the like.
Referring to fig. 1, the invention provides a control system based on a meteorological detection rocket, a hardware frame takes a DSP processor module as a core, a peripheral circuit comprises a power circuit module, a CAN bus communication module, an RS-422 serial port communication module, an AD acquisition circuit module and a switching value input and output circuit module,
the CAN bus communication module is connected with the DSP processor module, and bidirectional serial signals are converted into CAN-H, CAN-L bus level signals by using an isolator and a transceiver and are connected with a ground measurement and control system;
the RS422 bus communication module is connected with the DSP processor module, and bidirectional serial signals of the serial port transceiver chip are converted into bidirectional differential level signals to be communicated with other systems;
the AD acquisition module is connected with the DSP processor module and is used for detecting power supply voltages of all paths of the rocket (4 paths in total, namely, power supply voltage of the rocket is supplied by the power generation and control system, actual power consumption voltage of the rocket control system and rocket initiating explosive device activation bus voltage are measured and controlled);
the switching value input and output module is connected with the DSP processor module and mainly has the functions of switching value input and switching value output;
inputting a switching value: various pulse signals collected are converted into digital level (3.3V) of an IO (input/output) of a DSP (digital signal processor) chip through an optical coupler and are input to an IO pin of a DSP module;
and (3) switching value output: converting the level of a 3.3V pulse digital signal output from an IO pin of a DSP module into a level (28V and 10A) for initiating explosive device activation;
the DSP processor module is used as a main processor of the detection rocket control system and provides hardware resources for the detection rocket control system, and the DSP processor, a peripheral clock circuit and a JTAG circuit jointly form the processor module and are mainly used for flight control operation, time sequence processing and switching value input and output;
the power circuit module comprises an isolation DC/DC power supply and secondary power supply conversion, realizes the further conversion of power supply to the ground measurement and power control system or power supply to a thermal battery on a rocket, meets the requirements of filtering and power supply, mainly isolates and filters the power supply to the ground measurement and power control system or the power supply to the thermal battery on the rocket, supplies power to a chip after isolating a conversion level through a DC/DC converter, effectively inhibits system noise and eliminates the interference of a ground circuit; specifically, a TMS320F28335 chip in the processor module needs 3.3V and 1.9V power supply, an IL712 isolation chip in the CAN module needs 3.3V power supply, and a TJA1050 transceiver needs 5V power supply;
in the RS422 module: IL422 transceiver requires 3.3V and 5V power supplies
The CAN bus communication module is a two-channel CAN module (supporting data rate up to 1 Mbps) which is accessed to the CAN communication bus through a CAN isolator and a CAN transceiver. Wherein, the 1 path of CAN bus is used for communicating with the ground test launch and control system, and the other path of CAN bus is used as a reserved backup; the CAN isolator is used for electromagnetically isolating the transmitting and receiving signals; the CAN transceiver is used for converting the output signal into a CAN network differential signal; the CAN communication bus is accessed through the CAN isolator and the CAN transceiver, and the communication is carried out with the ground test and launch control system through one CAN bus and the launch flow control is realized; the ground test launch control system does not belong to a meteorological detection rocket control system, is an external single machine which is communicated with the control system through a CAN bus, and is mainly used for meteorological detection rocket test and launch flow control;
the RS-422 serial port communication module is a three-channel serial port module, wherein the first channel is used for communicating with the GNSS receiver, the second channel is used for communicating with the telemetering system, and the third channel is used as a backup channel and is used for data exchange between the control system and other single machines in the rocket by using an RS422 bus;
the GNSS receiver does not belong to a meteorological detection rocket control system, is an external single machine which is communicated with the control system through an RS-422 serial port and is mainly used for collecting positioning information such as speed, position and the like;
the remote measuring system does not belong to a meteorological detection rocket control system, is an external single machine which is communicated with the control system through an RS-422 serial port and is mainly used for carrying out power amplification and wireless transmission on various flight parameters of the control system;
the AD acquisition module is used for converting the analog quantity into digital quantity which can be identified by the DSP module and performing digital-to-analog conversion;
the switching value input and output circuit module comprises an output circuit module: sending out a corresponding time sequence control command through an I/O port of the main processor, driving a relay of a corresponding time sequence control board to act after isolation and amplification, and switching on a time sequence control loop; still include the input circuit module: the output signal and other state quantities are collected through the optical coupler. The collected signals are converted into digital switching values through the optical coupling circuit and sent back to the DSP processor for state detection.
The peripheral clock circuit adopts an external clock 30MHz clock crystal oscillator.
The AD acquisition module comprises twelve paths of voltage acquisition, and inputs an input signal through an attenuation network, gates an analog signal through a switch circuit and finally inputs the analog signal to a GPIO pin of the DSP.
Specifically, the switching value input circuit: the acquisition of twenty-four paths of signals is realized, and the acquisition signals are changed into digital switching values through the optical coupling circuit and are sent back to the DSP processor for state detection.
The switching value output circuit: the output of nineteen control signals is realized, and output signals meeting the driving requirements can be provided through a level conversion chip and a Darlington array.
In this embodiment, specifically:
1. the processor module is formed by the DSP, the peripheral clock circuit and the JTAG circuit and is mainly used for flight control operation, time sequence processing and switching value input and output.
The main processor of the detection rocket control system provides hardware resources for the detection rocket control system. In some examples, the DSP selects a TI corporation chip model TMS320F28335 with the following features:
a) a high performance 32-bit CPU;
b) the dominant frequency can reach 150 MHz;
c)256K × 16 Flash memory, 34K × 16 SARAM;
d)3 CPU timers;
e) the PIE module may support 96 different interrupts;
f) the periphery of the serial interface is provided with 2 channel CAN modules (supporting data rate up to 1 Mbps), 3 SCI modules, 2 multichannel buffer serial interface McBSP modules, 1 SPI module and 1I 2C bus;
g) 12-bit A/D converter with 16 conversion channels: a fast switching time of 80 ns;
h) there are 88 independently programmable multiplexed General Purpose Input Output (GPIO) pins.
2. The rocket power supply system is a ground measurement and launch control system (before launch) or a rocket thermal battery (after launch), both power supplies are 28V direct current power supplies, actually, the power supplies of chips of the modules are mainly +/-5V, +3.3V, +1.9V and the like, and the power supply module mainly isolates and converts the 28V input from the outside into power supply voltage required by the chips;
the power circuit module mainly isolates and filters power supplied by a ground measurement and control system or a rocket thermal battery, and supplies power to the chip after isolating the conversion level through the DC/DC converter, so that system noise is effectively inhibited, and interference of a ground circuit is eliminated. In some examples, RECOM power module RP15-2405SAW module is employed.
Power circuit working process
The 28V power supply link passes through an isolation power supply module (fig. 22-1), the isolation power supply module supplies power to the chip after isolating the conversion level by using a DC/DC converter, so as to effectively suppress system noise and eliminate ground loop interference, in some examples, 3 DC/DC converters DCR010505U (fig. 3-1) are used to convert VCC5V into 3 paths of +5V voltage, and the 3 paths of +5V voltage are respectively supplied to 1 path of CAN transceiver, 3 paths of RS422 communication circuit and a switching value output circuit; VCC5V was converted to two +5V/-5V voltages by a 2-chip DC/DC converter DCP01050DBPU (FIG. 3-1) to be supplied to an isolation amplifier and a multiplexer, respectively.
The TPS70302PWP (figure 3-2) is utilized to convert +5V into 1.9V and 3.3V voltage to be supplied to chips such as a DSP, an optical coupler and level conversion, 1.9V output can provide 1A current, 3.3V output can provide 2A current, and the use requirement of a control system is met. Power supply: and the switching value outputs of 28V, 5V, 3.3V, 1.9V and the like used by each module are as follows: it has just been mentioned that the processor module can only output the LVTTL level of 3.3V, which cannot drive the engine ignition or the start of the opening release mechanism, so the switching value input and output module is required to convert the LVTTL level into the 28V level that can be used to drive the engine ignition and the start of the opening release mechanism in an isolated manner.
CAN bus communication module, CAN bus communication module: according to the embodiment of the patent, the rocket and the ground test launch control system exchange data through a CAN bus to complete the functions of testing, state preparation and the like before launch, specifically, a processor module is communicated with the ground test launch control system, but a CAN interface of a DSP (digital signal processor) of the processor module cannot be directly used for bus communication, and CAN-TX and CAN-RX ends need to be converted into explicit and implicit differential levels, namely CAN-H, CAN-L, by using a CAN bus transceiver;
the CAN bus is accessed to the CAN communication bus through the CAN isolator and the CAN transceiver. In some examples, the meteorological sounding rocket control system communicates with the ground test launch control system through the CAN bus and implements launch flow control.
CAN bus communication circuit work flow
In the embodiment, a CAN bus is adopted for communication between the control system and the ground test launch control system, receiving the control instruction and uploading the system state information. The CAN signal is subjected to electromagnetic isolation of transmitting and receiving signals through an IL712-3 (figure 4) isolator, then converted into a differential signal of a CAN network through a high-speed CAN transceiver TJA1050T, the highest transmission rate CAN reach 1Mbps, and the resistance value of a CAN interface matching resistor is set to be 120 omega +/-1 omega.
An RS-422 serial port module, according to the embodiment of the patent, a rocket control system and other single machines in the rocket use RS422 buses for data exchange, the RS422 buses are differential full-duplex data buses, but an external Serial Communication Interface (SCI) of a processor module DSP is a bidirectional non-differential signal (SCI-T, SCI-R), and the RS422 bus communication module is required to be used for converting the data into differential levels, namely R +, R-, T + and T-;
and the RS-422 serial port communication module is a 3-channel serial port module. In some examples, the first path is used for communicating with a GNSS receiver, the second path is used for communicating with a telemetry system, and the third path is used as a backup channel;
RS-422 bus communication circuit work flow
In this example, the RS-422 communication includes 3 paths, the 1 st path is used for communicating with the GNSS receiver, the 2 nd path is used for sending the on-missile measurement information to the telemetry system, and the 3 rd path is reserved for use. As shown in fig. 5, the RS422 communication circuit converts the interface chip IL422 into a differential level;
the two mentioned examples are RS422 and CAN modules, for example, a local measurement and control system CAN only support CAN bus communication externally, that is, CAN bus messages sent by the local measurement and control system need to be converted into information that CAN be identified by a processor module through a CAN communication module, so that the rocket CAN normally communicate with the local measurement and control system. RS422 is similar.
The system comprises an AD acquisition circuit module, a processor module DSP and a ground measurement and control system, wherein the AD acquisition circuit module mainly converts analog quantity into digital quantity which can be identified by the processor module DSP, 4 paths of power supply signals including power supply + BK of the ground measurement and control system, power supply + DD of a rocket thermal battery, power supply + BF of an initiating explosive device bus in a rocket and actual power consumption +28V of the control system are analog quantity according to the embodiment of the patent, the 4 paths of voltage analog quantity are input to an 'ADIN' pin of the DSP through an attenuation network, gating and isolation through the AD acquisition module, and the DSP determines the correctness of each power supply system through interpreting 4 paths of voltage values and is used for controlling a rocket launching process;
the DSP is provided with a 16-channel 12-bit AD conversion channel, the measurement resolution ratio of the DSP passing through the attenuation network can reach 0.012V/bit, and the actual measurement precision can reach 0.2V. In some examples, the AD acquisition circuit is used to measure the amount of power bus voltage (+ BK, + DD, + BF, 28V +) on an rocket-borne computer. The input analog signal needs to pass through an attenuation network (the attenuation multiple is 16 times) to control the voltage range to be 0V-2V, and the selected analog signal enters an AD port of the DSP for digital-to-analog conversion after being electromagnetically isolated by an isolation amplifying circuit.
AD acquisition circuit working process
In this example, the AD acquisition circuit (FIG. 6-1) is used to measure the amount of supply bus voltage (+ BK, + DD, + BF, 28V +) on the control system. The input analog signal needs to pass through an attenuation network (figure 6-3) (the attenuation multiple is 16 times) to control the voltage range to be 0V-2V, an analog switch circuit is adopted to gate the analog signal (figure 6-2), and the gating signal is output by 4 GPIO pins of the DSP and is provided by a digital isolation circuit (IL 260-3). The selected analog signal is electromagnetically isolated by an isolation amplifying circuit and enters an AD acquisition port of the DSP for digital-to-analog conversion, and the voltage input range of the port is (0V-3.0V). In design, the maximum value of the input voltage is generally set to about 80% of 3V (2.4V), and the actual maximum value is 2V, so that the design requirement is met. The DSP is provided with a 16-channel 12-bit AD conversion channel, the measurement resolution ratio of the DSP passing through the attenuation network can reach 0.012V/bit, and the actual measurement precision can reach 0.2V.
6. Switching value input/output circuit module: a. a switching value output module: according to the patent example, the DSP sends out a pulse signal through an IO pin (not less than 20 paths), the pulse width of the pulse signal is 100ms, the level is 3.3V, the pulse signal is used for activating the initiating explosive device, such as engine ignition, opening a bin to release the initiating explosive device activation and the like, but the actual initiating explosive device activation threshold voltage is 28V, and the driving current is 5-10A. Therefore, the pulse signal output by the DSP cannot activate each initiating explosive device of the rocket, and the level needs to be converted into 5V through the switching value output module, and then the DSP output pulse is converted into the level (28V, 10A) which can be used for driving ignition through the driving circuit and the initiating explosive device activation bus (+ BF).
b. The switching value input module: according to the embodiment of the patent, the switching value input is mainly used for two parts, wherein after the switching value output pulse signal is sent out, in order to determine whether the level conversion of the switching value output module and the driving circuit work normally, the switching value input module is required to be used for extracting ignition levels (28V and 10A) for the DSP to confirm that the signal is sent out normally; and secondly, other pulse signals in the transmitting and flying processes need to be collected through a switching value input circuit and input into an IO pin of the DSP for time sequence planning in the transmitting and flying processes.
An output circuit module: and a corresponding time sequence control instruction is sent out through an I/O port of the main processor, and after isolation and amplification, the corresponding time sequence control board relay is driven to act, so that the time sequence control loop is switched on.
An input circuit module: the output signal and other state quantities are collected through the optical coupler. The collected signals are converted into digital switching values through the optical coupling circuit and sent back to the DSP processor for state detection.
Switching value input/output circuit working process
Switching value input circuit:
in this example, the switch signal measurements include 24 switching value input signals of T0, CSZT1/2, GZZT1/2, FDJDH +, etc. (FIG. 7-2). And voltage signals at the action contact of the optical coupler TLP281 and the two ends of the initiating explosive device are recovered, and the recovered signals are converted into digital switching values through an optical coupling circuit and are sent back to the DSP processor for state detection.
Taking the signal acquisition of T0 as an example, the T0 signal is active at 28V low, when T0 is at 28V high, pins 1 and 2 of the input terminal of the optocoupler are not conductive, the corresponding pins OUT1 and DGND are not conductive, and the signal terminal DIN1 is maintained at 3.3V (digital high).
When the T0 signal changes from 28V high to 28V low, the optocoupler inputs 1 and 2 are turned on, the corresponding output OUT1 and DGND pin are turned on, and the DIN1 signal changes from 3.3V (digital high) to digital ground (digital low). When the pin of the DSP acquisition DIN1 changes from a digital high level to a digital low level, the T0 signal is acquired to be effective.
Inputting a switching value: there are many links in the rocket launching process, including separation signal after starting, output recovery signal, etc., these signals need the processor module to calculate, but these signals can't be directly input to the processor module, need the switching value input/output module to isolate and convert into the LVTTL signal of 3.3V.
As shown in fig. 8, the signal direction, i.e. signal flow, of the present embodiment is as follows: the power module converts the externally input 28V electricity into 3.3V and 1.9V electricity and transmits the electricity to the DSP chip for chip power supply; the 28V electricity input from the outside is converted into +5V and-5V electricity and is transmitted to the CAN bus communication module and the RS422 bus communication module for chip power supply; and converting the externally input 28V electricity into an initiating explosive device activation bus (+ BF) to be electrically transmitted to the switching value input and output circuit.
Communication signals: the DSP inputs 3.3V bidirectional non-differential signals (SCI-T, SCI-R) to the RS422 bus communication module, and the RS422 bus communication module converts the signals into 5V differential full-duplex bus signals to communicate with other single machines. The DSP inputs 3.3V bidirectional CAN communication signals (CAN-TX and CAN-RX) to the CAN bus communication module, and the CAN bus communication module is converted into a 5V display and recessive differential level CAN-H, CAN-L for communicating with a ground test launch control system bus.
Switching value input and output: switching value output, namely converting a 3.3V pulse level output by DSP IO into a level with stronger 28V driving performance through level conversion and driving, and activating each initiating explosive device of the rocket; the switching value input is to input the externally input 28V level and the self output 28V switching output value to a DSP IO pin through optical coupling isolation for time sequence interpretation.
Claims (6)
1. A control system based on a meteorological detection rocket is characterized in that a hardware frame takes a DSP processor module as a core, a peripheral circuit comprises a power circuit module, a CAN bus communication module, an RS-422 serial port communication module, an AD acquisition circuit module and a switching value input and output circuit module,
the CAN bus communication module is connected with the DSP processor module, and bidirectional serial signals are converted into CAN-H, CAN-L bus level signals by using an isolator and a transceiver and are connected with a ground measurement and control system;
the RS422 bus communication module is connected with the DSP processor module, and bidirectional serial signals of the serial port transceiver chip are converted into bidirectional differential level signals to be communicated with other systems;
the AD acquisition module is connected with the DSP processor module and is used for detecting each path of power supply voltage of the rocket;
the switching value input and output module is connected with the DSP processor module and mainly has the functions of switching value input and switching value output;
the processor module is used as a main processor of the detection rocket control system and provides hardware resources for the detection rocket control system, and the processor DSP, the peripheral clock circuit and the JTAG circuit form the processor module and are mainly used for flight control operation, time sequence processing and switching value input and output;
the power circuit module is mainly used for isolating and filtering power supplied by a ground measurement and control system or a rocket thermal battery, and supplying power to the chip after isolating a conversion level through the DC/DC converter, so that system noise is effectively inhibited, and interference of a ground circuit is eliminated;
the CAN bus communication module is accessed to a CAN communication bus through a CAN isolator and a CAN transceiver, and communicates with a ground test and launch control system through one CAN bus to realize launch flow control;
the RS-422 serial port communication module is used for data exchange between the control system and other single machines in the rocket by using an RS422 bus;
the AD acquisition module is used for converting the analog quantity into digital quantity which can be identified by the DSP module and performing digital-to-analog conversion;
the switching value input and output circuit module comprises an output circuit module: sending out a corresponding time sequence control command through an I/O port of the main processor, driving a relay of a corresponding time sequence control board to act after isolation and amplification, and switching on a time sequence control loop; still include the input circuit module: the output signal and other state quantities are collected through the optical coupler. The collected signals are converted into digital switching values through the optical coupling circuit and sent back to the DSP processor for state detection.
2. A weather-sounding rocket-based control system according to claim 1, wherein said peripheral clock circuit employs an external clock 30MHz clock crystal.
3. A weather-sounding rocket-based control system according to claim 2 and further comprising another CAN bus as a reserved backup.
4. The weather-sounding rocket-based control system according to claim 3, wherein the RS-422 serial port communication module is a three-channel serial port module, the first channel is used for communicating with the GNSS receiver, the second channel is used for communicating with the telemetry system, and the third channel is used as a backup channel.
5. The weather-detection rocket-based control system according to claim 4, wherein the AD acquisition module comprises twelve voltage acquisition channels, the input signal is passed through the attenuation network, and the analog signal is gated by the switch circuit and finally input to the GPIO pin of the DSP.
6. The weather-detection-rocket based control system according to claim 5, wherein said switching value input circuit: the acquisition of twenty-four paths of signals is realized, and the acquisition signals are changed into digital switching values through the optical coupling circuit and are sent back to the DSP processor for state detection.
The switching value output circuit: the output of nineteen control signals is realized, and output signals meeting the driving requirements can be provided through a level conversion chip and a Darlington array.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011573417.9A CN112783023A (en) | 2020-12-24 | 2020-12-24 | Control system based on meteorological detection rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011573417.9A CN112783023A (en) | 2020-12-24 | 2020-12-24 | Control system based on meteorological detection rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112783023A true CN112783023A (en) | 2021-05-11 |
Family
ID=75752780
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011573417.9A Pending CN112783023A (en) | 2020-12-24 | 2020-12-24 | Control system based on meteorological detection rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112783023A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116110268A (en) * | 2023-04-17 | 2023-05-12 | 北京星途探索科技有限公司 | Signal simulation equipment for teaching of carrier rocket measurement system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105467898A (en) * | 2015-12-28 | 2016-04-06 | 北京航天新风机械设备有限责任公司 | Embedded processing circuit of electric control combination of carrying section |
| CN106325292A (en) * | 2016-10-17 | 2017-01-11 | 湖北航天技术研究院总体设计所 | Universal controller of spaceflight carrier rocket |
| CN110488862A (en) * | 2019-08-02 | 2019-11-22 | 南京理工大学 | A kind of sub- grade integration flight control system of rocket one |
| CN110631431A (en) * | 2019-07-08 | 2019-12-31 | 北京星际荣耀空间科技有限公司 | Rocket-borne integrated electronic system |
| CN211041964U (en) * | 2019-07-08 | 2020-07-17 | 北京星际荣耀空间科技有限公司 | Rocket-borne integrated electronic system |
| CN111854543A (en) * | 2020-07-07 | 2020-10-30 | 深圳零壹空间电子有限公司 | Rocket control device |
-
2020
- 2020-12-24 CN CN202011573417.9A patent/CN112783023A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105467898A (en) * | 2015-12-28 | 2016-04-06 | 北京航天新风机械设备有限责任公司 | Embedded processing circuit of electric control combination of carrying section |
| CN106325292A (en) * | 2016-10-17 | 2017-01-11 | 湖北航天技术研究院总体设计所 | Universal controller of spaceflight carrier rocket |
| CN110631431A (en) * | 2019-07-08 | 2019-12-31 | 北京星际荣耀空间科技有限公司 | Rocket-borne integrated electronic system |
| CN211041964U (en) * | 2019-07-08 | 2020-07-17 | 北京星际荣耀空间科技有限公司 | Rocket-borne integrated electronic system |
| CN110488862A (en) * | 2019-08-02 | 2019-11-22 | 南京理工大学 | A kind of sub- grade integration flight control system of rocket one |
| CN111854543A (en) * | 2020-07-07 | 2020-10-30 | 深圳零壹空间电子有限公司 | Rocket control device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116110268A (en) * | 2023-04-17 | 2023-05-12 | 北京星途探索科技有限公司 | Signal simulation equipment for teaching of carrier rocket measurement system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN1331035C (en) | Sampling method and system for multi-channel analog signal | |
| CN110040263B (en) | Micro satellite information system based on CAN bus | |
| US20040199343A1 (en) | Integrated, self-powered battery monitoring device and system | |
| CN106354124B (en) | Self-diagnosable system and method based on FPGA analog input device channel | |
| CN101539483B (en) | Electric propulsion testing platform measurement control device | |
| CN109067447B (en) | Beidou RDSS multi-antenna switching communication method | |
| CN101442211A (en) | Monitoring device and monitoring methods for distributed battery management system | |
| CN208188215U (en) | Aircraft ground Auto-Test System based on Real Time Serial Communication | |
| CN103925853A (en) | Carrier rocket ground test system device | |
| CN102096657B (en) | System-on-chip (SOC)-based micro information processing module | |
| CN112783023A (en) | Control system based on meteorological detection rocket | |
| CN110132354B (en) | System and method for multiplexing measurement ports of multiple types of sensors | |
| CN104950773B (en) | Mixed type intelligent data acquisition processing unit | |
| CN203872178U (en) | Photoelectric switching circuit used for transmitting 1553B bus signal | |
| CN203014825U (en) | PCM interface test device | |
| CN210514976U (en) | Multi-channel synchronous real-time high-speed data acquisition system based on FPGA | |
| CN208460081U (en) | A kind of flying quality collector | |
| CN218601846U (en) | Airborne optical fiber video shunting equipment | |
| CN108827377A (en) | Untetheredization measuring system for aircraft | |
| AU2019216880A1 (en) | Multichannel software defined radio receiver with optically isolated ADC | |
| CN213023537U (en) | Installation type standard meter with pulse input and output switching function | |
| CN201041582Y (en) | Battery detection device | |
| CN112859687A (en) | Integrated satellite integrated electronic system | |
| CN211505696U (en) | Automatic aviation complex cable resistance value measuring equipment | |
| CN202126902U (en) | Resistance device with adjustable digital quantity |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210511 |