CN105549042A - Multi-sensor auxiliary satellite signal capturing apparatus and method - Google Patents
Multi-sensor auxiliary satellite signal capturing apparatus and method Download PDFInfo
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- CN105549042A CN105549042A CN201610008808.3A CN201610008808A CN105549042A CN 105549042 A CN105549042 A CN 105549042A CN 201610008808 A CN201610008808 A CN 201610008808A CN 105549042 A CN105549042 A CN 105549042A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
- G01S19/26—Acquisition or tracking or demodulation of signals transmitted by the system involving a sensor measurement for aiding acquisition or tracking
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- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Computer Networks & Wireless Communication (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
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Abstract
The invention discloses a multi-sensor auxiliary satellite signal capturing apparatus and method. Under the condition that a main power supply of a receiver fails, a backup power supply drives a real-time clock to maintain time continuity, at the same time, the temperature of a surrounding environment is monitored by use of a temperature sensor and the shock of the receiver is monitored by use of an acceleration transducer. When the receiver is thermally started again, a search strategy for satellite signals is determined according to change of the temperature and the shock. According to the invention, abnormal conditions of the real-time clock can be detected by use of the sensors so that different search strategies can be employed during thermal start, and the receiver can be positioned more stably and rapidly.
Description
Technical field
The invention belongs to field of satellite navigation, particularly relate to the apparatus and method of multisensor secondary satellite signal capture.
Background technology
The typical workflow of satellite navigation receiver comprises: capturing satellite signal, and demodulation telegraph text data calculates and exports customer location.For gps system, whole process need about 32 seconds, when being in the complex environments such as city, this process required time is longer.
It is comparatively large that satellite navigation receiver runs required power consumption continuously, and user's not necessarily consecutive tracking.After user completes location, close receiver, when again opening receiver in the short time, the object reducing start-up time can be reached, i.e. so-called warm start by the information (as ephemeris, time, positioning result) of preserving location last time.
Ephemeris in locating information and positioning result can be kept in FLASH, but the time needs to keep running by real-time clock (RTC), thus directly can obtain the correct time in start moment when again starting shooting.When primary power cuts out, real-time clock still needs to keep running, so real-time clock is driven by backup battery.In addition, wanting counting also needs crystal oscillator to provide clock signal.
The frequency of crystal oscillator is very large by the impact of ambient temperature and vibration.If namely during receiver primary power source de-energizes, the crystal oscillator variation of ambient temperature of real-time clock is very large, then crystal oscillator frequency can change, and cause clock time too fast or excessively slow, time when again starting shooting is inaccurate.If now still think, the time is accurately, then can cause auxiliary data mistake, makes capture time longer on the contrary.
But real-time clock self is whether can not detect its time kept accurate, so need other sensors to carry out auxiliary its judge the reliability of time.
Therefore, those skilled in the art is devoted to the apparatus and method developing a kind of multisensor secondary satellite signal capture, makes after receiver primary power source de-energizes, ensures that system time is not lost, does not change.
Summary of the invention
Because the above-mentioned defect of prior art, technical matters to be solved by this invention is after receiver primary power source de-energizes, the problem that system time is lost or changed.
For achieving the above object, the invention provides a kind of device of multisensor secondary satellite signal capture, comprise satellite navigation receiver, host-processor, temperature sensor, acceleration transducer; Described satellite navigation receiver comprises receiver crystal oscillator and backup battery territory, and described backup battery territory comprises reserce cell, real-time clock and backup crystal oscillator; Satellite navigation receiver closes primary power when not needing location, and kept the operation of real-time clock (RTC) by backup battery territory, real-time clock is driven by crystal oscillator; Temperature sensor is configured to the change of monitoring receiver environment temperature and provides temperature to indicate, and acceleration transducer is configured to the acceleration of monitoring receiver and provides vibrations instruction; When satellite navigation receiver is configured to warm start, satellite navigation receiver reads the time of real-time clock, read temperature instruction, vibrations instruction, the error of satellite navigation receiver determination real-time clock, then uses searching method or extensive search method among a small circle to catch satellite-signal.
Further, described real-time clock, when primary power cuts out, is run by backup battery territory, retention time continuous.
Further, when primary power cuts out, described temperature sensor and described acceleration transducer are configured to the monitoring still kept environment temperature and acceleration.
Further, the change of described monitors temperature, with the temperature T of primary power close moment
0for benchmark, when temperature is higher or lower than T
0put temperature during certain limit and be designated as 1.
Further, the change of described acceleration transducer monitoring acceleration is initial with primary power close moment, when the change of acceleration shows that receiver is subject to comparatively big bang tense marker vibrations and is designated as 1.
Further, when described satellite navigation receiver is started shooting again, detected temperatures instruction and vibrations instruction, if be all 0, use searching method capturing satellite signal among a small circle; Otherwise, use large-scale searching method capturing satellite signal.
Further, described searching method is among a small circle search of satellite signals on less code phase and Doppler spread.
Further, described large-scale searching method is search of satellite signals on larger code phase and Doppler spread.
Further, the value of described temperature instruction or acceleration instruction is stored on the internal memory of satellite navigation receiver.
Present invention also offers a kind of method of multisensor secondary satellite signal capture, comprise the following steps:
The first step 201, reads the value of temperature mark Tflag;
Second step 202, reads the value of acceleration sign A flag;
3rd step 203, judges whether Tflag and Aflag equals 0 simultaneously; If both are 0 simultaneously, turn to the 4th step 204; If any one is not 0 in both, turn to the 5th step 205;
4th step 204, centered by the satellite-signal code phase of this time prediction and Doppler, adopts less hunting zone and longer capturing satellite signal search time;
5th step 205, centered by the satellite-signal code phase of this time prediction and Doppler, adopts larger hunting zone and shorter capturing satellite signal search time.
The object of the invention is to overcome the deficiencies in the prior art, a kind of method and apparatus of multisensor secondary satellite signal capture is provided.The abnormal conditions of real-time clock can be detected, thus when warm start, according to the accuracy of temporal information, use different search patterns, make the location of receiver more sane and quick.
The present invention monitors receiver with temperature sensor and acceleration transducer, thus reaches the object of above-mentioned monitoring real-time clock reliability.
In receiver primary power source de-energizes situation, drive real-time clock and crystal oscillator by backup battery.Crystal oscillator runs according to certain frequency, makes the real-time clock retention time.In addition, the temperature of the temperature sensor monitors surrounding environment in system, with the temperature in receiver shutdown moment for benchmark, when ambient temperature exceedes benchmark certain limit, is set to 1 by " temperature mark ".The dynamic of acceleration transducer monitoring receiver, at short notice, shake acutely, repeatedly, thinks that receiver experienced by larger vibrations to acceleration, and " vibrations mark " is put 1.
When receiver starts (warm start) again, first read " temperature mark " and " vibrations mark ", if both 0, illustrate during primary power source de-energizes, receiver environment temperature does not have large change, do not experience larger vibrations, and then illustrate that the crystal oscillator frequency of real-time clock does not have large change, so can determine that the time of now real-time clock is more accurately yet; If there is any one to be 1 in both, illustrate during primary power source de-energizes, receiver environment temperature has had large change or has experienced larger vibrations, and then illustrates that the crystal oscillator frequency of real-time clock produces larger change, so can determine that the time of now real-time clock is not too accurately.
If judge that the time of real-time clock is accurately, so utilize this time can the code phase of Accurate Prediction satellite and Doppler, centered by this predicted value, carry out code acquisition satellite-signal a less scope, can to realize fast and high sensitivity is caught.
If judge that the time of real-time clock is inaccurate, so utilize code phase and the Doppler of this time prediction satellite, centered by this predicted value, code acquisition satellite-signal is carried out to a larger scope, prevents from missing satellite-signal.
Advantage of the present invention is: during receiver primary power source de-energizes, utilizes temperature sensor and the crystal oscillator of acceleration transducer to real-time clock to monitor.During warm start, indicated by detected temperatures and shake instruction, judging the accuracy of present receiving machine real-time clock.Take different searching methods, realize stablizing, catching fast and locate.
Be described further below with reference to the technique effect of accompanying drawing to design of the present invention, concrete structure and generation, to understand object of the present invention, characteristic sum effect fully.
Accompanying drawing explanation
Fig. 1 is the sensor of a preferred embodiment of the present invention and the unitized construction schematic diagram of satellite navigation receiver;
Fig. 2 is that process flow diagram is caught in the receiver warm start of a preferred embodiment of the present invention.
Embodiment
Below in conjunction with drawings and Examples, the invention will be further described.
Fig. 1 is the unitized construction of sensor and satellite navigation receiver.As shown in Figure 1,101 is systems that sensor and satellite navigation receiver combine, and mainly comprises satellite navigation receiver 103, the processor 102 of main frame and multiple sensor.Sensor comprises temperature sensor 110, acceleration transducer 111.
During normal work, satellite navigation receiver 103 provides power supply by primary power 105, provides clock by receiver crystal oscillator 104, and now satellite navigation receiver 103 can normal capturing satellite signal export positioning result.The each location of satellite navigation receiver also can obtain UTC time accurately simultaneously, and this time is inserted real-time clock 108, thus makes the time clock of real-time clock 108 and UTC time unifying accurately.
When user does not temporarily need location, close primary power 105, receiver crystal oscillator 104 quits work, and now the main functional modules of satellite navigation receiver 103 all quits work, cannot capturing satellite signal, can not locate.But the backup battery territory 106 of satellite navigation receiver still can work, this is because this territory can provide power supply by reserce cell 107, provide clock by crystal oscillator 109, real-time clock 108 still can keep timing.
For whole system 101, temperature sensor 110 and acceleration transducer 111 in running order all the time, in order to temperature and the acceleration of monitoring system.Temperature Warning Mark 112 and vibrations Warning Mark 113 are all registers.When user's temporary close location, while primary power 105 cuts out, host-processor 102 records the temperature value T of temperature sensor 110
0, and start the data of monitor temperature sensor 110 and acceleration transducer 111:
1) if the temperature data that temperature sensor 110 exports departs from temperature T
0certain scope (this scope is designed according to demand by designer), then think that environment temperature plays larger change, and the value of temperature instruction 112 is put 1.
2) if acceleration transducer 111 export acceleration information at short notice, shake acutely, repeatedly, then think that system receives larger vibrations, by vibrations instruction 113 value put 1.
When user needs again to locate, start satellite navigation receiver, 112 can be indicated to pass to satellite navigation receiver 103 with the value of vibrations instruction 113 by interface temperature by the processor 102 of main frame.Also can directly read by satellite navigation receiver 103 value that temperature indicates 112 and vibrations instruction 113.Then satellite navigation receiver takes different harvesting policies.
Fig. 2 is that process flow diagram is caught in receiver warm start.As shown in Figure 2, (warm start) is again started afterwards at satellite navigation receiver:
The first step 201, reads the value of temperature mark Tflag.
Second step 202, reads the value of acceleration sign A flag.
3rd step 203, judges whether Tflag and Aflag equals 0 simultaneously.If both are 0 simultaneously, illustrate real-time clock 108 retention time during this period of time in, the temperature of system does not have large change, larger vibrations are not subject to yet, then the frequency of crystal oscillator 109 is more stable, so the time that real-time clock 108 keeps also is reliable, turn to the 4th step 204.
If any one is not 0 in both, illustrate real-time clock 108 retention time during this period of time in, the temperature of system has had large change, or is subject to larger vibrations.No matter be which kind of situation, the frequency of crystal oscillator 109 all can be affected and unstable, so the time that real-time clock 108 keeps also can be affected and insecure, turns to the 5th step 205.
4th step 204, has determined that the time that real-time clock 108 keeps is reliable, so centered by the satellite-signal code phase of this time prediction and Doppler, adopts less hunting zone and longer capturing satellite signal search time.
5th step 205, has determined that the time that real-time clock 108 keeps is insecure, so centered by the satellite-signal code phase of this time prediction and Doppler, adopts larger hunting zone and shorter capturing satellite signal search time.
More than describe preferred embodiment of the present invention in detail.Should be appreciated that the ordinary skill of this area just design according to the present invention can make many modifications and variations without the need to creative work.Therefore, all technician in the art, all should by the determined protection domain of claims under this invention's idea on the basis of existing technology by the available technical scheme of logical analysis, reasoning, or a limited experiment.
Claims (10)
1. a device for multisensor secondary satellite signal capture, is characterized in that, comprises satellite navigation receiver, host-processor, temperature sensor, acceleration transducer; Described satellite navigation receiver comprises receiver crystal oscillator and backup battery territory, and described backup battery territory comprises reserce cell, real-time clock and backup crystal oscillator; Satellite navigation receiver closes primary power when not needing location, and kept the operation of real-time clock (RTC) by backup battery territory, real-time clock is driven by crystal oscillator; Temperature sensor is configured to the change of monitoring receiver environment temperature and provides temperature to indicate, and acceleration transducer is configured to the acceleration of monitoring receiver and provides vibrations instruction; When satellite navigation receiver is configured to warm start, satellite navigation receiver reads the time of real-time clock, read temperature instruction, vibrations instruction, the error of satellite navigation receiver determination real-time clock, then uses searching method or extensive search method among a small circle to catch satellite-signal.
2. the device of multisensor secondary satellite signal capture as claimed in claim 1, it is characterized in that, described real-time clock, when primary power cuts out, is run by backup battery territory, retention time continuous.
3. the device of multisensor secondary satellite signal capture as claimed in claim 1, it is characterized in that, when primary power cuts out, described temperature sensor and described acceleration transducer are configured to the monitoring still kept environment temperature and acceleration.
4. the device of multisensor secondary satellite signal capture as claimed in claim 1, is characterized in that, the change of described monitors temperature, with the temperature T of primary power close moment
0for benchmark, when temperature is higher or lower than T
0put temperature during certain limit and be designated as 1.
5. the device of multisensor secondary satellite signal capture as claimed in claim 1, it is characterized in that, the change of described acceleration transducer monitoring acceleration is initial with primary power close moment, when the change of acceleration shows that receiver is subject to comparatively big bang tense marker vibrations and is designated as 1.
6. the device of multisensor secondary satellite signal capture as claimed in claim 1, is characterized in that, when described satellite navigation receiver is started shooting again, detected temperatures instruction and vibrations instruction, if be all 0, use searching method capturing satellite signal among a small circle; Otherwise, use large-scale searching method capturing satellite signal.
7. the device of multisensor secondary satellite signal capture as claimed in claim 1, it is characterized in that, described searching method is among a small circle search of satellite signals on less code phase and Doppler spread.
8. the device of multisensor secondary satellite signal capture as claimed in claim 1, it is characterized in that, described large-scale searching method is search of satellite signals on larger code phase and Doppler spread.
9. the device of multisensor secondary satellite signal capture as claimed in claim 1, is characterized in that, the value of described temperature instruction or acceleration instruction is stored on the internal memory of satellite navigation receiver.
10. a method for multisensor secondary satellite signal capture, is characterized in that, comprises the following steps:
The first step 201, reads the value of temperature mark Tflag;
Second step 202, reads the value of acceleration sign A flag;
3rd step 203, judges whether Tflag and Aflag equals 0 simultaneously; If both are 0 simultaneously, turn to the 4th step 204; If any one is not 0 in both, turn to the 5th step 205;
4th step 204, centered by the satellite-signal code phase of this time prediction and Doppler, adopts less hunting zone and longer capturing satellite signal search time;
5th step 205, centered by the satellite-signal code phase of this time prediction and Doppler, adopts larger hunting zone and shorter capturing satellite signal search time.
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| CN201610008808.3A CN105549042B (en) | 2016-01-05 | 2016-01-05 | A kind of apparatus and method of multisensor secondary satellite signal capture |
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| CN201610008808.3A CN105549042B (en) | 2016-01-05 | 2016-01-05 | A kind of apparatus and method of multisensor secondary satellite signal capture |
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Citations (4)
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| CN103605141A (en) * | 2013-11-27 | 2014-02-26 | 中国科学院嘉兴微电子与系统工程中心 | Fast capturing method for GNSS code |
| US20140062770A1 (en) * | 2012-09-05 | 2014-03-06 | O2Micro Inc. | Satellite Signal Receiver and Method for Updating Ephemeris Information Thereby |
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2016
- 2016-01-05 CN CN201610008808.3A patent/CN105549042B/en active Active
Patent Citations (4)
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|---|---|---|---|---|
| CN101636637A (en) * | 2007-03-23 | 2010-01-27 | 高通股份有限公司 | Multi-sensor data collection and/or processing |
| CN102449436A (en) * | 2009-05-29 | 2012-05-09 | 高通股份有限公司 | Method and apparatus for accurate acquisition of inertial sensor data by compensating the relative processing delays between signal channels |
| US20140062770A1 (en) * | 2012-09-05 | 2014-03-06 | O2Micro Inc. | Satellite Signal Receiver and Method for Updating Ephemeris Information Thereby |
| CN103605141A (en) * | 2013-11-27 | 2014-02-26 | 中国科学院嘉兴微电子与系统工程中心 | Fast capturing method for GNSS code |
Non-Patent Citations (1)
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|---|
| 何文涛 等: "《基于FFT的GPS信号二维大规模并行捕获》", 《电子器件》 * |
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Effective date of registration: 20230710 Address after: 310053 room 1001, innovation building, 3850 Jiangnan Road, high tech (Binjiang), Hangzhou, Zhejiang Patentee after: Hangzhou Zhongke Microelectronics Co.,Ltd. Address before: 314006 Building 2, No. 778, Asia Pacific Road, Jiaxing, Zhejiang Province (Jiaxing Technopole) Patentee before: JIAXING MICROELECTRONICS AND SYSTEM ENGINEERING CENTER, CHINESE ACADEMY OF SCIENCES |
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