CN109342067A - A kind of solid rocket ramjet test macro - Google Patents
A kind of solid rocket ramjet test macro Download PDFInfo
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- CN109342067A CN109342067A CN201811011757.5A CN201811011757A CN109342067A CN 109342067 A CN109342067 A CN 109342067A CN 201811011757 A CN201811011757 A CN 201811011757A CN 109342067 A CN109342067 A CN 109342067A
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- engine
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- feedback signal
- board
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Combustion & Propulsion (AREA)
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Abstract
The invention discloses a kind of solid rocket ramjet test macros, belong to solid rocket ramjet technical field, comprising: simulation of engine board, external equipment and host computer；The simulation of engine board is plugged on the card slot of host computer, for the pressure of simulated engine in actual work；The external equipment is used to receive the test instruction of host computer sending, and the actual rocket engine ground test of simulation or HWIL simulation process are realized by the control of simulation of engine board；The host computer is used to send test instruction to external equipment, to realize the real-time control to simulation of engine board；The present invention completes engines ground test run or Hardware-in-loop Simulation Experimentation for simulating solid rocket ramjet work whole process.
Description
Technical field
The invention belongs to solid rocket ramjet technical fields, and in particular to a kind of solid rocket ramjet survey
Test system.
Background technique
Combustion gas in oxygen and engine gas generator in air is mixed and burned by solid rocket ramjet
It generates thrust and increases the electronic devices such as executing agency, engine controller, sensor compared with traditional solid engines,
The specific impulse of engine is effectively increased, the range of missile armament is improved, volume is smaller, and weight is lighter, is the following war
The Main way of art missile power system research.Since China's solid rocket ramjet is also in the tackling key problem development stage, need
Largely test to verify its reliability requirements, therefore necessary testing equipment and test macro are particularly important.
Existing solid rocket ramjet simulator does not use modularized design, is a set of independent big system
System, volume is larger, higher cost；Simultaneously because leading to not without special solid rocket ramjet test macro
Engine operation data are acquired in experimentation in real time, greatly reduce the probability of success of test in this way, after can not also carrying out
Continuous analysis of experiments.
Summary of the invention
In view of this, the object of the present invention is to provide a kind of solid rocket ramjet test macro, it is solid for simulating
Body rocket ramjet work whole process, completes engines ground test run or Hardware-in-loop Simulation Experimentation.
The present invention is achieved through the following technical solutions:
A kind of solid rocket ramjet test macro, comprising: simulation of engine board, external equipment and host computer；
The simulation of engine board is plugged on the card slot of host computer, for the pressure of simulated engine in actual work
By force；
The external equipment includes simulation flying control equipment, engine controller and servo mechanism；
The simulation flying control equipment is used to receive the test instruction of host computer sending, and the test received is instructed and is sent
To engine controller；The test instruction includes: flow instruction and firing command；
The engine controller is used to receive the test instruction that simulation flying control equipment is sent；If what is received is that igniting refers to
It enables, firing command is sent to simulation of engine board, simulation of engine board completes the igniting of simulated engine；
If what is received is flow instruction, the instruction of pressure needed for flow instruction is converted to engine, then by pressure
The pressure analog feedback signal for the simulation of engine board for instructing and receiving is converted to angle command signal and is sent to servo
Structure；
Connecting rod pendulum after the servo mechanism receives the angle command signal of engine controller transmission, in servo mechanism
Angle identical with angle command signal is moved, angle feedback signal is generated and is sent to angle feedback signal in real time and start
Machine simulates board；Simulation of engine board resolves to obtain pressure analog feedback signal according to the angle feedback signal, retransmits
To engine controller, the closed loop of pressure analog feedback signal is formed；
Wherein, to the real-time control of the angle of servo mechanism as to the simulation pressure of the generation of simulation of engine board
Thus real-time control meets sets requirement to guarantee to simulate pressure, the simulation pressure is what pressure analog feedback signal was recorded
Pressure values.
Further, the simulation of engine board includes: external signal input and output control unit module, engine mould
Shape parameter solving unit, A/D input module, D/A output module, discrete magnitude output module and serial communication modular；
External signal input and output control unit module in the simulation of engine board from servo mechanism for that will connect
The angle feedback signal received is sent to engine mockup parameter calculation unit module by internal bus；
The engine mockup parameter calculation unit module is for being converted to obtained angle feedback signal by resolving
Pressure digital feedback signal needed for engine controller, and it is sent to external signal input and output control unit module；
The pressure digital feedback signal that the external signal input and output control unit module is used to obtain is defeated by D/A
Module is converted to pressure analog feedback signal and is sent to engine controller out；
The external signal input and output control unit module receives the point of engine controller by serial communication modular
Fire instruction；And firing command is sent to discrete magnitude output module；
The discrete magnitude output module is received to after firing command, by connecting the positive and negative electrode of its lead, to simulate
The igniting of engine.
Further, the simulation of engine board further includes power conversion module, and the power conversion module is used for will
Outer power voltage conversion is an externally input required for output control unit module and engine mockup parameter calculation unit module
Voltage, realize power supply to external input and output control unit module and engine mockup parameter calculation unit.
Further, the simulation of engine board further includes pci bus driver, and the pci bus driver is used for
Reset operation is carried out to engine mockup parameter calculation unit module by host computer.
Further, the simulation of engine board further includes data memory module；Data memory module is for receiving simultaneously
The pressure digital feedback signal that storage engine mockup parameter calculation unit module calculates.
Further, the simulation of engine board further includes program download interface, described program download interface for pair
Engine mockup parameter calculation unit module carries out software modification and debugging.
The utility model has the advantages that (1) simulation of engine board of the invention is PCI board card, it is plugged on the card slot of host computer, solves
The problem of in the prior art host computer and simulation of engine device must be two sets of autonomous systems realizes simulation of engine dress
Set integration, the modularized design with host computer, can facilitate transplanting in arbitrarily with PCI board card card slot industrial control computer on,
Reduce testing equipment, reduce costs and is easy to carry about with one.
(2) simulation of engine board of the invention has reserved program download interface, in the case where bulk test system,
Only needing to modify software can be realized different test requirements documents.
(3) present invention can simulate the test stream for completing engines ground test run under not true engine conditions
Journey can be combined on guided missile other component and carry out HWIL simulation process, substantially increase in this way engines ground test run and
The reliability and the probability of success of guided missile practical flight.
Detailed description of the invention
Fig. 1 is structure composition schematic diagram of the invention.
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
A kind of solid rocket ramjet test macro is present embodiments provided, referring to attached drawing 1, comprising: engine mould
Quasi- board, external equipment and host computer；
The simulation of engine board is plugged on the card slot of host computer, for the pressure of simulated engine in actual work
By force；
The external equipment is used to receive the test instruction of host computer sending, by the control of simulation of engine board come real
Now simulate actual rocket engine ground test or HWIL simulation process；
The host computer is used to send test instruction to external equipment, to realize the real-time control to simulation of engine board
System；
Wherein, the external equipment includes simulation flying control equipment, engine controller and servo mechanism；
The simulation flying control equipment is used to receive the test instruction of host computer sending, and the test received is instructed and is sent
To engine controller；
The engine controller is used to receive the test instruction that simulation flying control equipment is sent, and (test instructs
Flow instruction and firing command), and pressure needed for flow instruction is converted to engine instructs, then will by PI control algolithm
The pressure analog feedback signal of simulation of engine board that pressure is instructed and received, which is converted to angle command signal and is sent to, to be watched
Take mechanism (initial value of pressure analog feedback signal is preset in engine controller, when initial, by pressure instruction and it is preset
The initial value of pressure analog feedback signal is converted to angle command signal and is sent to servo mechanism)；Firing command is sent simultaneously
Give simulation of engine board, the accurate igniting of the complete coupled engines of simulation of engine board；
Connecting rod pendulum after the servo mechanism receives the angle command signal of engine controller transmission, in servo mechanism
Angle identical with angle command signal is moved, angle feedback signal is generated and is sent to angle feedback signal in real time and start
Machine simulates board；Wherein, the simulation pressure to the real-time control of the angle of servo mechanism as to the generation of simulation of engine board
The real-time control of (the simulation pressure is the pressure values that pressure analog feedback signal is recorded) by force, thus expires to guarantee to simulate pressure
Sufficient sets requirement, to complete to simulate actual rocket engine ground test or HWIL simulation process；
The simulation of engine board includes external signal input and output control unit module, engine mockup parameter calculation
Unit, A/D input module, D/A output module, discrete magnitude output module, power conversion module, serial communication modular, pci bus
Driver, data memory module and program download interface；
External signal input and output control unit module in the simulation of engine board will be connect by A/D input module
The angle feedback signal received is sent to engine mockup parameter calculation unit module by internal bus；
The engine mockup parameter calculation unit module resolves obtained angle feedback signal for engine controller
Required pressure digital feedback signal, and it is sent to external signal input and output control unit module；Meanwhile it being sent to data and depositing
Storage module is stored；
Obtained pressure digital feedback signal is exported mould by D/A by the external signal input and output control unit module
Block is converted to pressure analog feedback signal and is sent to engine controller；
The external signal input and output control unit module receives the point of engine controller by serial communication modular
Fire instruction；And firing command is sent to discrete magnitude output module；
The discrete magnitude output module is received to after firing command, by connecting the positive and negative electrode of its lead, to simulate
The igniting of engine；
The power conversion module is used to outer power voltage conversion being an externally input output control unit module and hair
Voltage required for Motivation Model parameter calculation unit module is realized to external input and output control unit module and engine mould
The power supply of shape parameter solving unit；
The pci bus driver is used to carry out reset behaviour to engine mockup parameter calculation unit module by host computer
Make；
Described program download interface is used to carry out software modification and debugging to engine mockup parameter calculation unit module, with
Meet different test demands.
Working principle: host computer sends out test instruction (including flow instruction to engine controller by simulation flying control equipment
And firing command) after, after engine controller receives firing command, firing command is sent to hair by serial communication modular
Motivation simulates the external signal input/output units module in board, and external signal input/output units module is again by firing command
It is sent to discrete magnitude output module, discrete magnitude output module is received to after firing command, by connecting the positive and negative electrode of its lead
It connects, carrys out the igniting of simulated engine；
After engine controller receives flow instruction, the instruction of pressure needed for flow instruction is converted to engine, then
The initial value of pressure instruction and preset pressure analog feedback signal is converted into angle command signal hair by PI control algolithm
Servo mechanism is given, after servo mechanism receives angle command signal, the connecting rod swing in servo mechanism is believed to angle command
Number identical angle generates angle feedback signal, and angle feedback signal is sequentially passed through to A/D input module, outside in real time
Signal input-output unit module, internal bus are sent to engine mockup parameter calculation unit module；
The engine mockup parameter calculation unit module, which is converted to obtained angle feedback signal by resolving, to be started
Pressure digital feedback signal needed for machine controller is simultaneously sent to external input output control unit module, external input output control
Pressure digital feedback signal is converted to pressure analog feedback signal by D/A output module and is sent to engine by unit module processed
Controller, the instruction of engine controller pressure according to needed for obtained pressure analog feedback signal and engine are converted to angle
Command signal is sent to servo mechanism, after servo mechanism receives the angle command of engine controller transmission, in servo mechanism
Connecting rod swing to angle identical with angle command signal, the real-time control to the angle of servo mechanism is to engine mould
The real-time control of the simulation pressure (the simulation pressure is the pressure values that pressure analog feedback signal is recorded) of the generation of quasi- board,
Thus meet sets requirement to guarantee to simulate pressure, to complete to simulate actual rocket engine ground test or HWIL simulation stream
Journey；Meanwhile servo mechanism generates angle feedback signal, then the angle feedback signal is sent to simulation of engine board, with
Realize the closed loop of pressure analog feedback signal.
Meanwhile the data resolved are sent to simulation flying control equipment by engine controller, simulate flying control equipment for the number
According to host computer is sent to, to carry out real-time display.
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (6)
1. a kind of solid rocket ramjet test macro characterized by comprising simulation of engine board, external equipment
And host computer；
The simulation of engine board is plugged on the card slot of host computer, for the pressure of simulated engine in actual work；
The external equipment includes simulation flying control equipment, engine controller and servo mechanism；
The simulation flying control equipment is used to receive the test instruction of host computer sending, and the test received instruction is sent to
Motivation controller；The test instruction includes: flow instruction and firing command；
The engine controller is used to receive the test instruction that simulation flying control equipment is sent；If what is received is firing command,
Firing command is sent to simulation of engine board, simulation of engine board completes the igniting of simulated engine；
If what is received is flow instruction, pressure needed for flow instruction is converted to engine is instructed, then pressure is instructed
Angle command signal, which is converted to, with the pressure analog feedback signal of the simulation of engine board received is sent to servo mechanism；
After the servo mechanism receives the angle command signal of engine controller transmission, the connecting rod swing in servo mechanism is arrived
Angle identical with angle command signal generates angle feedback signal and angle feedback signal is sent to engine mould in real time
Quasi- board；Simulation of engine board resolves to obtain pressure analog feedback signal according to the angle feedback signal, is then forwarded to hair
Motivation controller forms the closed loop of pressure analog feedback signal；
Wherein, to the real-time control of the angle of servo mechanism as to the real-time of the simulation pressure of the generation of simulation of engine board
Control, thus meets sets requirement to guarantee to simulate pressure, and the simulation pressure is the pressure that pressure analog feedback signal is recorded
Value.
2. a kind of solid rocket ramjet test macro as described in claim 1, which is characterized in that the engine mould
Quasi- board includes: external signal input and output control unit module, engine mockup parameter calculation unit, A/D input module, D/
A output module, discrete magnitude output module and serial communication modular；
External signal input and output control unit module in the simulation of engine board from servo mechanism for that will receive
Angle feedback signal engine mockup parameter calculation unit module is sent to by internal bus；
The engine mockup parameter calculation unit module, which is used to be converted to obtained angle feedback signal by resolving, to be started
Pressure digital feedback signal needed for machine controller, and it is sent to external signal input and output control unit module；
The external signal input and output control unit module is used to obtained pressure digital feedback signal exporting mould by D/A
Block is converted to pressure analog feedback signal and is sent to engine controller；
The external signal input and output control unit module is referred to by the igniting that serial communication modular receives engine controller
It enables；And firing command is sent to discrete magnitude output module；
The discrete magnitude output module is received to after firing command, by connecting the positive and negative electrode of its lead, is started to simulate
The igniting of machine.
3. a kind of solid rocket ramjet test macro as claimed in claim 2, which is characterized in that the engine mould
Quasi- board further includes power conversion module, and the power conversion module is used to outer power voltage conversion being an externally input output
Voltage required for control unit module and engine mockup parameter calculation unit module is realized and controls list to external input and output
The power supply of element module and engine mockup parameter calculation unit.
4. a kind of solid rocket ramjet test macro as claimed in claim 2, which is characterized in that the engine mould
Quasi- board further includes pci bus driver, and the pci bus driver is used for through host computer to engine mockup parameter calculation
Unit module carries out reset operation.
5. a kind of solid rocket ramjet test macro as claimed in claim 2, which is characterized in that the engine mould
Quasi- board further includes data memory module；Data memory module is for receiving and storing engine mockup parameter calculation unit module
The pressure digital feedback signal calculated.
6. a kind of solid rocket ramjet test macro as claimed in claim 2, which is characterized in that the engine mould
Quasi- board further includes program download interface, and described program download interface is used to carry out engine mockup parameter calculation unit module
Software modification and debugging.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811011757.5A CN109342067A (en) | 2018-08-31 | 2018-08-31 | A kind of solid rocket ramjet test macro |
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| CN201811011757.5A CN109342067A (en) | 2018-08-31 | 2018-08-31 | A kind of solid rocket ramjet test macro |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110109374A (en) * | 2019-05-13 | 2019-08-09 | 九州云箭(北京)空间科技有限公司 | The Hardware In The Loop Simulation Method and device of liquid-propellant rocket engine thrust regulating system |
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