CN105044431A - Ignition sequence signal measurement method used for solid propellant ramjet ground test and ignition sequence signal measurement device used for solid propellant ramjet ground test - Google Patents
Ignition sequence signal measurement method used for solid propellant ramjet ground test and ignition sequence signal measurement device used for solid propellant ramjet ground test Download PDFInfo
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- CN105044431A CN105044431A CN201510368567.9A CN201510368567A CN105044431A CN 105044431 A CN105044431 A CN 105044431A CN 201510368567 A CN201510368567 A CN 201510368567A CN 105044431 A CN105044431 A CN 105044431A
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Abstract
The present invention provides an ignition sequence signal measurement method used for a solid propellant ramjet ground test and an ignition sequence signal measurement device used for the solid propellant ramjet ground test. The device comprises a current sensor, a DC voltage stabilization source and a signal conditioning module, the current sensor can be accessed in a corresponding ignition loop of the solid propellant ramjet ground test, the DC voltage stabilization source supplies power to the current sensor, and an output voltage signal of the current sensor is processed into a standard electric signal according with requirements by the signal conditioning module. The present invention relates to the measurement method of obtaining an ignition sequence signal indirectly from the ignition loop. The input and output loops are isolated completely, the current sensor carries out the real-time non-contact measurement on a DC and an AC in the ignition loop on an electric isolation condition, and a voltage signal proportional with the currents in the ignition loop at any time can be outputted by tracking a voltage output end. The measurement method and the measurement device of the present invention enable the measurement precision to be improved, do not influence the ignition loop and a data acquisition system at all, are convenient, at the same time, enable the safety and reliability of an ignition test to be enhanced.
Description
Technical field
The present invention relates to signal testing technical field, specifically a kind of igniting clock signal measuring method for solid rocket ramjet ground experiment and device.
Background technology
Igniting clock signal is the important parameter that must provide in solid rocket ramjet test, and it is directly connected to the accuracy at engine operating duration zero point.Solid rocket ramjet can produce multiple ignition signal having critical timing requirements in ground firing, accurately and reliably survey record igniting clock signal becomes one of gordian technique of solid rocket ramjet test, for solid rocket ramjet development provides important reference data.
The method of current measurement igniting clock signal has:
1, NI clamp is utilized to carry the measuring method of relay acquisition igniting clock signal.
This is that a kind of NI clamp controlling igniting sequential that utilizes carries the measuring method that relay obtains igniting clock signal indirectly.One of them plate is carried relay and is set to lock-on relay, the plate controlling to light a fire with other carries the instruction of relay synchronized transmission, and sends to data acquisition system (DAS) to carry out record as igniting clock signal this lock-on relay instruction.Schematic diagram is shown in Fig. 1.
There is following drawback in the method:
(1) require that the command interval time of lock-on relay must be greater than its switching time.Otherwise, being forced to when not completing this switching over perform next instruction, twice instruction must being caused all to lose efficacy and the serious consequence that igniting cannot be measured zero point, causing test figure to lose efficacy.
(2) electric initiating portfire is issued to from firing command, the transmission of igniting clock signal will through the switch control rule of two-step relay (plate carries relay and ignition relay), plate carries the asynchronism of relay and the switching over precision of two-step relay, makes to certainly exist the time deviation of can not ignore between the signal that records and actual signal.
2, the measuring method of igniting clock signal is obtained by ignition relay.
This is a kind of measuring method indirectly obtaining igniting clock signal from ignition relay, does not namely have the pair of contact of access point ignition circuit to obtain make-and-break signal from ignition relay, in this, as igniting clock signal.Schematic diagram is shown in Fig. 2.
The method is improved for method one, eliminates plate and carries the synchronous error that relay brings, but still have following drawback:
(1) require that ignition relay has multipair contact, and the asynchronism of each pair of contact action makes to certainly exist the mistiming between the signal of measurement and true ignition signal.
(2) two pairs of contacts of ignition relay tie point ignition circuit and data acquisition system (DAS) respectively, the data acquisition system (DAS) that the firing circuit flowing through big current must be run to light current brings interference, and once igniting is abnormal, the destruction that cannot envision will be brought to data acquisition system (DAS), cause the serious consequence that test figure is all lost, bring serious threat to test reliability and security, therefore this method is urgently improved.
Due to measuring principle itself, the current two kinds precision measuring igniting clock signal method still have deficiency.
Summary of the invention
The present invention one of is intended to solve the problems of the technologies described above at least to a certain extent or at least provides a kind of useful business to select.For this reason, one object of the present invention is that providing a kind of has the high-precision igniting clock signal measuring method for solid rocket ramjet ground experiment, and utilizes current sensor design pick-up unit to carry out the measurement of igniting clock signal accordingly.
Technical scheme of the present invention is:
In one aspect of the invention, the present invention proposes a kind of igniting clock signal measuring method for solid rocket ramjet ground experiment, it is characterized in that: comprise
Current sensor is accessed respectively in the multi-stage ignition loop of solid rocket ramjet ground experiment; In portfire in current sensor in self place ignition circuit of resistance and this current sensor, resistance is identical, and current sensor connects DC voltage-stabilizing power supply;
The multi-stage ignition loop of solid rocket ramjet ground experiment is connected according to test design sequential;
Satisfactory standard electric signal is obtained after the output voltage signal of current sensor is carried out signal condition.
In one aspect of the invention, the present invention proposes a kind of igniting clock signal measurement mechanism for solid rocket ramjet ground experiment, it is characterized in that: comprise current sensor, direct-flow voltage regulation source, Signal-regulated kinase; Current sensor can access in the corresponding ignition circuit of solid rocket ramjet ground experiment; Direct-flow voltage regulation source is powered to current sensor; The output voltage signal of current sensor obtains satisfactory standard electric signal after Signal-regulated kinase.
Adopt electromagnetic induction principle, current sensor is nested in ignition circuit, its magneto sensor is made to produce a magnetic field to the external DC voltage-stabilizing power supply of sensor, when have in tested ignition circuit electric current by time produce induced potential immediately, and through amplification after be transformed to according to certain rules satisfactory standard electric signal export.This is a kind of measuring method indirectly obtaining igniting clock signal from ignition circuit, input and output loop is completely isolated, current sensor carries out real-time non-contact measurement to the AC DC electric stream in ignition circuit under electrically isolated condition, by the voltage signal of floating voltage output terminal with regard to current in proportion in exportable any moment and ignition circuit.Compared to aforementioned two kinds of methods, method of the present invention has that precision is higher, the advantage of better reliability.
In addition, according to embodiments of the invention, following additional technical characteristic can also be had:
According to embodiments of the invention, the present invention proposes a kind of igniting clock signal measurement mechanism for solid rocket ramjet ground experiment, it is characterized in that: comprise four current sensors, wherein in the internal resistance value of the first current sensor and the portfire of roll booster ignition circuit in solid rocket ramjet ground experiment, resistance is identical, the internal resistance value of the second current sensor is identical with resistance in the portfire of entrance blanking cover ignition circuit in solid rocket ramjet ground experiment, the internal resistance value of the 3rd current sensor is identical with resistance in the portfire of solid rocket ramjet ground experiment middle outlet blanking cover ignition circuit, the internal resistance value of the 4th current sensor is identical with resistance in the portfire in engine ignition loop in solid rocket ramjet ground experiment.
Additional aspect of the present invention and advantage will part provide in the following description, and part will become obvious from the following description, or be recognized by practice of the present invention.
Accompanying drawing explanation
Above-mentioned and/or additional aspect of the present invention and advantage will become obvious and easy understand from accompanying drawing below combining to the description of embodiment, wherein:
Fig. 1: plate carries relay measures igniting clock signal schematic diagram;
Fig. 2: ignition relay measures igniting clock signal schematic diagram;
Fig. 3: measurement igniting clock signal schematic diagram of the present invention;
Fig. 4: the test comparison schematic diagram in embodiment.
Embodiment
Be described below in detail embodiments of the invention, the example of described embodiment is shown in the drawings, and wherein same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.
In describing the invention, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ", " thickness ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", " outward ", " clockwise ", orientation or the position relationship of the instruction such as " counterclockwise " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore limitation of the present invention can not be interpreted as.
In addition, term " first ", " second " only for describing object, and can not be interpreted as instruction or hint relative importance or imply the quantity indicating indicated technical characteristic.Therefore, be limited with " first ", the feature of " second " can express or impliedly comprise one or more these features.In describing the invention, the implication of " multiple " is two or more, unless otherwise expressly limited specifically.
According to embodiments of the invention, a kind of igniting clock signal measuring method for solid rocket ramjet ground experiment that the present invention proposes, comprises
As shown in Figure 3, in the multi-stage ignition loop of solid rocket ramjet ground experiment, current sensor is accessed respectively; And due to portfire difference, the initial firing current of every grade of ignition circuit there are differences, therefore accurate recording every waypoint fire clock signal is wanted will to carry out choose reasonable to the parameter index of current sensor, so require that in the portfire in current sensor in self place ignition circuit of resistance and this current sensor, resistance is identical; In addition, current sensor connects DC voltage-stabilizing power supply;
Then, the multi-stage ignition loop of solid rocket ramjet ground experiment is connected according to test design sequential; Solid rocket ramjet fire trial mainly comprises roll booster igniting, the igniting of entrance blanking cover, the igniting of outlet blanking cover and engine ignition totally four ignition processes, can produce the igniting clock signal of at least 4 grades;
Satisfactory standard electric signal is obtained after finally the current sensor output voltage signal in every grade of ignition circuit being carried out signal condition.
The method of the invention adopts electromagnetic induction principle, current sensor is nested in ignition circuit, its magneto sensor is made to produce a magnetic field to the external DC voltage-stabilizing power supply of sensor, when have in tested ignition circuit electric current by time produce induced potential immediately, and through amplification after be transformed to according to certain rules satisfactory standard electric signal export.This is a kind of measuring method indirectly obtaining igniting clock signal from ignition circuit, input and output loop is completely isolated, current sensor carries out real-time non-contact measurement to the AC DC electric stream in ignition circuit under electrically isolated condition, by the voltage signal of floating voltage output terminal with regard to current in proportion in exportable any moment and ignition circuit.Compared to aforementioned two kinds of methods, method of the present invention has that precision is higher, the advantage of better reliability.
According to method requirement, the present invention proposes a kind of igniting clock signal measurement mechanism for solid rocket ramjet ground experiment, comprises current sensor, direct-flow voltage regulation source, Signal-regulated kinase; Current sensor can access in the corresponding ignition circuit of solid rocket ramjet ground experiment; Direct-flow voltage regulation source is powered to current sensor; The output voltage signal of current sensor obtains satisfactory standard electric signal after Signal-regulated kinase.
Further, because solid rocket ramjet fire trial mainly comprises roll booster igniting, entrance blanking cover is lighted a fire, the igniting of outlet blanking cover and engine ignition totally four ignition processes, so at least comprise four current sensors in measurement mechanism, wherein in the internal resistance value of the first current sensor and the portfire of roll booster ignition circuit in solid rocket ramjet ground experiment, resistance is identical, the internal resistance value of the second current sensor is identical with resistance in the portfire of entrance blanking cover ignition circuit in solid rocket ramjet ground experiment, the internal resistance value of the 3rd current sensor is identical with resistance in the portfire of solid rocket ramjet ground experiment middle outlet blanking cover ignition circuit, the internal resistance value of the 4th current sensor is identical with resistance in the portfire in engine ignition loop in solid rocket ramjet ground experiment.Specific in the present embodiment, measurement mechanism adopts Redundancy Design.
In order to the existing methodical precision of two kinds in the method that proposes the present invention and background technology contrast, adopt the ignition relay of two pairs of contacts in the present embodiment, object is in single test, to carry out the measurement of three kinds of methods simultaneously.To compare analysis in identical time origin.Contrast test circuit theory diagrams are as Fig. 4.
The current sensor that access is identical with portfire internal resistance at different levels respectively in test-fired four ignition circuits of solid rocket ramjet, its input/output interface connects the ignition lead of corresponding ignition circuit, current sensor output signal to Signal-regulated kinase, Signal-regulated kinase is connected with data acquisition system (DAS) by aviation socket output interface, and the external 5V direct-flow voltage regulation source of power lead powers (method 3 wiring completes) to current sensor.Meanwhile, respective plate is carried relay to be connected with data acquisition system (DAS) respective channel respectively (method 1 and method 2 wiring complete) with the remaining pair of contact of ignition relay.Afterwards, run igniting sequential control system software, igniting time sequence parameter is set as shown in table 1.1, starts and control, ignition relay at different levels performs timing instructions, is carried the Output rusults of relay, ignition relay and proving installation of the present invention by data acquisition system data board.Debugging test like this carries out 3 times respectively.Test findings is as shown in table 1.2.1,1.2.3,1.2.3.
Table 1.1 is lighted a fire time sequence parameter
Table 1.2.1 debugging test result
Table 1.2.2 bis-debugging test results
Table 1.2.3 tri-debugging test results
From above-mentioned measurement result computational analysis:
(1) there is the superposition of two-stage error between the test signal that obtains of Application way 1 and actual signal, namely the switching time of ignition relay and plate carry the asynchronism error of relay, and error range is 17ms ~ 24ms;
(2) there is ignition relay self contact asynchronism between the test signal that obtains of Application way 2 and actual signal and contact change-over disturbs the brought time difference mutually, this by mistake the characteristic of extent and selected ignition relay and fired state relevant, have very large uncertainty, be generally several milliseconds to a few tens of milliseconds not etc.;
(3) there is the response time difference of current sensor between the test signal that obtains of Application way 3 and actual signal, i.e. 0ms ~ 1ms.
By more known, the precision that method 3 measures igniting clock signal is the highest.
The present invention adopts current sensor to be electricity capacity separation sensor, it is nested in ignition circuit, test signal is measured from ignition terminal, and test signal is transformed into satisfactory standard electric Signal transmissions to acquisition system, contrast test illustrates, the present invention both improve measuring accuracy, has any impact can not to again ignition circuit and data acquisition system (DAS), simultaneously easily, test-fired safety and reliability is in turn enhanced.
Although illustrate and describe embodiments of the invention above, be understandable that, above-described embodiment is exemplary, can not be interpreted as limitation of the present invention, those of ordinary skill in the art can change above-described embodiment within the scope of the invention when not departing from principle of the present invention and aim, revising, replacing and modification.
Claims (3)
1., for an igniting clock signal measuring method for solid rocket ramjet ground experiment, it is characterized in that: comprise
Current sensor is accessed respectively in the multi-stage ignition loop of solid rocket ramjet ground experiment; In portfire in current sensor in self place ignition circuit of resistance and this current sensor, resistance is identical, and current sensor connects DC voltage-stabilizing power supply;
The multi-stage ignition loop of solid rocket ramjet ground experiment is connected according to test design sequential;
Satisfactory standard electric signal is obtained after the output voltage signal of current sensor is carried out signal condition.
2., for an igniting clock signal measurement mechanism for solid rocket ramjet ground experiment, it is characterized in that: comprise current sensor, direct-flow voltage regulation source, Signal-regulated kinase; Current sensor can access in the corresponding ignition circuit of solid rocket ramjet ground experiment; Direct-flow voltage regulation source is powered to current sensor; The output voltage signal of current sensor obtains satisfactory standard electric signal after Signal-regulated kinase.
3. a kind of igniting clock signal measurement mechanism for solid rocket ramjet ground experiment according to claim 2, it is characterized in that: comprise four current sensors, wherein in the internal resistance value of the first current sensor and the portfire of roll booster ignition circuit in solid rocket ramjet ground experiment, resistance is identical, the internal resistance value of the second current sensor is identical with resistance in the portfire of entrance blanking cover ignition circuit in solid rocket ramjet ground experiment, the internal resistance value of the 3rd current sensor is identical with resistance in the portfire of solid rocket ramjet ground experiment middle outlet blanking cover ignition circuit, the internal resistance value of the 4th current sensor is identical with resistance in the portfire in engine ignition loop in solid rocket ramjet ground experiment.
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| CN201510368567.9A CN105044431A (en) | 2015-06-29 | 2015-06-29 | Ignition sequence signal measurement method used for solid propellant ramjet ground test and ignition sequence signal measurement device used for solid propellant ramjet ground test |
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| CN201510368567.9A CN105044431A (en) | 2015-06-29 | 2015-06-29 | Ignition sequence signal measurement method used for solid propellant ramjet ground test and ignition sequence signal measurement device used for solid propellant ramjet ground test |
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Citations (3)
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|---|---|---|---|---|
| GB1498543A (en) * | 1976-02-19 | 1978-01-18 | Sun Electric Corp | Distributor voltage sensor |
| CN103901339A (en) * | 2014-04-16 | 2014-07-02 | 上海航天电子通讯设备研究所 | Device and method for detecting one-way reliability of carrier rocket two-out-of-three ignition circuit |
| CN204312242U (en) * | 2014-12-18 | 2015-05-06 | 深圳市健科电子有限公司 | A kind of ATS Automatic Test System of ignition module |
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2015
- 2015-06-29 CN CN201510368567.9A patent/CN105044431A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1498543A (en) * | 1976-02-19 | 1978-01-18 | Sun Electric Corp | Distributor voltage sensor |
| CN103901339A (en) * | 2014-04-16 | 2014-07-02 | 上海航天电子通讯设备研究所 | Device and method for detecting one-way reliability of carrier rocket two-out-of-three ignition circuit |
| CN204312242U (en) * | 2014-12-18 | 2015-05-06 | 深圳市健科电子有限公司 | A kind of ATS Automatic Test System of ignition module |
Non-Patent Citations (2)
| Title |
|---|
| 庞海洋等: "发动机地面试验点火信号在线隔离测量方法研究", 《固体火箭技术》 * |
| 郭建忠等: "提高固体发动机试验时统零点及时序控制方法研究", 《计算机测量与控制》 * |
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Inventor after: Yang Xiaohui Inventor after: Li Jie Inventor after: Wang Ling Inventor after: Zhu Xinli Inventor after: He Desheng Inventor after: Huang Peng Inventor after: Zuo Hongxing Inventor after: Zhao Jiwei Inventor after: Lan Baogang Inventor after: Huo Fei Inventor after: Zhang Yuxia Inventor before: Yang Xiaohui Inventor before: Zhu Xinli Inventor before: Huang Peng Inventor before: Zuo Hongxing Inventor before: Zhao Jiwei Inventor before: Lan Baogang Inventor before: Huo Fei Inventor before: Zhang Yuxia |
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