CN103532527A - Real-time and reliable inertia measuring device information recording system - Google Patents
Real-time and reliable inertia measuring device information recording system Download PDFInfo
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- CN103532527A CN103532527A CN201310300713.5A CN201310300713A CN103532527A CN 103532527 A CN103532527 A CN 103532527A CN 201310300713 A CN201310300713 A CN 201310300713A CN 103532527 A CN103532527 A CN 103532527A
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Abstract
The invention relates to a real-time and reliable inertia measuring device information recording system comprising a signal optical coupler isolation module, a digital filtering module, a signal counting and resetting module and a data latching module. With modes of an optical coupler isolation hardware circuit which is strictly calculated and designed, a digital filtering technology, a configurable (e.g. 5ms, 10ms) sampling period, two configurable modes that numerical reading of each sampling period is reset and cumulative counts are not reset, etc., requirements of real-time recording of inertia measuring device information of different missile-manufacturing periods and different data processing modes of missiles and rockets are met.
Description
Technical field
The present invention relates to reliable admission inertial measuring unit information system in real time.
Background technology
In the model control system such as guided missile, rocket, inertial measuring unit is to measure rocket around the device of the heart (angle) motion and particle (line) kinematic parameter, is used for determining the information such as attitude, position and speed in guided missile, rocket flight.Therefore, missile-borne, arrow borne computer need the information that admission inertial measuring unit gyro and Jia Biao export reliably in real time.
Traditional inertial measuring unit information generally adopts after light-coupled isolation, directly give missile-borne computer pulse technique circuit and carry out step-by-step counting, owing to not carrying out configurable digital filtering after light-coupled isolation, sampling period is fixed, cannot be configured as required, adopt the modes such as each sampling period reading zero clearing, the accuracy of its counting and the flexibility of application and adaptability are very restricted.
Summary of the invention
The technical problem that the present invention solves is: overcome the deficiencies in the prior art, a kind of in real time reliable admission inertial measuring unit information system is provided, has utilized digital filtering technique, realized the sampling period configurable, sampling period reading zero clearing mode is configurable etc., has improved reliability, adaptability.
Technical scheme of the present invention is: a kind of reliable admission inertial measuring unit information system in real time, comprises light-coupled isolation module, digital filtering module, counting and dump block, data latch module; Light-coupled isolation module carries out, after effectively isolation and shaping, pulse signal being delivered to digital filtering module to the pulse signal of inertial measuring unit output; Digital filtering module, according to the feature of pulse signal, filters the interference signal that is less than 3 sampling clock cycles in pulse signal, and the pulse signal after processing is delivered to counting and dump block; After system power-up starts, counting and dump block start to carry out the counting of pulse signal and store count value, and the reset signal that counting and dump block are sent according to external computer system simultaneously, periodically to count value zero clearing; Data latch module, according to default control cycle, is latched in the count value in counting and dump block in data register, and counting and dump block produce interrupt signal simultaneously; Outside missile-borne computer is received after interrupt signal, reads the count value that is latched in data register, completes the admission of inertial measuring unit data.
In described data latch module, default control cycle is 5ms or 10ms.
The present invention's advantage is compared with prior art:
1) adopt digital filtering technique, can be according to the pulse signal feature of inertial measuring unit information output, effective filtering interference signals;
2) adopt the separately design of counter and latch, when missile-borne computer is read count results, do not affect counter and continue, avoided occurring when counter rollover, missile-borne computer is reading simultaneously, causes the inaccurate situation of reading;
3) adopt configurable mode of sampling period, and the mode that each sampling period reading zero clearing and two kinds of patterns of not zero clearing of stored counts also can configure, can be applied to flexibly guided missile or the rocket control system in different guidance cycles, there is very high flexibility and applicability;
4) interrupt signal of the latch signal of counter and notice missile-borne computer reading is same signal, and minimizing system to greatest extent receives the error of missile-borne computer data, guarantees that reading is to approach current state most.
Accompanying drawing explanation
Fig. 1 is the present invention's reliable admission inertial measuring unit information system composition schematic diagram in real time.
Embodiment
According to technical scheme, the specific embodiment of the invention is as follows, as shown in Figure 1.
1. inertial measuring unit output of pulse signal
Pulse signal is the 6 passage 12 road pulse signals (comprising positive and negative signal) from inertial measuring unit output.Inertial measuring unit output pulse signal is random, and maximum output frequency is 800KHz, and its output form is identical, and each passage has positive and negative two-way output, and output pulse is negative pulse.
2. light-coupled isolation module
6 passage 12 road pulse signals are through optical coupling isolation circuit.Choose the chip that input characteristics meets 1MHz, carry out light-coupled isolation, the output pulse signal of optocoupler is again through delivering to digital filtering module again after Schmidt trigger shaping.
3. digital filtering module
According to the feature of inertial measuring unit output pulse signal and employing clock frequency ，Dui 12 road pulse signals, carry out digital filtering.Be specially: by synchronised clock, 6 road positive pulse signals being carried out to continuous sampling, when continuous sampling to 3 ' 1 ' state, think that signal jumps to state ' 1 ' by state ' 0 ', is useful signal; If continuous sampling ' 1 ' state is less than 3, think that signal is invalid signals.In like manner, by synchronised clock, 6 tunnel undersuings being carried out to continuous sampling, when continuous sampling to 3 ' 0 ' state, think that signal jumps to state ' 0 ' by state ' 1 ', is useful signal; If continuous sampling ' 0 ' state is less than 3, think that signal is invalid signals.In like this can Ba12 road pulse signal, being less than the interference signal in 3 sampling clock cycles filters.
4. signal-count and dump block
Signal-count and dump block have counting and zero clearing two parts function.Counter module detects the effective positive pulse signal of being brought by digital filtering module and jumps to state ' 1 ' by state ' 0 ', or undersuing jumps to state ' 0 ' by state ' 1 ', and count value adds ' 1 '.Dump block, computer can pass through reset signal, the value of counter, is clearly " 00000000 ", due to the existence of reset signal, can realize each sampling period reading zero clearing and two kinds of patterns of not zero clearing of stored counts.
5. data latch module
By latch signal the value of counter real-time lock the latch register of 32, interrupt signal is sent into processor simultaneously, real-time informing processor Ba12 road step-by-step counting data are read away.Latch signal is produced by an independent control module, and the cycle of latch signal can dynamically arrange as required, can meet the demand in different guidance cycles.
The content not being described in detail in specification of the present invention belongs to professional and technical personnel in the field's known technology.
Claims (2)
1. reliably enroll in real time an inertial measuring unit information system, it is characterized in that: comprise light-coupled isolation module, digital filtering module, counting and dump block, data latch module; Light-coupled isolation module carries out, after effectively isolation and shaping, pulse signal being delivered to digital filtering module to the pulse signal of inertial measuring unit output; Digital filtering module, according to the feature of pulse signal, filters the interference signal that is less than 3 sampling clock cycles in pulse signal, and the pulse signal after processing is delivered to counting and dump block; After system power-up starts, counting and dump block start to carry out the counting of pulse signal and store count value, and the reset signal that counting and dump block are sent according to external computer system simultaneously, periodically to count value zero clearing; Data latch module, according to default control cycle, is latched in the count value in counting and dump block in data register, and counting and dump block produce interrupt signal simultaneously; Outside missile-borne computer is received after interrupt signal, reads the count value that is latched in data register, completes the admission of inertial measuring unit data.
2. a kind of reliable admission inertial measuring unit information system in real time according to claim 1, is characterized in that: in described data latch module, default control cycle is 5ms or 10ms.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310300713.5A CN103532527A (en) | 2013-07-15 | 2013-07-15 | Real-time and reliable inertia measuring device information recording system |
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| CN201310300713.5A CN103532527A (en) | 2013-07-15 | 2013-07-15 | Real-time and reliable inertia measuring device information recording system |
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Citations (4)
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| CN201181848Y (en) * | 2008-04-28 | 2009-01-14 | 天津市津开电气有限公司 | Filter device of intelligent dynamic reactive-load compensation thyristor |
| CN101807053A (en) * | 2010-02-23 | 2010-08-18 | 浙江省新昌县康立电子有限公司 | Structure of multi-channel high-speed pulse counting for industrial control touch screen |
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2013
- 2013-07-15 CN CN201310300713.5A patent/CN103532527A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4859986A (en) * | 1987-09-24 | 1989-08-22 | Auken John A Van | Object touchdown and net contact detection systems and game apparatus employing same |
| CN2757310Y (en) * | 2004-08-03 | 2006-02-08 | 东南大学 | Mixed power electronic breaker observe and control device |
| CN201181848Y (en) * | 2008-04-28 | 2009-01-14 | 天津市津开电气有限公司 | Filter device of intelligent dynamic reactive-load compensation thyristor |
| CN101807053A (en) * | 2010-02-23 | 2010-08-18 | 浙江省新昌县康立电子有限公司 | Structure of multi-channel high-speed pulse counting for industrial control touch screen |
Non-Patent Citations (1)
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| 杨甘霖等: ""基于CPCI总线的运载火箭脉冲信号多路采集卡"", 《兵工自动化》 * |
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Application publication date: 20140122 |