CN109857081A - A kind of carrier rocket emissioning controling signal measurement method - Google Patents
A kind of carrier rocket emissioning controling signal measurement method Download PDFInfo
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- CN109857081A CN109857081A CN201811536076.0A CN201811536076A CN109857081A CN 109857081 A CN109857081 A CN 109857081A CN 201811536076 A CN201811536076 A CN 201811536076A CN 109857081 A CN109857081 A CN 109857081A
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- emissioning controling
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- controling signal
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Abstract
The invention discloses a kind of carrier rocket emissioning controling signal measurement methods, realize the high-precision detection to not charged emissioning controling signal in carrier rocket test emission process, and the flexible setting of not charged emissioning controling signal availability deciding threshold value, simultaneously, it can also complete effective to emissioning controling signal and invalid state high-precision timing, it ensure that the accuracy of signal acquisition and the accuracy of judgement, provide high-precision emissioning controling signal so as to the test for carrier rocket, emission process.
Description
Technical field
The invention belongs to carrier rocket testing field, be a kind of not charged emissioning controling signal of carrier rocket high-precision,
High reliability detection method.
Background technique
As active service is succeeded in developing and be included in new-generation digital carrier rocket, the New Launch based on digital signal
Gradually instead of original simulation launching control equipment, the transmitting of carrier rocket controls signal in carrier rocket for transmitting, control equipment
Power supply, gas supply, igniting, flight, key operations control aspect play very important effect, therefore, emit carrier rocket and control
It is very important for the high-acruracy survey of signal processed, currently, carrier rocket is only able to achieve height electricity to the detection for generating control signal
Flat detection cannot achieve and send out control signal validity to uncharged contact type, the duration carries out high-precision detection.
Summary of the invention
The main object of the present invention is to solve carrier rocket to test, in emission process, not charged emissioning controling signal measurement
In to distinguishing validity inaccuracy problem, realize the high-precision detection of rocket hair control signal validity, be completed at the same time to hair control letter
Number effectively and the high-precision timing of invalid state, high-precision emission control is provided for the test of carrier rocket, emission process and is believed
Number.
A kind of carrier rocket emissioning controling signal measurement method of the invention, detailed process are as follows:
Step 1: being initialized starting to acquire the moment, the state for being 0 by all data initializations；
Step 2: the detection voltage of+12V can be provided for not charged emissioning controling signal input terminal after the completion of initialization,
When without the input of not charged emissioning controling signal, circuit is obstructed, and test side voltage is 0, when there is not charged emissioning controling signal defeated
Fashionable, circuit is connected, and test side voltage is+12V；
Step 3: the voltage to test side improves, it is allowed to be converted into high level to be+3.3V, low level is the survey of 0V
Measure signal；
Step 4: from the measuring signal after the access conditioning of the input terminal of FPGA, FPGA carries out essence to the measuring signal of access
Degree is the timing of 0.2ms, and records the polarity of measuring signal at this time；Timing knot when measuring signal change in polarity, before variation
Fruit and signal polarity information will be saved into register；If measuring signal polarity is constant in 1 second, FPGA exports scheduled coding
To host, host measuring signal is notified not yet to change；
Step 5: the duration is more than setting time threshold value if measuring signal after change in polarity, then the signal is sentenced
Not Wei useful signal, the signal in register export it is to be output to caching etc., if the duration is less than setting time threshold value,
Invalid signals are determined as, register, the signal in caching are constant at this time, and return step four；When signal distinguishing validity is set
Between threshold value be traditionally arranged to be 1 second, can flexible configuration as needed；
Step 6: buffered signal update 0.2ms after, FPGA by caching timing result and signal polarity export to host
It is shown；
Step 7: test device continues or stops to detect according to control machine instruction.
The present invention realizes the high-precision detection (essence to not charged emissioning controling signal in carrier rocket test emission process
Degree is 0.2ms), and can realize and the validity high-precision of signal is detected, availability deciding threshold value can flexible setting；Meanwhile also
High-precision timing can be carried out to the make-and-break time of not charged emissioning controling signal, ensure that the accuracy and judgement of signal acquisition
Accuracy, meet the special testing requirement of new generation's carrier rocket.
Detailed description of the invention
Fig. 1 is measurement method operational flow diagram of the invention.
Fig. 2 is realization basic block diagram of the invention.
Specific embodiment
A kind of carrier rocket emissioning controling signal measurement method of the invention is described in further detail in conjunction with attached drawing, this
The detailed process of method are as follows:
Step 1: being initialized starting to acquire the moment, the state for being 0 by all data initializations；
Step 2: being not charged emissioning controling signal input terminal by the self-powered module of conditioning circuit after the completion of initialization
The detection voltage of offer+12V, when without the input of not charged emissioning controling signal, circuit is obstructed, and test side detection signal voltage is
0, it is judged as emissioning controling signal access failure, when there is the input of not charged emissioning controling signal, circuit is connected, test side detection letter
Number voltage is+12V, is judged as that emissioning controling signal is connected；
Step 3: the voltage to test side carries out rectifying and wave-filtering, while by conditioning circuit voltage conversion device to test side
It detects signal and carries out voltage conversion, be allowed to be converted into high level to be+3.3V, low level is the measuring signal of 0V, conveniently accessible
FPGA；
Step 4: from the measuring signal after the access conditioning of the input terminal of FPGA, FPGA carries out essence to the measuring signal of access
Degree is the timing of 0.2ms, and records the polarity of measuring signal at this time.Concrete operation method are as follows: 1 period of setting is in FPGA
Input signal of the timing signal of 0.2ms as all counters, meanwhile, for every drive test examination transmitting signal, two counters are set
One register, starting at the time of test transmitting signal is by just becoming negative of counter 1, is closed, counter 2 at the time of positive by negative change
Start at the time of test transmitting signal is positive by negative change, closing at the time of by just becoming negative, then two counters can obtain respectively
0.2ms pulse number namely signal duration in the high and low level time-continuing process of test transmitting signal.Work as measuring signal
When change in polarity, changing instantaneous timing result and signal polarity information will be saved into register；If measuring signal in 1 second
Polarity is constant, and the 1s timer in FPGA will export scheduled coding to host, and host measuring signal is notified not yet to become
Change；
Step 5: the duration is more than setting time threshold value if measuring signal after change in polarity, then the signal is sentenced
Not Wei useful signal, the signal in register export it is to be output to caching etc., if the duration is less than setting time threshold value,
Invalid signals are determined as, register, the signal in caching are constant at this time, and return step four；When signal distinguishing validity is set
Between threshold value be traditionally arranged to be 1 second, can flexible configuration as needed；
Step 6: buffered signal update 0.2ms after, FPGA by caching timing result and signal polarity export to host
It is shown；
Step 7: test device continues or stops to detect according to control machine instruction.
Claims (1)
1. a kind of carrier rocket emissioning controling signal measurement method can provide one for the not charged emissioning controling signal of carrier rocket
Kind of measurement method, which is characterized in that this method comprising the following specific steps
Step 1: being initialized starting to acquire the moment, the state for being 0 by all data initializations；
Step 2: can provide the detection voltage of+12V after the completion of initialization for not charged emissioning controling signal input terminal, work as nothing
When not charged emissioning controling signal inputs, circuit is obstructed, and test side voltage is 0, when there is the input of not charged emissioning controling signal,
Circuit is connected, and test side voltage is+12V；
Step 3: the voltage to test side improves, it is allowed to be converted into high level to be+3.3V, the measurement that low level is 0V is believed
Number；
Step 4: FPGA carries out precision to the measuring signal of access and is from the measuring signal after the access conditioning of the input terminal of FPGA
The timing of 0.2ms, and record the polarity of measuring signal at this time；When measuring signal change in polarity, timing result before variation and
Signal polarity information will be saved into register；If measuring signal polarity is constant in 1 second, FPGA can export scheduled coding extremely
Host, notice host measuring signal not yet change；
Step 5: the duration is more than setting time threshold value if measuring signal after change in polarity, then the signal is determined as
Useful signal, the signal in register export to be output to caching etc., if the duration is less than setting time threshold value, differentiate
For invalid signals, register, the signal in caching are constant at this time, and return step four；Signal distinguishing validity setting time threshold
Value is traditionally arranged to be 1 second, can flexible configuration as needed；
Step 6: buffered signal update 0.2ms after, FPGA by caching timing result and signal polarity export to host carry out
Display；
Step 7: test device continues or stops to detect according to control machine instruction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811536076.0A CN109857081A (en) | 2018-12-14 | 2018-12-14 | A kind of carrier rocket emissioning controling signal measurement method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811536076.0A CN109857081A (en) | 2018-12-14 | 2018-12-14 | A kind of carrier rocket emissioning controling signal measurement method |
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| Publication Number | Publication Date |
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| CN109857081A true CN109857081A (en) | 2019-06-07 |
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| CN201811536076.0A Pending CN109857081A (en) | 2018-12-14 | 2018-12-14 | A kind of carrier rocket emissioning controling signal measurement method |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102694530A (en) * | 2012-05-11 | 2012-09-26 | 蔡远文 | Pulse signal test device of inertial platform for launch vehicle |
| CN106508021B (en) * | 2012-06-18 | 2014-10-22 | 上海新跃仪表厂 | Spacecraft instructs pulsewidth identification circuit |
| CN105134451A (en) * | 2015-09-25 | 2015-12-09 | 天津斯巴克瑞汽车电子股份有限公司 | Pulse monitoring device for durability of automobile ignition coil and realizing method of pulse monitoring device |
| CN106685380A (en) * | 2016-12-28 | 2017-05-17 | 中国建材国际工程集团有限公司 | Accurate obtaining processing method of switching value rising edge signal of control system |
-
2018
- 2018-12-14 CN CN201811536076.0A patent/CN109857081A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102694530A (en) * | 2012-05-11 | 2012-09-26 | 蔡远文 | Pulse signal test device of inertial platform for launch vehicle |
| CN106508021B (en) * | 2012-06-18 | 2014-10-22 | 上海新跃仪表厂 | Spacecraft instructs pulsewidth identification circuit |
| CN105134451A (en) * | 2015-09-25 | 2015-12-09 | 天津斯巴克瑞汽车电子股份有限公司 | Pulse monitoring device for durability of automobile ignition coil and realizing method of pulse monitoring device |
| CN106685380A (en) * | 2016-12-28 | 2017-05-17 | 中国建材国际工程集团有限公司 | Accurate obtaining processing method of switching value rising edge signal of control system |
Non-Patent Citations (2)
| Title |
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| 程龙等: "运载火箭控制***信号综合测试方法", 《兵工自动化》 * |
| 解维奇等: "激光惯组脉冲信号计数***的设计与FPGA实现", 《科技信息》 * |
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Application publication date: 20190607 |
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