KR102245574B1 - Aircraft gps signal splitter and method for controlling thereof - Google Patents

Abstract

The present invention relates to a GPS signal splitter for aircraft mounted between a GPS antenna and a GPS receiver of the aircraft and to a control method thereof. The GPS signal splitter includes: an RF GPS signal processing unit which amplifies and filters the GPS signal input through the GPS antenna, and provides the amplified and filtered GPS signal to the GPS receiver and other receivers; and a digital GPS signal processing unit which receives the divided GPS signal from the RF GPS signal processing unit, and controls amplification gain and channel filter path setting in the RF GPS signal processing unit based on the carrier-to-noise power ratio of the GPS signal and the number of detected satellites per channel.

Description

Aircraft GPS signal splitter and its control method {AIRCRAFT GPS SIGNAL SPLITTER AND METHOD FOR CONTROLLING THEREOF}

The present invention relates to a GPS signal splitter for an aircraft and a control method thereof, and in particular, a GPS antenna and a GPS capable of branching a GPS signal for newly installed equipment while utilizing the GPS antenna and receiver mounted on the aircraft as it is. It relates to a GPS signal splitter for aircraft mounted between receivers and a control method thereof.

Conventional GPS antennas and receivers mounted on aircraft are often as old as the aircraft's age, and parts are often expensive. In addition, in the design of an aircraft where stability is important, it is difficult to modify the GPS system installed in the aircraft that has already undergone numerous certifications, as there is a possibility that the existing performance and stability may be degraded.

In modern times, there is a lot of demand for remodeling and improving aircraft in order to increase the operational capability of the aircraft. In particular, in technology related to communication between aircraft and aircraft, and between aircraft and ground control centers, a method of using GPS signals received from aircraft is applied for security reasons.

Accordingly, in the case of remodeling or improving an aircraft, there should be no influence on the existing peripheral equipment, and at the same time, a technology capable of providing GPS signals for newly installed equipment is required.

The problem to be solved of the present invention is a GPS signal for an aircraft mounted between a GPS antenna and a GPS receiver that can utilize the GPS antenna and receiver installed in the aircraft as it is and branch the GPS signal for newly installed equipment. A divider and a control method thereof are provided.

However, the technical problem to be achieved by the present embodiment is not limited to the technical problem as described above, and other technical problems may exist.

As a technical means for achieving the above-described technical problem, the GPS signal splitter for an aircraft mounted between the GPS antenna and the GPS receiver of the aircraft according to the first aspect of the present invention amplifies and amplifies the GPS signal input through the GPS antenna. Filtering and receiving the divided GPS signal from the RF GPS signal processing unit and the RF GPS signal processing unit to provide the amplified and filtered GPS signal to the GPS receiver and other receivers, and detection per channel and carrier-to-noise power ratio of the GPS signal And a digital GPS signal processor for controlling an amplification gain and channel filter path setting in the RF GPS signal processor based on the number of satellites.

In some embodiments of the present invention, the digital GPS signal processor may rectify power input from an external power source and supply it to an unknown antenna, and determine the type of the antenna based on a current consumption value of the antenna.

In some embodiments of the present invention, when the digital GPS signal processor determines that the antenna is an active antenna, the power is continuously supplied to the active antenna, and the power previously supplied to the active antenna may be DC Blocked. .

In some embodiments of the present invention, when determining that the antenna is a passive antenna, the digital GPS signal processor may stop supplying power to the passive antenna.

In some embodiments of the present invention, the RF GPS signal processor adjusts an amplification gain for amplifying a GPS signal input through the GPS antenna based on at least one of the number of satellites detected per channel and a carrier-to-noise power ratio. It may include an amplifier (Low Noise Amplifier).

In some embodiments of the present invention, the RF GPS signal processor may include a divider for distributing the GPS signal output from the low noise amplifier, and may transmit some of the GPS signals distributed by the divider to the digital GPS signal processor. .

In some embodiments of the present invention, the digital GPS signal processing unit includes a high-frequency front-end unit for receiving the partial GPS signals, down-converting to correspond to a center frequency of each channel, and converting the digital signal, and the detected per channel for each channel. The number of satellites and the carrier-to-noise power ratio of the GPS signal converted into the digital signal are checked, and based on whether at least one channel that satisfies a predetermined number of satellites and has a value equal to or higher than a predetermined carrier-to-noise power ratio exists. It may include a processor that adjusts the amplification gain of the low noise amplifier.

In some embodiments of the present invention, the processor amplifies the amplification gain of the low-noise amplifier when a channel having a value greater than or equal to the predetermined carrier-to-noise power ratio does not exist, but the amplification of the low-noise amplifier satisfies the predetermined number of satellites or more. When the gain has the maximum value, it can be controlled so that the GPS signal cannot be detected or the radio wave interference warning light is turned on.

In some embodiments of the present invention, when there is at least one channel that satisfies the predetermined number of satellites or has a value equal to or higher than a predetermined carrier-to-noise power ratio, the processor has a predetermined number of identified satellites for each channel. As a result of classifying the group into groups, calculating the UTC for each group and comparing it with the UTC stored in the internal timer module, the group that satisfies a predetermined time or less is classified as a higher grade group, and the group exceeding a predetermined time is classified as an average grade group. Can be classified.

In some embodiments of the present invention, the processor replaces the satellites belonging to the average grade group into higher grade groups one by one, calculates UTC for the transferred group, and satisfies a predetermined time or less, the higher grade group And, when a predetermined time is exceeded, the satellites that have been incorporated into the substitute can be classified into sub-class groups, and tracking may be stopped.

In some embodiments of the present invention, the processor checks the number of satellites belonging to the upper level group for each channel, assigns a first priority to the channel with the largest number of satellites, and assigns a first priority to the channel assigned as the second priority. When the number of satellites is greater than or equal to the predetermined number, paths of the low-noise amplifier and the output filter of the low-noise amplifier may be set to amplify channels including all channels corresponding to the first and second ranks.

In some embodiments of the present invention, when the number of satellites in the channel to which the second priority is assigned is less than the predetermined number, the processor is configured to amplify the channel corresponding to the first priority. Can be set.

In addition, the control method in the GPS signal splitter for aircraft mounted between the GPS antenna of the aircraft and the GPS receiver according to the second aspect of the present invention comprises the steps of rectifying power input from an external power source and supplying it to an unknown antenna; Determining an active antenna or a passive antenna based on the current consumption value of the GPS antenna; Determining whether to supply power to the GPS antenna based on the determination result; Setting an amplification gain and a channel filter path based on a performance optimization algorithm of a GPS signal input from the GPS antenna; And providing a GPS signal output according to the set channel filter path to a GPS receiver and another receiver. In this case, the step of setting an amplification gain and a channel filter path based on a performance optimization algorithm of a GPS signal input from the GPS antenna may include an amplification gain and a channel based on the carrier-to-noise power ratio of the GPS signal and the number of satellites detected per channel. Set the filter path.

In addition to this, another method for implementing the present invention, another system, and a computer-readable recording medium for recording a computer program for executing the method may be further provided.

Other specific details of the present invention are included in the detailed description and drawings.

According to any one of the above-described problem solving means of the present invention, it is possible to improve the performance of the GPS receiver for an aircraft, and to provide the GPS signal by dividing it, thereby improving the convenience of interworking with other equipment.

In addition, there is an advantage in that it is possible to block radio wave interference or to immediately check the quality of a GPS signal through GPS signal analysis, and to avoid jamming according to a GPS channel selection.

The effects of the present invention are not limited to the effects mentioned above, and other effects not mentioned will be clearly understood by those skilled in the art from the following description.

The accompanying drawings are provided to aid understanding of the present embodiment, and provide the embodiments together with a detailed description. However, the technical features of the present embodiment are not limited to a specific drawing, and features disclosed in each drawing may be combined with each other to constitute a new embodiment.
1 is a view for explaining a GPS signal splitter for an aircraft according to an embodiment of the present invention.
2 is a diagram showing an example of the structure of a GPS signal splitter for an aircraft according to an embodiment of the present invention.
3 is a diagram for describing a GPS signal performance optimization algorithm.
4 is a flowchart of a method for controlling a GPS signal divider according to an embodiment of the present invention.

Advantages and features of the present invention, and a method of achieving them will become apparent with reference to the embodiments described below in detail together with the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below, but may be implemented in a variety of different forms, only the present embodiments are intended to complete the disclosure of the present invention, and those of ordinary skill in the art to which the present invention pertains. It is provided to completely inform the scope of the present invention, and the present invention is only defined by the scope of the claims.

The terms used in this specification are for describing exemplary embodiments and are not intended to limit the present invention. In this specification, the singular form also includes the plural form unless specifically stated in the phrase. As used herein, “comprises” and/or “comprising” do not exclude the presence or addition of one or more other elements other than the mentioned elements. Throughout the specification, the same reference numerals refer to the same elements, and "and/or" includes each and all combinations of one or more of the mentioned elements. Although "first", "second", and the like are used to describe various elements, it goes without saying that these elements are not limited by these terms. These terms are only used to distinguish one component from another component. Therefore, it goes without saying that the first component mentioned below may be the second component within the technical idea of the present invention.

Unless otherwise defined, all terms (including technical and scientific terms) used in the present specification may be used with meanings that can be commonly understood by those of ordinary skill in the art to which the present invention belongs. In addition, terms defined in a commonly used dictionary are not interpreted ideally or excessively unless explicitly defined specifically.

Hereinafter, a GPS signal splitter for an aircraft and a control method thereof according to a preferred embodiment of the present invention will be described in detail with reference to the accompanying drawings.

1 is a block diagram of a GPS signal splitter 100 for an aircraft according to an embodiment of the present invention, and FIG. 2 is a block diagram illustrating a structure of a GPS signal splitter 100 for an aircraft according to an embodiment of the present invention. It is a drawing.

The GPS signal splitter 100 for an aircraft according to an embodiment of the present invention includes an RF GPS signal processing unit 110 and a digital GPS signal processing unit 120.

The RF GPS signal processing unit 110 amplifies and filters a GPS signal input through the GPS antenna 10 and provides the amplified and filtered GPS signal to the GPS receiver 20 and other receivers 30.

The digital GPS signal processing unit 120 extracts and calculates various data from the GPS signal output from the RF GPS signal processing unit 110, and controls the RF GPS signal processing unit 110 based on this.

The digital GPS signal processing unit 120 receives the divided GPS signal from the RF GPS signal processing unit 110, and based on the carrier-to-noise power ratio of the GPS signal and the number of satellites detected per channel, the amplification gain and channel of the RF signal processing unit are Controls filter path setting. Details related to this will be described later.

In addition, the present invention includes a warning indicating unit 130 for notifying a user of the current GPS status, and a timer module 140 for calculating and recording time independently and continuously using individual batteries.

First, an algorithm of operation of the GPS signal splitter 100 according to an embodiment of the present invention will be described.

The GPS signal divider 100 according to the present invention operates according to the operation algorithm of the GPS signal divider 100, and has the following main functions.

The GPS signal splitter 100 according to an embodiment of the present invention is connected between the GPS antenna 10 and the GPS receiver 20 for convenience of remodeling and improvement of an aircraft. If only external power is supplied, the antenna 10 Regardless of the type (active or passive) of the GPS signal splitter 100 is characterized in that it operates.

Specifically, the digital GPS signal processing unit 120 rectifies power received from an external power source and supplies it to the unknown antenna 10, and based on the current consumption value of the antenna 10 due to the power being supplied to the antenna 10 The type of antenna 10 can be determined.

When the GPS signal processing unit determines that the current consumption value of the unknown antenna 10 is an active antenna, power is continuously supplied to the active antenna, and the power previously supplied to the active antenna is DC Blocked.

In contrast, when the digital GPS signal processing unit 120 determines the unknown antenna 10 as a passive antenna, it stops supplying power to the passive antenna.

At this time, the low noise amplifier (LNA) of the GPS signal divider 100 has the lowest gain.

Thereafter, the GPS signal splitter 100 performs a GPS signal performance optimization algorithm, and then outputs a GPS signal and provides it to the GPS receiver 20 and other receivers 30. Details related to the GPS signal performance optimization algorithm will be described later.

As another feature, the GPS signal splitter 100 according to an embodiment of the present invention amplifies and filters the output of the antenna 10 manufactured in accordance with the old standard for convenience of remodeling and improving the aircraft. For some items, it can be made to meet the performance required by the latest standard. In particular, the low-noise amplifier included in the GPS signal divider 100 according to an embodiment of the present invention is a total antenna system gain and G/T ratio of DO-301 standard that could not be achieved when using a conventional passive antenna. The quality of the output signal of the passive antenna can be improved to match the performance of

In addition, the GPS signal splitter 100 according to an embodiment of the present invention may select a GPS signal reception path filter by itself for convenience of remodeling and improvement of an aircraft. This considers the characteristics of conventional passive antennas matched for multiple channels, while filtering radio waves (closed in frequency) radiated from other RF equipment to suppress radio wave interference, and detects GPS signals that change from time to time depending on the measurement time and location. This is to optimize performance in the environment.

In addition, the GPS signal splitter 100 according to an embodiment of the present invention includes an output of the GPS signal splitter 100 and an output input to the GPS receiver 20 of the aircraft, for convenience of remodeling and improvement of the aircraft. Provides a signal that has been branched by a predetermined number (for example, 4 branches, splitter 1Χ4). Although these output branches naturally degrade the performance of Total Antenna System Gain and G/T Ratio, they are naturally traded off as the gain of the low-noise amplifier increases in order to improve the signal quality.

In addition, when the GPS signal splitter 100 fails to initialize and operate for reasons of unknown cause, so as not to disconnect the GPS antenna 10 and the GPS receiver 20 installed on the aircraft, it is composed of only passive components even in the absence of power. The GPS antenna 10 and the GPS receiver 20 are connected through a signal line.

The GPS signal splitter 100 having such an operation algorithm adjusts the amplification gain through the GPS signal performance optimization algorithm, branches the GPS signal, and outputs it to the GPS receiver 20 and other receivers 30. Let's be specific.

3 is a diagram for describing a GPS signal performance optimization algorithm.

In an embodiment of the present invention, the GPS signal performance optimization algorithm continuously and continuously operates while the GPS signal splitter 100 is operating to optimize and maintain GPS signal detection performance in real time.

First, the RF GPS signal processing unit 110 acquires a GPS signal received from the GPS antenna 10 through each channel for a predetermined time (eg, 15 minutes) (S11). Here, each channel may be an L1 channel, an L2 channel, and an L5 channel.

After a predetermined time has elapsed (S13), the RF GPS signal processing unit 110 inputs three signals of the GPS signals obtained by dividing the output of the internal low noise amplifier into four from the 1x4 divider to the digital GPS signal processing unit.

When the digital GPS signal processing unit 120 receives three GPS signals, it down-converts to correspond to the center frequency of each channel through a high-frequency front end block, and converts it into a digital signal through an ADC. , Input to the internal processor.

The processor checks the number of satellites detected per channel and the quality of the GPS signal (carrier-to-noise power ratio, hereinafter C/No) through a signal processing process of a predetermined GPS receiver 20 (S15). Further, the processor adjusts the amplification gain of the low-noise amplifier based on whether at least one channel having a value greater than or equal to a predetermined number of satellites is satisfied and a value equal to or greater than a predetermined C/No exists (S17) (S19).

Here, when the processor satisfies the predetermined number of satellites and there is no channel having a value of C/No or higher (S17-N), the amplification gain of the low-noise amplifier is gradually amplified (S19), Repeat the previous steps again (S11 ~ S17).

At this time, when the amplification gain of the low-noise amplifier has a maximum value in the process of repeating the previous steps (S21), the processor controls to turn on (red) the GPS signal detection inability or the radio interference warning light of the warning indicator 130. Can be (S23).

In contrast, the processor satisfies a predetermined number of satellites and has at least one channel having a value equal to or higher than a predetermined carrier-to-noise power ratio (S17-Y), for example, among the three channels L1, L2, and L5. Even in one channel, if there are 4 or more satellites and the C/No value is 35 or more, the next step is performed.

Next, the processor classifies the satellites identified for each channel into groups having a predetermined number (S25). For example, the processor can randomly group the detected satellites into groups of four. If, as a result of grouping, there are less than 4 satellites remaining, the satellites of the last group may be duplicated and included in the group.

Then, the processor calculates UTC from the GPS data (location, time) obtained from the satellites of each group, compares it with the UTC stored in the internal timer module 140, and selects a group satisfying a predetermined time or less as an upper class group. The group is classified as ("GOOD" group), and the group exceeding a predetermined time is classified as an average grade group ("AVERAGE group") (S27 to S43).

2초는 신호 처리 시간의 단축을 위해

2초로 설정한 것으로, GPS 신호 분할기(100) 내부 프로세서의 성능을 증가시킬수록 작은 값을 가질 수 있으며, 다양한 값을 가질 수 있음은 물론이다.Here, presented at a predetermined time

2 seconds to shorten the signal processing time

It is set to 2 seconds, and as the performance of the internal processor of the GPS signal divider 100 increases, it may have a smaller value, and of course, it may have various values.

The processor checks the number of high-ranking groups upon completion of classifying all the groups into the upper grade group and the average grade group (S45).

At this time, if there is no group classified as a higher level group (S47), the processor determines that there is an abnormality in the quality of the currently tracked GPS signal, and turns on the warning light of the warning instruction unit 130 (yellow), so that the pilot or flight attendant A warning can be made about the quality of the GPS signal (S49).

On the other hand, that the value of UTC is different enough to exceed a predetermined time means that there is an error in the GPS data (location, time) of some or all of the four satellites. Therefore, according to the completion of classifying all the groups into the upper class group and the average class group, the processor replaces the satellites belonging to the average class group one by one into the higher class group when the average class group exists (S51). The process of calculating UTC is repeated (S53~S55).

2초) 이하를 만족하는 경우(S57-Y), 대체 편입된 위성을 상위 등급 그룹으로 분류한다(S59).Based on the replaced satellite, the comparison value of UTC of the upper class group is determined at a predetermined time (

2 seconds) If the following is satisfied (S57-Y), the satellites incorporating the replacement are classified into a higher class group (S59).

2초)을 초과하는 경우(S57-N), 대체 편입된 위성을 하위 등급 그룹으로 분류하고 해당 위성에 대해서는 추적을 중단한다(S61).In contrast, the comparison value of UTC of the upper class group based on the replaced satellite is a predetermined time (

If it exceeds 2 seconds) (S57-N), the satellites that have been incorporated into the substitute are classified into sub-class groups, and the tracking of the satellites is stopped (S61).

This process is repeatedly performed until there are no satellites left in the average rating group (S63).

When the classification of all the detected satellites is completed, the processor checks the number of satellites belonging to the upper class group for each channel (S65) and assigns a ranking to each channel based on the number of detected satellites (S67).

At this time, when the number of satellites in the channel to which the second priority is assigned is greater than or equal to a certain number (S69-Y), the processor of the low noise amplifier and the low noise amplifier amplifies a channel including all channels corresponding to the first priority and the second priority. The path of the output filter is set (S71).

That is, in the above-described example, when the number of satellites in the second group is four or more, which is a predetermined number, an output filter path including channels corresponding to the first priority and the second priority is set.

In contrast, when the number of satellites in the channel assigned the second priority is less than a certain number (S69-N), the processor sets the path of the low-noise amplifier and the output filter of the low-noise amplifier to amplify the channel corresponding to the first priority. It is done (S73).

On the other hand, the number of satellites to which the third priority is assigned may be more than a certain number, but since most of the GPS antennas for aircraft 10 are matched only for two GPS channels, the channel of the low noise amplifier and the output filter It is inefficient to match three to three.

Thereafter, the processor calculates UTC based on all detected satellites and stores it in the timer module 140. This is performed only once for the first time after power is supplied from among continuously repeated algorithms, and is used as a comparison target UTC when power is supplied to the GPS signal divider 100 later (S75).

The UTC stored in the timer module 140 measures and records the time in 0.1 units through a precision oscillator and a micro control unit (MCU) inside the timer module 140. When power is not supplied, the timer module 140 operates independently until the internal battery is discharged, and operates using power at the same time as power is supplied to charge the internal battery.

On the other hand, the warning instruction unit 130, as described above, turns on the OLED when none of the higher grade groups are detected to warn the pilot or crew about the current GPS signal quality.

In addition, if the red OLED is turned on immediately after power is supplied to the GPS signal splitter 100 for the first time, this is a case where detection of all channels is impossible and the probability of the antenna 10 failure is high, thus providing convenience related to aircraft maintenance. Can give.

In addition, when the yellow OLED or the red OLED is sequentially lit, there is a possibility of radio wave interference, so it can give a warning to fly with more confidence in the location information obtained from other electronic equipment than the pilot or GPS location information.

On the other hand, since some of the airborne radio equipment allows the GPS information to be interlocked through a digital communication method, GPS location information naturally obtained while performing the UTC calculation may be provided through various digital communication methods (S77).

Hereinafter, a control method in the GPS signal splitter 100 for an aircraft mounted between the GPS antenna 10 and the GPS receiver 20 of an aircraft according to an embodiment of the present invention will be described.

4 is a flowchart of a method of controlling the GPS signal splitter 100 according to an embodiment of the present invention.

First, the GPS signal splitter 100 rectifies power received from an external power source and supplies it to the unknown antenna 10 (S110).

Next, it is determined as an active antenna or a passive antenna based on the current consumption value of the GPS antenna 10 (S120), and whether or not power is supplied to the antenna 10 is determined based on the determination result (S130).

to the next. The amplification gain and the channel filter path are set based on the performance optimization algorithm of the GPS signal input from the GPS antenna 10 (S140), and the GPS signal output according to the set channel filter path is transmitted to the GPS receiver 20 and other receivers ( 30) is provided (S150).

In the above description, steps S110 to S150 may be further divided into additional steps or may be combined into fewer steps, according to an embodiment of the present invention. In addition, some steps may be omitted as necessary, or the order between steps may be changed. In addition, even if other contents are omitted, the contents described in FIGS. 1 to 3 may also be applied to the method of controlling the GPS signal divider 100 of FIG. 4.

The method for controlling the GPS signal splitter 100 according to an embodiment of the present invention described above may be implemented as a program (or application) to be executed by being combined with a computer, which is hardware, and stored in a medium.

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The above-described program includes C, C++, JAVA, Ruby, which can be read by a processor (CPU) of the computer through the device interface of the computer, in order for the computer to read the program and execute the methods implemented as a program. It may include a code (Code) coded in a computer language such as machine language. Such code may include a functional code related to a function defining necessary functions for executing the methods, and a control code related to an execution procedure necessary for the processor of the computer to execute the functions according to a predetermined procedure. can do. In addition, these codes may further include additional information required for the processor of the computer to execute the functions or code related to a memory reference to which location (address address) of the internal or external memory of the computer should be referenced. have. In addition, when the processor of the computer needs to communicate with any other computer or server in a remote in order to execute the functions, the code is It may further include a communication-related code for whether to communicate, what kind of information or media to be transmitted and received during communication.

The stored medium is not a medium that stores data for a short moment, such as a register, cache, memory, etc., but a medium that stores data semi-permanently and can be read by a device. Specifically, examples of the storage medium include, but are not limited to, ROM, RAM, CD-ROM, magnetic tape, floppy disk, optical data storage device, and the like. That is, the program may be stored in various recording media on various servers to which the computer can access, or on various recording media on the user's computer. In addition, the medium may be distributed over a computer system connected through a network, and computer-readable codes may be stored in a distributed manner.

The above description of the present invention is for illustrative purposes only, and those of ordinary skill in the art to which the present invention pertains will be able to understand that other specific forms can be easily modified without changing the technical spirit or essential features of the present invention. will be. Therefore, it should be understood that the embodiments described above are illustrative and non-limiting in all respects. For example, each component described as a single type may be implemented in a distributed manner, and similarly, components described as being distributed may also be implemented in a combined form.

The scope of the present invention is indicated by the claims to be described later rather than the detailed description, and all changes or modified forms derived from the meaning and scope of the claims and their equivalent concepts should be construed as being included in the scope of the present invention. do.

10: GPS antenna
20: GPS receiver
30: other receiver
100: GPS signal splitter
110: RF GPS signal processing unit
120: digital GPS signal processing unit
130: warning instruction unit
140: timer module

Claims (13)

In the aircraft GPS signal splitter mounted between the GPS antenna of the aircraft and the GPS receiver,
An RF GPS signal processor for amplifying and filtering a GPS signal input through the GPS antenna, and providing the amplified and filtered GPS signal to the GPS receiver and other receivers, and
Digital GPS for receiving the divided GPS signal from the RF GPS signal processor and controlling the amplification gain and channel filter path setting in the RF GPS signal processor based on the carrier-to-noise power ratio of the GPS signal and the number of satellites detected per channel Including a signal processing unit,
The RF GPS signal processing unit,
And a low noise amplifier in which an amplification gain for amplifying a GPS signal input through the GPS antenna is adjusted based on at least one of the number of satellites detected per channel and a carrier-to-noise power ratio, from the low noise amplifier. A divider for distributing the output GPS signal, and transmitting some of the GPS signals distributed by the divider to the digital GPS signal processing unit,
The digital GPS signal processing unit,
A high-frequency front end for receiving the partial GPS signals, down-converting to correspond to the center frequency of each channel, and converting it to a digital signal; and
At least one channel that checks the number of detected satellites per channel and the carrier-to-noise power ratio of the GPS signal converted to the digital signal for each channel, satisfies a predetermined number of satellites or has a value equal to or higher than a predetermined carrier-to-noise power ratio A processor that adjusts the amplification gain of the low noise amplifier based on whether or not is present,
The processor,
When at least one channel that satisfies the predetermined number of satellites or has a value equal to or higher than the predetermined carrier-to-noise power ratio exists, the satellites identified for each channel are classified into groups having a predetermined number, and UTC for each group is calculated. As a result of comparing with the UTC stored in the internal timer module, a group satisfying a predetermined time or less is classified as an upper grade group, and a group exceeding the predetermined time is classified as an average grade group.
The method of claim 1,
The digital GPS signal processing unit.
A GPS signal divider for aircraft, which rectifies power received from an external power source and supplies it to an unknown antenna, and determines the type of the antenna based on a current consumption value of the antenna.
The method of claim 2,
The digital GPS signal processing unit,
When it is determined that the antenna is an active antenna, the power is continuously supplied to the active antenna, and the power previously supplied to the active antenna is DC Block processed.
The method of claim 2,
The digital GPS signal processing unit,
When it is determined that the antenna is a passive antenna, the GPS signal splitter for aircraft to stop supplying power to the passive antenna.
delete delete delete The method of claim 1,
The processor,
When the number of satellites is satisfied and there is no channel having a value greater than or equal to the predetermined carrier-to-noise power ratio, the amplification gain of the low-noise amplifier is amplified. Or a GPS signal splitter for aircraft that controls the radio wave interference warning light to light up.
delete The method of claim 1,
The processor,
Satellites belonging to the average class group are replaced one by one into a higher class group, and UTC is calculated for the transferred group, and if a certain time or less is satisfied, the satellite is classified into the upper class group, and a predetermined time is exceeded. The GPS signal splitter for aircraft to classify the satellites incorporated into sub-class groups and stop tracking.
The method of claim 1,
The processor,
For each channel, a first priority is given to the channel with the largest number of satellites by checking the number of satellites belonging to the upper level group, and when the number of satellites of the channel assigned with the second priority is greater than or equal to the predetermined number, the second A GPS signal divider for an aircraft to set the path of the output filter of the low noise amplifier and the low noise amplifier to amplify a channel including all channels corresponding to the first and second ranks.
The method of claim 11,
The processor,
When the number of satellites in the channel assigned the second priority is less than the predetermined number, paths of the low noise amplifier and the output filter of the low noise amplifier are set to amplify the channel corresponding to the first priority.
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