CN109592082B - Device for detecting rocket power filling system signal - Google Patents
Device for detecting rocket power filling system signal Download PDFInfo
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- CN109592082B CN109592082B CN201811432475.2A CN201811432475A CN109592082B CN 109592082 B CN109592082 B CN 109592082B CN 201811432475 A CN201811432475 A CN 201811432475A CN 109592082 B CN109592082 B CN 109592082B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G5/00—Ground equipment for vehicles, e.g. starting towers, fuelling arrangements
Abstract
The invention provides a device for detecting rocket power filling system signals, and aims to solve the problems that the heads of warehouse tables for filling in a target range are various, the data at the front end and the rear end of a filling system cannot be linked in real time, and the universality among various types is not strong. The invention can meet the signal acquisition function of the power filling system in different test sites among different models, carries out front-end detection on the whole filling process of the rocket power system, and transmits data to the rear end for real-time interpretation through an RS485 bus technology. When a fault occurs in the filling process, the fault is timely found, and the system command can master the filling dynamic state in real time and master the power system shooting range test and propellant filling display information.
Description
Technical Field
The invention relates to a device for detecting signals of a rocket power filling system.
Background
The existing carrier rocket power filling system can only carry out front-end display on signals such as air source pressure of an air distribution table, propellant storage tank pressure, gas cylinder pressure and the like of a filling storehouse through a gauge head, a rear-end interpretation hall cannot master data of the front-end power filling system in real time, and the front end and the rear end are difficult to link. In addition, most of the existing signal acquisition equipment belongs to special equipment, and is only designed for a certain specific test unit and a specific model rocket, so that the universal performance is poor, a plurality of gauge heads in a front-end storehouse are difficult to manage in a centralized manner, and the cost is high.
Disclosure of Invention
The invention aims to provide a device for detecting signals of a rocket power filling system.
In order to solve the above problems, the present invention provides an apparatus for detecting a rocket power filling system signal, comprising:
one side of the pressure measurement and transmission conversion unit receives air source pressure signals given by a first-stage air distribution table, a second-stage air distribution table and a third-stage air distribution table of a filling storehouse;
a PI optical coupling isolation conversion unit;
a tank filling signal conversion unit;
the device comprises a digital display controller and a main control computer connected with the digital display controller, wherein the digital display controller and the main control computer are respectively connected with a pressure measurement transmission conversion unit, a PI optical coupling isolation conversion unit and a storage tank filling signal conversion unit.
Further, in the device for detecting signals of a rocket power filling system, the pressure measurement and transmission conversion unit is used for converting air source pressure signals given by the first-stage air distribution table and the second-stage air distribution table of the filling storehouse and pressure signals given by the third-stage air distribution table into electric signals through transmission, transmitting the electric signals to the digital display controller in the power filling system acquisition equipment, converting the electric signals into pressure values by the digital display controller, and displaying the pressure signal values on the front-end display screen; and meanwhile, the digital display controller transmits the displayed pressure signal value to the main control computer through an RS485 bus technology.
Further, in the device for detecting signals of the rocket power filling system, the PI optical coupling isolation conversion unit is used for collecting passive contact signals given by the ground filling and liquid level signal boxes and 28 switching value signals given by the R box and the Y box in total, and broadcasting the collected signals of ground filling, overflow and seven-tube falling to the main control computer for interpretation and display.
Further, in the above apparatus for detecting signals of a rocket power filling system, the storage tank filling signal conversion unit is configured to collect 4 liquid level signals of each storage tank in a filling process of the oxidizing agent tanks Y1, Y2, Y3 and the fuel tanks R1, R2, R3 in a filling storehouse, and when it is monitored that the liquid level reaches a specified position according to the 4 liquid level signals, convert the 4 liquid level signals into electrical signals and send the electrical signals to the main control computer for interpretation through an RS485 bus technology.
Further, in the device for detecting signals of the rocket power filling system, the main control computer comprises a front-end industrial control computer and a rear-end interpretation computer, wherein the front-end industrial control computer is used for receiving RS485 bus data through the CONTEC data acquisition board card and displaying the data in real time; and the back-end interpretation computer is used for carrying out data interpretation and fault diagnosis.
Further, in the device for detecting signals of the rocket power filling system, the digital display controller selects a communication expansion card RS485 for communication, the isolation between the digital display controller and a common end of instrument signal input is more than 500Vrms, 8-bit data is expanded, the baud rate of the data meets 300-38400, and 32 instruments are connected to one bus in parallel and used for transmitting data to the front-end industrial personal computer and the rear-end interpretation computer through an ASCII communication protocol.
Compared with the prior art, the invention has the following beneficial effects:
1. multiple instruments for detection are packaged in a front-end filling warehouse, so that ground test equipment of the carrier rocket is simplified;
2. by the RS485 bus technology, the whole-process monitoring of each key pressure value and liquid level signal in the power filling process by front end command and rear end command is realized;
3. the signal acquisition equipment meets the redundancy of functions of various models, realizes the maximum design, and can be used in a mutually compatible way when various models are produced by the same set of technical indexes. The front panel of the acquisition equipment is provided with the state change-over switch, so that the generalization of the power signal acquisition function of the ground test emission control equipment is realized, the design flow and the time period are reduced, and the time cost is saved.
Drawings
FIG. 1 is a block diagram of a RS485 based signal acquisition device for a universal rocket power filling system according to one embodiment of the present invention;
fig. 2 is a schematic block diagram of a signal acquisition device of a general rocket power filling system based on RS485 according to an embodiment of the present invention.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
As shown in fig. 1 and 2, the present invention provides an apparatus for detecting a rocket power filling system signal, comprising:
a pressure measurement and transmission conversion unit 104, wherein one side of the pressure measurement and transmission conversion unit receives air source pressure signals given by a first-stage air distribution table, a second-stage air distribution table and a third-stage air distribution table of a filling storehouse;
a PI optical coupling isolation conversion unit 105;
a tank filling signal conversion unit 106;
the device comprises a digital display controller 107 and a main control computer 108 connected with the digital display controller 107, wherein the digital display controller 107 and the main control computer 108 are respectively connected with a pressure measurement transmission conversion unit 104, a PI optical coupling isolation conversion unit 105 and a storage tank filling signal conversion unit 106.
In one embodiment of the device for detecting rocket power filling system signals, the pressure measurement and transmission conversion unit is used for converting air source pressure signals given by the first-stage air distribution table and the second-stage air distribution table of the filling storehouse and pressure signals given by the third-stage air distribution table into electric signals through transmission, transmitting the electric signals to the digital display controller in the power filling system acquisition equipment, converting the electric signals into pressure values by the digital display controller, and displaying the pressure signal values on the front-end display screen; and meanwhile, the digital display controller transmits the displayed pressure signal value to the main control computer through an RS485 bus technology.
Here, the acquisition equipment front panel adjustment state change over switch, because of the difference of each unit and concrete model, tertiary pressure parameter exists in some models, switches state switch to corresponding position. According to the signal on the connecting arrow, the specific adjustment is made according to whether the three-stage rocket exists on the rocket on the connecting arrow, and when a test unit or model is changed, the general function of the device can be realized only by changing the state switch.
The function of the pressure measurement transmission conversion unit comprises the following steps: the method comprises the steps of receiving air source pressure values of a first-stage air distribution table and a second-stage air distribution table, receiving pressure values of a first-stage oxidant storage tank, receiving pressure values of a first-stage fuel storage tank, receiving pressure values of a second-stage oxidant storage tank and receiving pressure values of a second-stage fuel storage tank.
When the front panel switch is switched to the three-stage gas distribution table to be measured, the pressure measurement transmission conversion can also receive the helium gas source pressure value of the three-stage gas distribution table, receive the pressure value of the three-stage oxidant storage tank and receive the pressure value of the three-stage fuel storage tank.
In an embodiment of the device for detecting signals of a rocket power filling system, the PI optical coupling isolation conversion unit is used for obtaining passive contact signals given by a ground filling and liquid level signal box and total 28-path switching value signals given by an R box and a Y box, and broadcasting the collected signals of ground filling, overflow and seven-tube falling to the main control computer for interpretation and display.
In an embodiment of the apparatus for detecting rocket power filling system signals, the storage tank filling signal conversion unit is configured to collect liquid level signals of four liquid level detection points Y, and Y of each oxidizer tank Y, and Y during filling, respectively collect liquid level signals of four liquid level detection points R, and R of each fuel tank R, and R during filling, respectively collect liquid level signals of four liquid level detection points Y, and Y and liquid level signals of four liquid level detection points R, and R, all of which are passive contact signals, and when liquid levels reach a designated position according to the monitored liquid levels of the four liquid level detection points Y, and Y of each oxidizer tank and the monitored liquid levels of the four liquid level detection points R, and R of each fuel tank, Y, and Y, Liquid level signals of the four liquid level detection points r2, r3 and r4 are respectively converted into electric signals and are sent to the main control computer for interpretation through RS485 bus technology.
The passive contact signals given by the fuel tank and the oxidant tank of the ground storehouse of the shooting range are isolated and converted, the optical signals are converted into electric signals to be transmitted to the signal acquisition equipment, and the electric signals are transmitted to the microcomputer through the RS485 bus technology, and isolation measures are taken to ensure that products on the arrow cannot be damaged when ground equipment fails.
The PI optical coupling isolation conversion unit has the following functions: signals of the filling liquid level of the oxidant tank are collected, and the signals are respectively four liquid level detection points of y1, y2, y3 and y 4. Collecting signals of filling liquid level of a fuel tank, wherein the signals are four liquid level detection points r1, r2, r3 and r 4;
the functions of the tank filling signal conversion unit include: receiving ground oxidant filling overflow signals, including switching value signals of y1 zero liquid level, y1 filling and leaking valve opening, y1 propellant overflow, y2 zero liquid level, y2 filling and leaking valve opening, y2 propellant overflow, y3 zero liquid level, y3 filling and leaking valve opening, y3 propellant overflow, preparation filling, emergency stop, filling start, filling end, warehouse fault and the like, and transmitting the switching value signals to a main control microcomputer for acquisition and interpretation. The pressure signal access pressure measurement conversion unit such as ground storehouse gas distribution platform, propellant at first, transmits the digital display control appearance in the collection equipment of power filling system through the transmission, and digital display control appearance converts the signal of telecommunication into pressure numerical value, shows pressure signal value at the front end display screen. Meanwhile, the numerical value of the digital display controller transmits data to the rear-end main control microcomputer through an RS485 bus technology, so that the state of the air source pressure of the storehouse can be judged. When the ground filling liquid level sends a signal, the signal is converted into a switching value signal through the PI optical coupling isolation conversion unit and is transmitted to the digital display controller, and the digital display controller is transmitted to the front end and the rear end through RS485 so that post personnel can visually test the dynamic state. When the seven pipes on the ground fall off, fill and overflow to send signals, the signals are converted into switching value signals through the storage tank filling signal conversion unit, the switching value signals are also sent to the front end and the rear end through the digital display control instrument, the collected information is sent to the rear end computer to be displayed, and the variation trend of the propellant filling flow and the temperature in the whole filling process can be judged and read through the displayed curve.
In one embodiment of the device for detecting rocket power filling system signals, the main control computer comprises a front-end industrial control computer and a rear-end interpretation computer, wherein the front-end industrial control computer is used for receiving RS485 bus data through a CONTEC data acquisition board card and displaying the data in real time; and the back-end interpretation computer is used for carrying out data interpretation and fault diagnosis.
And the RS485 signal transmitted by the signal acquisition equipment is analyzed, and the data is broadcasted to a rear-end interpretation hall for monitoring and interpretation.
In one embodiment of the device for detecting rocket power filling system signals, the digital display controller adopts a communication expansion card RS485 for communication, the isolation between the digital display controller and a common end for inputting instrument signals is more than 500Vrms, 8-bit data can be expanded, the baud rate of the digital display controller meets 300-38400, 32 instruments can be connected to one bus in parallel, and data can be transmitted to the front-end industrial personal computer and the rear-end interpretation computer through an ASCII communication protocol.
The invention provides a RS 485-based signal acquisition device of a universal rocket power filling system, which aims to solve the problems that the warehouse headers of a shooting range are various, the front and rear end data of the filling system cannot be linked in real time, and the universality among all types of rockets is not strong. The invention can meet the signal acquisition function of the power filling system in different test sites among different models, carries out front-end detection on the whole filling process of the rocket power system, and transmits data to the rear end for real-time interpretation through an RS485 bus technology. When a fault occurs in the filling process, the fault is timely found, and the system command can master the filling dynamic state in real time and master the power system shooting range test and propellant filling display information.
Through adopting above technical means, make it have following beneficial effect compared with prior art:
1. multiple instruments for detection are packaged in a front-end filling warehouse, so that ground test equipment of the carrier rocket is simplified;
2. by the RS485 bus technology, the whole-process monitoring of each key pressure value and liquid level signal in the power filling process by front end command and rear end command is realized;
3. the signal acquisition equipment meets the redundancy of functions of various models, realizes the maximum design, and can be used in a mutually compatible way when various models are produced by the same set of technical indexes. The front panel of the acquisition equipment is provided with the state change-over switch, so that the generalization of the power signal acquisition function of the ground test emission control equipment is realized, the design flow and the time period are reduced, and the time cost is saved.
The invention solves the problems that the system command can not monitor the gas source pressure of the gas distribution platform, the pressure of the propellant storage tank, the pressure of the gas cylinder and the like in real time in the filling process of the carrier rocket power system, and can not monitor the temperature of the propellant in the storage tank, the filling liquid level signal, the filling flow and the temperature of the propellant in the filling process of the propellant. The problem of be difficult to directly carry out the monitoring of directly perceivedly gathering to filling signal front and back end in the shooting range storehouse is solved. The invention can meet the signal acquisition function of the power filling system in different test sites among different models, and realizes the model removal and generalization of the ground equipment of the carrier rocket. The method is beneficial to the front-end system to direct and intuitively master the test dynamics and the scientific judgment of the back-end data interpretation personnel.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Those of skill would further appreciate that the various illustrative elements and algorithm steps described in connection with the embodiments disclosed herein may be implemented as electronic hardware, computer software, or combinations of both, and that the various illustrative components and steps have been described above generally in terms of their functionality in order to clearly illustrate this interchangeability of hardware and software. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the implementation. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present invention.
It will be apparent to those skilled in the art that various changes and modifications may be made in the invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (1)
1. An apparatus for detecting rocket power filling system signals, comprising:
one side of the pressure measurement and transmission conversion unit receives air source pressure signals given by a first-stage air distribution table, a second-stage air distribution table and a third-stage air distribution table of a filling storehouse;
the PI optical coupling isolation conversion unit is used for obtaining passive contact signals given by a ground filling and liquid level signal box and 28 switching value signals given by an R box and a Y box in total, and broadcasting the collected ground filling, overflowing and seven-tube falling signals to a main control computer for interpretation and display;
a storage tank filling signal conversion unit used for the storage tank filling signal conversion unit and used for respectively acquiring liquid level signals of four liquid level detection points of Y, Y and Y of each oxidant tank in the filling process of the oxidant tanks Y, Y and Y, respectively acquiring liquid level signals of four liquid level detection points of R, R and R of each fuel tank in the filling process of the fuel tanks R, R and R, respectively acquiring liquid level signals of four liquid level detection points of Y, Y and liquid level signals of four liquid level detection points of R, R and R which are passive contact signals, respectively converting the liquid level signals of the four liquid level detection points of Y, Y and Y of each oxidant tank and the liquid level signals of the four liquid level detection points of R, R and R of each fuel tank into electric signals and sending the electric signals to the main bus 485 technology through the RS485 bus technology when the monitored liquid levels reach specified positions Judging by a control computer;
the digital display control instrument and the main control computer are respectively connected with the pressure measurement transmission conversion unit, the PI optical coupling isolation conversion unit and the storage tank filling signal conversion unit;
the pressure measurement and transmission conversion unit is used for converting air source pressure signals given by the first-stage air distribution table and the second-stage air distribution table of the filling storehouse and pressure signals given by the third-stage air distribution table into electric signals through transmission, transmitting the electric signals to the digital display controller in the power filling system acquisition equipment, converting the electric signals into pressure numerical values by the digital display controller, and displaying the pressure signal values on a front-end display screen; meanwhile, the digital display controller transmits the displayed pressure signal value to the main control computer through an RS485 bus technology;
the main control computer comprises a front-end industrial control computer and a rear-end interpretation computer, wherein the front-end industrial control computer is used for receiving RS485 bus data through the CONTEC data acquisition board card and displaying the data in real time; the back-end interpretation computer is used for carrying out data interpretation and fault diagnosis;
the digital display controller selects a communication expansion card RS485 for communication, the isolation between the digital display controller and a signal input public end of the instrument is more than 500Vrms, 8-bit data is expanded, the baud rate of the digital display controller meets 300-38400, and 32 instruments are connected to one bus in parallel and used for transmitting data to the front-end industrial personal computer and the rear-end interpretation computer through an ASCII communication protocol.
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| CN101170251A (en) * | 2007-10-10 | 2008-04-30 | 三门尔格科技有限公司 | Electronic quick oil pressure relay device for oil filling power device |
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