JP4285509B2 - POSITIONING DEVICE, POSITIONING DEVICE CONTROL METHOD, AND PROGRAM - Google Patents

Description

The present invention relates to a positioning device that uses radio waves from a transmission source, a positioning device control method, and a program .

Conventionally, a positioning system that measures the current position of a GPS receiver by using, for example, a GPS (Global Positioning System) that is a satellite navigation system has been put into practical use.
This GPS receiver uses radio waves from GPS satellites (hereinafter referred to as satellite radio waves) based on navigation messages (including approximate satellite orbit information: almanac, precision satellite orbit information: ephemeris, etc.) indicating the orbits of GPS satellites. A C / A (Clear and Acquisition or Coarse and Access) code, which is one of pseudo noise codes (hereinafter referred to as PN (Psuedo random noise code) codes), is received. The C / A code is a code that is the basis of positioning.
The GPS receiver specifies the GPS satellite from which the C / A code is transmitted, and, for example, based on the phase (code phase) of the C / A code, receives the GPS satellite and the GPS reception. The distance of the machine (pseudo distance) is calculated. Then, the GPS receiver measures the position of the GPS receiver based on the pseudoranges of three or more GPS satellites and the position of each GPS satellite on the satellite orbit. For example, the C / A code has a bit rate of 1.023 Mbps and the code length is 1,023 chips. Therefore, it can be considered that the C / A code runs side by side at intervals of about 300 kilometers (km), which is the distance traveled by radio waves in 1 millisecond (ms). Therefore, by calculating the number of C / A codes between the GPS satellite and the GPS receiver from the position of the GPS satellite on the satellite orbit and the approximate position of the GPS receiver, the pseudo distance is calculated. Can do. More specifically, one period (1,023 chips) of the C / A code (the integer part of the C / A code) is calculated, and the phase of the C / A code (the fractional part of the C / A code) is calculated. If specified, the pseudo distance can be calculated. Here, the integer part of the C / A code can be estimated if the approximate position of the GPS receiver has a certain accuracy, for example, within 150 km. For this reason, the GPS receiver can calculate the pseudorange by specifying the phase of the C / A code.
The GPS receiver, for example, calculates the correlation between the received C / A code and the replica C / A code generated inside the GPS receiver and integrates the C / A code when the correlation integrated value reaches a certain level. Specify the phase of the code. At this time, the GPS receiver performs correlation processing while shifting the phase and frequency of the replica C / A code.
However, in the case of an indirect wave (hereinafter referred to as “indirect wave”) in which the received satellite radio wave is reflected on a building or the like, the GPS receiver cannot accurately specify the phase of the C / A code. .
On the other hand, a GPS receiver with a communication function holds map data with multipath frequent occurrence area information, determines whether the current position acquired by positioning is a multipath frequent occurrence value range, and further GPS receiver However, if the position of the communication base station in communication is an urban area, a technique for determining whether the area is a multipath frequent occurrence area has been proposed (for example, Patent Document 1).
JP 2001-272450 A

  However, according to the above-described technique, there is a problem that it is necessary to hold map data or to communicate with a communication base station.

Therefore, the present invention determines the bias of the satellite position as a technique for quickly eliminating the multipath and performing the positioning even though there is no need to hold the map data or communicate with the communication base station. It aims at providing the technique to do.

  A first invention for achieving the object is a positioning device that determines a position bias of the SPS satellite based on a satellite signal from an SPS (Satellite Positioning System) satellite and performs positioning based on the determination result. And determining means for determining the position bias of the SPS satellite based on the position of the center of gravity of the figure connecting the position coordinates of the strong signal satellites in which the received satellite signal is a predetermined strong electric field signal among the SPS satellites. It is a positioning device provided.

  According to another aspect of the present invention, there is provided a method for controlling a positioning device that determines a position bias of the SPS satellite based on a satellite signal from the SPS satellite and performs positioning based on a determination result. The positioning device control method for determining the position bias of the SPS satellite based on the position of the center of gravity of the figure obtained by connecting the position coordinates of the strong signal satellite in which the received satellite signal is a predetermined strong electric field signal is configured. Also good.

  According to another aspect of the present invention, there is provided a program for causing a computer built in a positioning device to determine a positional deviation of the SPS satellite based on a satellite signal from the SPS satellite and performing positioning based on the determination result. In the computer, the position deviation of the SPS satellite is determined based on the position of the center of gravity of the figure connecting the position coordinates of the strong signal satellites of which the received satellite signal is a predetermined strong electric field signal. It is good also as comprising the program for making it determine.

Preferred embodiments of the present invention will be described below in detail with reference to the accompanying drawings.
The embodiments described below are preferred specific examples of the present invention, and thus various technically preferable limitations are given. However, the scope of the present invention is particularly limited in the following description. Unless otherwise stated, the present invention is not limited to these embodiments.

(Embodiment which is a premise of the present application)
First, an embodiment as a premise of the present application will be described.
FIG. 1 is a schematic diagram illustrating a terminal 20 and the like according to the embodiment of this invention.
As shown in FIG. 1, the terminal 20 is an SPS satellite such as GPS satellites 12a, 12b, 12c, 12d, 12e, 12f, 12g, and 12h, and radio waves S1, S2, S3, S4, S5, S6, and S7. And S8 can be received. The SPS satellite is not limited to a GPS satellite.
Various codes (codes) are carried on the radio wave S1 and the like. One of them is the C / A code Sca. The C / A code Sca is a signal having a bit rate of 1.023 Mbps and a bit length of 1,023 bits (= 1 msec). The C / A code Sca is composed of 1,023 chips. The terminal 20 is an example of a positioning device that measures the current position, and receives the C / A code and measures the current position. This C / A code Sca is an example of a satellite signal.

Moreover, there are almanac Sal and ephemeris Seh as information put on the radio wave S1 and the like. Almanac Sal is information indicating the approximate satellite orbit of all the GPS satellites 12a and the like, and Ephemeris Seh is information indicating the precise satellite orbit of each of the GPS satellites 12a and the like. Almanac Sal and Ephemeris Seh are collectively called navigation messages.
The terminal 20 can determine the current position by specifying the phases of C / A codes from, for example, three or more different GPS satellites 12a.

FIG. 2 is a conceptual diagram illustrating an example of a positioning method.
As shown in FIG. 2, for example, it can be considered that C / A codes are continuously arranged between the GPS satellite 12 a and the terminal 20. Since the distance between the GPS satellite 12a and the terminal 20 is not necessarily an integer multiple of the length of the C / A code (300 kilometers (km)), the code fractional part C / Aa exists. That is, between the GPS satellite 12a and the terminal 20, there are a part that is an integral multiple of the C / A code and a fractional part. The total length of the integral multiple of the C / A code and the fractional part is the pseudorange. The terminal 20 performs positioning using pseudoranges for three or more GPS satellites 12a and the like.
In this specification, the fractional part C / Aa of the C / A code is called a code phase. For example, the code phase can be indicated by the number of the 1023 chip of the C / A code, or can be indicated in terms of distance. When calculating the pseudo distance, the code phase is converted into a distance.

  The position of the GPS satellite 12a in the orbit can be calculated using the ephemeris Seh. For example, if a distance between the position of the GPS satellite 12a in the orbit and an initial position P0 described later is calculated, a portion that is an integral multiple of the C / A code can be specified. Since the length of the C / A code is 300 kilometers (km), the position error of the initial position P0 needs to be within 150 kilometers (km).

Then, as shown in FIG. 2, the correlation process is performed while moving the phase of the replica C / A code in the direction of the arrow X1, for example. At this time, the terminal 20 performs correlation processing while changing the synchronization frequency. This correlation process includes a coherent process and an incoherent process which will be described later.
The phase at which the correlation integrated value is maximized is the code fraction C / Aa.

FIG. 3 is an explanatory diagram of the correlation processing.
Coherent is a process for correlating the C / A code received by the terminal 20 and the replica C / A code. The replica C / A code is a code generated by the terminal 20.
For example, as shown in FIG. 3, if the coherent time is 5 milliseconds (msec), the correlation value between the C / A code and the replica C / A code synchronously integrated in the time of 5 milliseconds (msec) Calculate .
Incoherent is a process of accumulating correlation values of coherent results , and the accumulated correlation value is referred to as a correlation accumulated value (incoherent value) .

The code phase CP1 corresponding to the maximum correlation integrated value Pmax is the code phase of the replica C / A code, that is, the code phase of the C / A code.
Then, for example, the terminal 20 sets the correlation integrated value having the smaller correlation integrated value in the code phase separated by a half chip from the code phase CP1 as the noise integrated correlation value Pnoise.
The terminal 20 defines the value obtained by dividing the difference between Pmax and Pnoise by Pmax as the signal strength XPR.

When a signal having a specific electric field strength is input, the calculated values of Pmax and signal strength XPR can be obtained by experiments. Therefore, the terminal 20 can calculate the electric field strength such as the radio wave S1 received by the terminal 20 from Pmax and the signal strength XPR.
The electric field strength means the electric field strength of the radio wave S1 or the like that reaches the antenna (not shown) of the terminal 20.

As the electric field strength increases, the code phase can be specified even if the incoherent time is short. The code phase is highly accurate.
On the other hand, when the electric field strength is weak, the code phase cannot be specified unless the incoherent time is increased. And the accuracy of the code phase is lower than when the electric field strength is high.

(Main hardware configuration of terminal 20)
FIG. 4 is a schematic diagram illustrating a main hardware configuration of the terminal 20.
As illustrated in FIG. 4 , the terminal 20 includes a computer, and the computer includes a bus 22. A CPU (Central Processing Unit) 24, a storage device 26, and the like are connected to the bus 22. The storage device 26 is, for example, a RAM (Random Access Memory), a ROM (Read Only Memory), or the like.
In addition, an input device 28, a power supply device 30, a GPS device 32, a display device 34, a communication device 36, and a clock 38 are connected to the bus 22.

(About main software configuration of terminal 20)
FIG. 5 is a schematic diagram showing a main software configuration of the terminal 20.
As shown in FIG. 5 , the terminal 20 includes a control unit 100 that controls each unit, a GPS unit 102 that corresponds to the GPS device 32 in FIG. 4 , a clock unit 104 that corresponds to the clock 38, and the like.
The terminal 20 also includes a first storage unit 110 that stores various programs and a second storage unit 150 that stores various information.

As illustrated in FIG. 5 , the terminal 20 stores a navigation message 152 in the second storage unit 150. The navigation message 152 includes an almanac 152a and an ephemeris 152b.
The terminal 20 uses the almanac 152a and the ephemeris 152b for positioning.

As illustrated in FIG. 5 , the terminal 20 stores initial position information 154 in the second storage unit 150. The initial position P0 is, for example, the previous positioning position.

As shown in FIG. 5 , the terminal 20 stores a satellite signal reception program 112 in the first storage unit 110. The satellite signal reception program 112 is a program for the control unit 100 to receive the radio wave S1 and the like. The control unit 100 refers to the almanac 152a to determine the GPS satellites 12a that can be observed at the current time. Then, the control unit 100 refers to the ephemeris 152b, calculates the current position on the orbit of the GPS satellite 12a, etc., calculates the Doppler shift of the radio wave S1, etc., and estimates the reception frequency. And the signal S1 etc. from GPS satellite 12a etc. are received using the estimated receiving frequency. At this time, the reference self-position is, for example, the initial position P0.

FIG. 6 is an explanatory diagram of the satellite signal reception program 112.
As shown in FIG. 6 , the satellite signal reception program 112 includes a program for executing the search mode M1, the first tracking mode M2, and the second tracking mode M3.
The search mode M1 is a mode for capturing the radio wave S1 and the like. For this reason, the search mode M1 searches a wide frequency range of, for example, 3 kilohertz (kHz).

The first tracking mode M2 (hereinafter referred to as “mode M2”) is a positioning mode in which tracking (tracking) is performed after the radio wave S1 or the like is captured. Mode M2 is an operation mode (positioning mode) when the signal strength (electric field strength) is strong. The case where the signal intensity is strong is, for example, minus (−) 139 dBm or more .

The second tracking mode M3 (hereinafter referred to as “mode M3”) is a positioning mode in which tracking (tracking) is performed after the radio wave S1 or the like is captured. Mode M3 is an operation mode (positioning mode) when the signal strength is weak. The case where the signal intensity is weak is, for example, minus (−) 160 dBm or more and less than minus (−) 139 dBm.
The integration time (incoherent time) t2 in the mode M3 is, for example, 2 seconds.

The integration time t2 in the mode M3 is defined to be longer than the integration time t1 in the mode M2.
As described above, the terminal 20 has a plurality of positioning modes with different operating signal strengths. Modes M2 and M3 are examples of positioning modes. The mode M2 is also an example of the first positioning mode. The mode M3 is also an example of the second positioning mode.

Based on the satellite signal reception program 112, the control unit 100 calculates a measurement including the code phase, signal strength, elevation angle, and azimuth angle of the received C / A code.
The measurement calculation program 114 and the control unit 100 are an example of an azimuth calculation unit.
The control unit 100 calculates the measurement while performing tracking in the mode M2 or M3.
The control unit 100 stores measurement information 156 indicating the measurement in the second storage unit 150.

FIG. 7 is a diagram illustrating an example of the measurement information 156.
As shown in FIG. 7 , the measurement information 156 includes satellite numbers 1 to 8. In the present embodiment, it is assumed that radio waves S1 to S8 are received from GPS satellites 12a to 12h.
Satellite numbers 1 to 8 correspond to GPS satellites 12a to 12h, respectively.

  The measurement information 156 also includes a code phase. The code phase is different for each GPS satellite 12a and the like.

The measurement information 156 also includes Pmax, Pnoise and XPR.
The measurement information 156 also includes an elevation angle and an azimuth angle. The elevation angle and the azimuth angle indicate the positions of the GPS satellites 12a and the like with the initial position P0 as a reference by the elevation angle and the azimuth angle. The control unit 100 calculates the original current position on the orbit of each GPS satellite 12a or the like by the ephemeris 152b, and calculates the elevation angle and azimuth angle of each GPS satellite 12a or the like with the initial position P0 as a reference.

Measurement information 156 also includes modes M2 and M3.
For example, when the radio wave S1 from the GPS satellite 12a is received in the mode M2, the satellite number 1 corresponds to the mode M2. When the radio wave S5 from the GPS satellite 12e is received in the mode M3, the mode M3 corresponds to the satellite number 5.
Therefore, for example, when the radio wave S1 from the GPS satellite 12a is received in the mode M2 in the mode M2, the GPS satellite 12a is also referred to as a “mode M2 satellite”.

Measurement information 156 also includes field strength. The control unit 100 calculates the electric field strength from Pmax or XPR. The electric field strength differs for each GPS satellite 12a and the like.
For example, v1 is minus (−) 159 dBm and v2 is minus (−) 140 dBm.
Of the information included in the measurement information 156, the code phase, Pmax, Pnoise, XPR, elevation angle, and azimuth angle are referred to as measurement.

As illustrated in FIG. 5 , the terminal 20 stores an environment determination program 114 in the first storage unit 110. The environment determination program 114 is a program for the control unit 100 to determine the reception environment of the C / A code based on the reception state of the C / A code from the plurality of GPS satellites 12a and the like. The environment determination program 114 and the control unit 100 are examples of reception environment determination means. As will be described later, the reception environment includes a multipath environment in which multipath is likely to occur.

As illustrated in FIG. 5 , the terminal 20 stores a positioning program 116 in the first storage unit 110. The positioning program 116 is a program for the control unit 100 to perform positioning using measurement based on the reception environment. The positioning program 116 and the control unit 100 are examples of positioning means.

FIG. 8 is an explanatory diagram of the environment determination program 114.
FIG. 9 is an explanatory diagram of the environment determination program 114 and the positioning program 116.
As shown in FIG. 8 , the control unit 100 classifies the electric field strength v1 and the like (see FIG. 7 ) into a strong electric field and a weak electric field based on the environment determination program 114. The strong electric field is the electric field strength at which the mode M2 operates. The weak electric field is the electric field strength at which the mode M3 operates.
Further, the control unit 100 divides the strong electric field into a first strong electric field, a second strong electric field, and a third strong electric field.
The first strong electric field has an electric field strength of α1 or more and less than α2. The second strong electric field is an electric field strength of α2 or more and less than α3. The third strong electric field has an electric field strength of α3 or higher. α1, α2, and α3 are threshold values of electric field strength, and α2 is larger than α1 and α3 is larger than α2. α1 is, for example, minus (−) 140. α2 is, for example, minus (−) 130. α3 is, for example, minus (−) 124.

In addition, the control unit 100 divides the weak electric field into a first weak electric field and a second weak electric field.
The first weak electric field has an electric field strength of β1 or more and less than β2. The second weak electric field has an electric field strength of β2 or more and less than β3. β1, β2, and β3 are electric field intensity threshold values, and β2 is larger than β1 and β3 is larger than β2. β1 is, for example, minus (−) 160 dBm. β2 is, for example, minus (−) 150 dBm. β3 is, for example, minus (−) 140 dBm.

As shown in FIG. 9 , based on the environment determination program 114, the control unit 100 includes eight or more M2 satellites with the third strong electric field and GPS satellites other than the M2 satellite with the third strong electric field. If not, it is determined that the environment is the first environment (OpenSky). For example, the expression “8 satellites of M2” is used to mean 8 GPS satellites tracked in mode M2.

10 to 15 are explanatory diagrams of the reception environment.
For example, as shown in FIG. 10A , the first environment is an environment in which an obstacle such as the radio wave S1 does not exist around the terminal 20. For this reason, there should be no multipath.
As illustrated in FIG. 9, when the control unit 100 determines that the environment is the first environment, the control unit 100 performs positioning using all the calculated GPS satellites 12 a and the like based on the positioning program 116.

As shown in FIG. 9 , based on the environment determination program 114, the control unit 100 determines that the second strong electric field M2, the second strong electric field M2, the M3 satellite, and the M3 satellite coexist. It is determined that the environment (quasi-OpenSky).
For example, as shown in FIG. 10B , the second environment is an environment in which buildings 13A to 13D that may become obstacles such as the radio wave S1 exist around the terminal 20. For this reason, at least signals from the M3 satellite may be multipath.
As illustrated in FIG. 9, when the control unit 100 determines that the environment is the second environment, the control unit 100 performs positioning by excluding the measurement of the M3 satellite based on the positioning program 116. As a result, the positioning accuracy can be improved as compared with the case where the measurement of the M3 satellite is used.

As shown in FIG. 9 , based on the environment determination program 114, the control unit 100 determines that the third strong electric field M2, the second strong electric field M2, the M3 satellite, and the M3 satellite coexist. It is determined that the environment is the first multipath environment.
In the third environment, for example, as shown in FIG. 11 , there are buildings 13A to 13D that may become obstacles such as radio waves S1 around the terminal 20, and a communication base that is a source of noise signals. This is an environment in which the station 14 exists. For this reason, not only signals from the M3 satellite but also signals from the M2 satellite may be multipath.
As illustrated in FIG. 9, when the control unit 100 determines that the environment is the third environment, the control unit 100 performs positioning by taking a multipath countermeasure based on the positioning program 116 .

As shown in FIG. 9 , based on the environment determination program 114, the control unit 100 has a case where the M2 satellite with the third strong electric field and the M3 satellite with the second weak electric field coexist and the satellite arrangement is biased. Is determined to be the fourth environment (biased environment). Here, the control unit 100 has the same number or more (in this case, 3 or more), such as when there are 3 or more M2 satellites with the third strong electric field and 4 or more M3 satellites with the second weak electric field. In some cases, it is determined that the M2 satellite having the third strong electric field and the M3 satellite having the second weak electric field coexist. The reason for this determination is as follows.
That is, it is assumed that 6 to 9 GPS satellites can be observed continuously at a specific location. For this reason, there are 3 to 4 satellites with strong signal strength (third strong electric field), and satellites with slightly weaker (second weak electric field) signal strength in the situation where one side is hidden or only the upward direction is visible. This is because it can be assumed that exists.
Fourth environment, for example, as shown in FIG. 12 (a), is an environment in which the satellite constellation is biased to the west. This is because, for example, due to the presence of the building 15, the radio waves S6, S7, and S8 from the GPS satellites 12f, 12g, and 12h do not reach the terminal 20 as direct waves. That is, the fourth environment is also a kind of multipath environment.
When the control unit 100 determines that the environment is the fourth environment, as shown in FIG. 9 , based on the positioning program 116, the GPS satellites 12 f, 12 g and 12 h in the direction opposite to the direction in which the satellites are biased are detected. Position without measuring.

16 , 17, and 18 are explanatory diagrams of determination of a biased environment.
As shown in FIG. 16 (a), the azimuth angle is defined by eight angular regions R1 to R8 formed by equally dividing an angular range of 360 degrees centered on the position of the terminal 20 into, for example, eight regions. Belonging to one. In FIG. 16A, the distance from the center of the circle indicates the elevation angle, and the elevation angle is 90 degrees at the center of the circle and the elevation angle is 0 degrees at the circumference.
Note that, unlike the present embodiment, the angle region is not limited to dividing the 360 degree angle range into eight equal parts, and may be divided into sixteen equal parts, for example.

  And the control part 100 judges whether the satellite of a strong electric field is biased in any angle area | region. A strong electric field satellite is an example of a strong signal satellite. That is, the control unit 100 determines the bias of the plurality of GPS satellites 12a and the like based on the azimuth angle of the strong signal satellite.

As shown in FIG. 16B , for example, the control unit 100 has three strong electric field satellites and three second weak electric field satellites, that is, the number of strong electric field satellites and the second weak electric field. When the number of satellites in the electric field is equal, judgment of bias is started.
Unlike the present embodiment, the control unit 100 is not limited to the case where the number of strong electric field satellites is equal to the number of second weak electric field satellites, for example, the number of strong electric field satellites and the number of second weak electric field satellites. However, when the number is a predetermined number, for example, three or more, determination of bias may be started. In this case, for example, the number of satellites with a strong electric field may be three and the number of satellites with a second weak electric field may be four.

First, as shown in FIG. 16B , the control unit 100 calculates the number of strong electric field satellites in the regions R1, R2, R7, and R8, which are half of the entire angle region. In the example of FIG. 16B, the number of satellites with a strong electric field is three. A region composed of the regions R1, R2, R7, and R8 is referred to as a first semicircular region, and a region composed of the regions R1 and R8 is referred to as a central region.
Subsequently, as illustrated in FIG. 16C , the control unit 100 removes the region R7 from the first semicircular region and adds a region R3 (referred to as a second semicircular region), for example. Calculate the number of satellites. In the example of FIG. 16C, the number of satellites with a strong electric field is three.
Subsequently, as illustrated in FIG. 17A , the control unit 100 removes the region R2 from the first semicircular region and adds a region R6 (referred to as a third semicircular region), for example, in the strong electric field. Calculate the number of satellites. In the example of FIG. 17A, the number of satellites with a strong electric field is three.

Subsequently, as illustrated in FIG. 17B , the control unit 100 removes the region R8 from the second semicircular region (see FIG. 16C ) and adds the region R4 (fourth semicircle), for example . The number of satellites with a strong electric field is calculated. In the example of FIG. 17B, the number of satellites with a strong electric field is one.
Subsequently, as illustrated in FIG. 17C, the control unit 100 removes the region R1 from the fourth semicircular region (see FIG. 17B) and adds the region R5 (fifth semicircle), for example . The number of satellites with a strong electric field is calculated. In the example of FIG. 17C, the number of satellites with a strong electric field is zero.

Subsequently, as illustrated in FIG. 18A , the control unit 100 removes the region R2 from the fifth semicircular region (see FIG. 17C) and adds the region R6 (sixth semicircle), for example . The number of satellites with a strong electric field is calculated. In the example of FIG. 18A, the number of satellites with a strong electric field is zero.
Subsequently, as illustrated in FIG. 18B , the control unit 100 removes the region R3 from the sixth semicircle region (see FIG. 18A ) and adds the region R7 (seventh semicircle), for example . The number of satellites with a strong electric field is calculated. In the example of FIG. 18B, the number of satellites with a strong electric field is zero.
Subsequently, as illustrated in FIG. 18C , the control unit 100 removes the region R4 from the seventh semicircular region (see FIG. 18B) and adds the region R8 (eighth semicircle), for example . The number of satellites with a strong electric field is calculated. In the example of FIG. 18C, the number of satellites with a strong electric field is two.

As described above, the control unit 100 rotates the semicircular region having an angle range of 180 degrees by 45 degrees and calculates the number of satellites with strong electric fields.
And the control part 100 judges that a satellite is biased, when satisfy | filling the conditions that the number of satellites of a strong electric field is equal in three continuous semicircle areas. Here, the control unit 100 determines that the direction of the bias is the direction of the center of the semicircular area at the center of the three semicircular areas.
For example, the first region (see FIG. 16B ), the second region (see FIG. 16C ), and the third region (see FIG. 17A ) are continuous, and the number of satellites in the strong electric field. Are equal. And the center semicircle area | region is a 1st area | region. The direction of the center of the first region is north.
For this reason, the control unit 100 determines that the GPS satellites 12a and the like are biased to the north.
In this example, the first region is an example of a central region, and the second region and the third region are examples of adjacent regions. The condition that the number of satellites with a strong electric field is equal in three consecutive semicircular regions is an example of the first bias condition.

As shown in FIG. 9 , based on the environment determination program 114, the control unit 100 has a case where the M2 satellite with the third strong electric field and the M3 satellite with the second weak electric field coexist and the satellite arrangement is not biased. When the condition that the number of satellites of the strong electric field is equal in the three consecutive semicircular regions is not satisfied, it is determined that the environment is the fifth environment (valley environment). For example, as shown in FIG. 12B , the fifth environment is an environment like a valley formed by the buildings 15 and 16, although the satellite arrangement is not biased. For example, the state in Ginza in Japan. The fifth environment is an environment in which many multipaths are likely to occur. That is, the fifth environment is also a kind of multipath environment.
As shown in FIG. 9, when the control unit 100 determines that the environment is the fifth environment, the control unit 100 excludes the measurement such as the GPS satellite 12a in the obstacle direction based on the positioning program 116, and further, the second weakness The positioning is performed by eliminating the measurement of the M3 satellite in the electric field .

FIG. 19 is an explanatory diagram of determination of the valley environment.
If there are almost the same number of M3 satellites with the third strong electric field and M3 satellites with the second weak electric field, and there is no bias, the elevation angle of the M2 satellite with the third strong electric field is as shown in FIG. The elevation angle is higher than that of the M3 satellite having the second weak electric field. And it has been confirmed by experiment by the inventor of the present invention that the relationship between the electric field strength and the elevation angle is generated in a terrain such as a valley.
For this reason, when there are almost the same number of the M2 satellites with the third strong electric field and the M3 satellites with the second weak electric field, and there is no bias, it can be determined that the valley environment exists.

As illustrated in FIG. 9 , based on the environment determination program 114, the control unit 100 determines that the environment is the sixth environment (second multipath environment) when there are more M3 satellites than M2 satellites.
For example, as shown in FIG. 13 , the sixth environment is an environment in which buildings are crowded, such as buildings 17A to 17E. Alternatively, the sixth environment is an indoor environment with a window. In the sixth environment, the electric field strength is weak and multipath is likely to occur.
As illustrated in FIG. 9, when the control unit 100 determines that the environment is the sixth environment, the control unit 100 performs positioning by taking a multipath countermeasure based on the positioning program 116.

As shown in FIG. 9 , based on the environment determination program 114, the control unit 100 determines that the seventh environment (the third multipath environment) when there is only one M2 satellite and all the others are M3 satellites. ).
For example, as shown in FIG. 14A , the seventh environment is an environment like a building 18 having only one window 18a. In the seventh environment, satellites in the direction of the window 18a can be tracked by M2, but signals from other satellites are likely to be multipath.
As illustrated in FIG. 9, when the control unit 100 determines that the environment is the seventh environment, the control unit 100 performs positioning by taking a multipath countermeasure based on the positioning program 116 .

As illustrated in FIG. 9 , based on the environment determination program 114, the control unit 100 determines that the environment is the eighth environment (second weak electric field) when only the M3 satellite having the second weak electric field is present.
For example, as shown in FIG. 14B , the eighth environment is an environment in which the communication base station 14 and the high-voltage line 18A that are noise sources are located in the vicinity.
As illustrated in FIG. 9, when the control unit 100 determines that the environment is the eighth environment, the control unit 100 performs positioning using all the measurements based on the positioning program 116.

As shown in FIG. 9 , based on the environment determination program 114, the control unit 100 determines that it is the ninth environment (first weak electric field) when only the M3 satellite having the first weak electric field is present.
For example, as shown in FIG. 15 , the ninth environment is an environment in which the communication base station 14 and the high-voltage lines 18A and 18B that are noise sources are located in the vicinity.
As shown in FIG. 9 , when it is determined that the environment is the ninth environment, the control unit 100 uses all the measurements based on the positioning program 116, and further increases the integration time (incoherent time). Measure.

The control unit 100 calculates the positioning position P by the above positioning, and stores the positioning position information 160 indicating the positioning position P in the second storage unit 150.
The third environment, the fourth environment, the fifth environment, the sixth environment, and the seventh environment described above are examples of a multipath environment.

As illustrated in FIG. 5 , the terminal 20 stores a positioning position output program 118 in the first storage unit 110. The positioning position output program 118 is a program for the control unit 100 to output the positioning position P from the display device 34 (see FIG. 4 ).

The terminal 20 is configured as described above.
As described above, the terminal 20 determines the reception environment (first environment to ninth environment) based on the number of GPS satellites 12a and the like corresponding to the C / A codes received in the modes M2 and M3. .
For this reason, the terminal 20 can determine the reception environment even though it does not need to hold map data or communicate with the communication base station.
Further, the terminal 20 determines whether to exclude the measurement and whether to correct the measurement based on the reception environment, and performs positioning.
Thus, the terminal 20 does not need to hold map data or communicate with the communication base station, and can perform positioning using the satellite signal effectively according to various reception environments.

The above is the configuration of the terminal 20 according to the present embodiment. Hereinafter, an example of the operation will be described mainly using FIG .
FIG. 20 is a schematic flowchart showing an operation example of the terminal 20.

First, the terminal 20 receives the radio wave S1 and the like (step ST1 in FIG. 20 ), and calculates a measurement (ST2). Steps ST1 and ST2 are an example of a basic value calculation step.
Subsequently, the terminal 20 makes an environment determination (step ST3). This step ST3 is an example of a reception environment determination step.

Subsequently, the terminal 20 performs positioning (step ST4). This step ST4 is an example of a positioning step.
Subsequently, the terminal 20 outputs the positioning position P (step ST5).
Through the above-described steps ST1 to ST5, the terminal 20 does not need to hold map data or communicate with a communication base station, and performs positioning using satellite signals effectively according to various reception environments. be able to.

( Embodiment of the present application )
Next, an embodiment of the present application will be described.
Terminal 20 intends row by another method the determination of the fourth environment (bias environment) in the embodiment as a premise of the above.

FIG. 21 is an explanatory diagram of bias determination.
FIG. 21A shows a situation where the satellites are biased.
As shown in FIG. 21A , the control unit 100 of the terminal 20 calculates the center of gravity G of the figure connecting the coordinates of each satellite defined by the elevation angle and the azimuth angle. Then, the control unit 100 calculates a vector H from the terminal 20 toward the center of gravity G. Then, the control unit 100 determines that the GPS satellites 12a and the like are biased in the direction of the vector H when the magnitude of the vector H, that is, the elevation angle component satisfies the condition that it is less than 45 degrees, for example. Less than 45 degrees is an example of a predetermined size.
The condition that the magnitude of the vector H, that is, the elevation angle component is, for example, less than 45 degrees is an example of the second bias condition.

FIG. 21B shows a situation where the satellites are not biased.
As shown in FIG. 21B , when the satellite is not biased, the vector H is 45 degrees or more.
For this reason, the deviation of the satellite can be determined by the magnitude of the vector H (elevation angle component).

(About programs and computer-readable recording media)
A positioning apparatus control program for causing a computer to execute the azimuth calculation step and the reception environment determination step of the above-described operation example can be provided.
Moreover, it can also be set as the computer-readable recording medium etc. which recorded the control program etc. of such a positioning apparatus.

  A program storage medium used for installing the control program of the positioning terminal device in the computer and making it executable by the computer is, for example, a flexible disk such as a floppy (registered trademark), a CD-ROM (Compact Disc Read). Semiconductors in which programs are stored temporarily or permanently, as well as package media such as Only Memory (CD), Compact Disc-Recordable (CD-R), Compact Disc-Rewriteable (CD-RW), DVD (Digital Versatile Disc), etc. It can be realized by a memory, a magnetic disk, a magneto-optical disk, or the like.

  The present invention is not limited to the embodiments described above. Furthermore, the above-described embodiments may be combined with each other.

It is the schematic which shows the terminal etc. of embodiment of this invention. It is a conceptual diagram which shows the positioning method. It is explanatory drawing of a correlation process. It is the schematic which shows the main hardware constitutions of a terminal. It is the schematic which shows the main software structures of a terminal. It is explanatory drawing of a satellite signal reception program. It is a figure which shows an example of measurement information. It is explanatory drawing of an environment determination program. It is explanatory drawing of an environment determination program and a positioning program. It is explanatory drawing of a reception environment. It is explanatory drawing of a reception environment. It is explanatory drawing of a reception environment. It is explanatory drawing of a reception environment. It is explanatory drawing of a reception environment. It is explanatory drawing of a reception environment. It is explanatory drawing of judgment of bias environment. It is explanatory drawing of judgment of bias environment. It is explanatory drawing of judgment of bias environment. It is explanatory drawing of judgment of a valley environment. It is a schematic flowchart which shows the operation example of a terminal. It is explanatory drawing of judgment of bias environment.

Explanation of symbols

  12a, 12b, 12c, 12d, 12e, 12f, 12g, 12h ... GPS satellite, 20 ... terminal, 112 ... satellite signal reception program, 114 ... environment determination program, 116 ... positioning program 118 ... Positioning position output program

Claims (5)

A positioning device that determines the position bias of the SPS satellite based on a satellite signal from an SPS (Satellite Positioning System) satellite and performs positioning based on the determination result,
Of the SPS satellites, the received satellite signal is a predetermined strong electric field signal, and the position of the center of gravity of the graphic connecting the position coordinates of the strong signal satellite is calculated, and the elevation angle of the vector from the positioning device to the position of the center of gravity is predetermined. When the elevation angle condition is satisfied, it is determined that the position of the SPS satellite is biased, and based on the position of the center of gravity , the SPS satellite in the direction opposite to the bias of the position of the SPS satellite is excluded and used for positioning. Determination means for determining a bias in the position of the SPS satellite in order to select an SPS satellite;
A positioning device comprising: The positioning device according to claim 1 , wherein the predetermined elevation angle condition is 0 degree or more and less than 45 degrees. The positioning device according to claim 1 , wherein the predetermined strong electric field signal is an electric field signal of −124 dBm or more. A positioning device control method for determining a positional deviation of the SPS satellite based on a satellite signal from an SPS satellite and performing positioning based on a determination result,
Of the SPS satellites, the received satellite signal is a predetermined strong electric field signal, and the position of the center of gravity of the graphic connecting the position coordinates of the strong signal satellite is calculated, and the elevation angle of the vector from the positioning device to the position of the center of gravity is predetermined. When the elevation angle condition is satisfied, it is determined that the position of the SPS satellite is biased, and based on the position of the center of gravity , the SPS satellite in the direction opposite to the bias of the position of the SPS satellite is excluded and used for positioning. A method for controlling a positioning device that determines a positional deviation of the SPS satellite in order to select an SPS satellite. A program for causing a computer built in the positioning device to determine the position bias of the SPS satellite based on the satellite signal from the SPS satellite, and to perform positioning based on the determination result,
The computer calculates a gravity center position of a figure connecting the position coordinates of a strong signal satellite in which the received satellite signal is a predetermined strong electric field signal among the SPS satellites, and a vector of the vector from the positioning device to the gravity center position is calculated. By determining that the position of the SPS satellite is biased when the elevation angle satisfies a predetermined elevation angle condition, and excluding the SPS satellite in the direction opposite to the bias of the position of the SPS satellite based on the position of the center of gravity . A program for determining the positional deviation of the SPS satellite in order to select the SPS satellite to be used for positioning.

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