KR100662255B1 - Satellite positioning device using satellite measurement signal and method - Google Patents

Abstract

1. TECHNICAL FIELD OF THE INVENTION

The present invention relates to an apparatus and method for positioning satellites using satellite measurement signals.

2. The technical problem to be solved by the invention

According to the present invention, two primary / secondary tracking, telemetry and command subsystem (TTC) subsystems individually receive a satellite measurement signal (TM) including a ranging packet to calculate pseudo distances from each satellite. The two pseudoranges are used to determine the distance from the TTC subsystem to the satellite and its positional coordinates, thereby reducing the burden on the satellite's signal processing and also eliminating interference due to multimodulation. The purpose of the present invention is to provide a satellite positioning device and method using the measured signal.

3. Summary of Solution to Invention

)와, 다른 부(Backup) TTC 서브시스템으로부터 전송받은 상기 부(Backup) TTC 서브시스템에서 상기 GEO위성까지의 제 2 의사거리(

)를 이용하여 상기 TTC 서브시스템에서 상기 GEO위성까지의 거리(R_p)를 산출하고, 상기 GEO위성까지의 거리(R_p)를 이용하여 상기 GEO위성의 좌표상의 위치를 결정하는 위성위치 결정하기 위한 위성위치 결정 수단을 포함함.The present invention provides a satellite positioning signal (TM) transmitted by a geostationary orbit (GEO) satellite in a satellite positioning device of a TTC subsystem (Tracking, Telemetry and Command Subsystem), and receives the received satellite measurement signal (TM). Baseband TM data generating means for converting the satellite measurement signal TM including ranging packets into digital baseband TM data; Reference ranging packet generation means for generating a reference ranging packet of the same type as the ranging packet inserted into the satellite measurement signal TM in the GEO satellite; Ranging packet arrival time calculating means for calculating an arrival time of the ranging packet through correlation between the digital baseband TM data and the reference ranging packet; And a first pseudo distance from the GEO satellite to the TTC subsystem calculated using the ranging packet arrival time.

) And a second pseudo-range (from the Backup TTC Subsystem received from another Backup TTC Subsystem to the GEO satellite).

Calculate a distance (R _p ) from the TTC subsystem to the GEO satellite and determine the satellite position to determine the coordinate position of the GEO satellite using the distance (R _p ) to the GEO satellite. Satellite positioning means.

4. Important uses of the invention

The present invention is used for positioning satellites.

Satellite location, ranging packet, ranging packet arrival time, Ranging PAT, TTC subsystem, pseudorange

Description

Apparatus and Method for determining a Satellite Position Using Telemetry}             

1 is a configuration diagram of a satellite communication system to which the present invention is applied;

2 is a configuration diagram of an embodiment of a satellite positioning device using satellite measurement signals according to the present invention;

3 is a flowchart illustrating a satellite positioning method using satellite measurement signals according to the present invention.

* Explanation of symbols for the main parts of the drawings

100: GEO satellite 110: GPS satellite

120: primary TTC subsystem 130: secondary TTC subsystem

200: baseband TM data generator 210: reference ranging packet generator

220: ranging packet arrival time calculation unit 230: satellite positioning unit

The present invention relates to a satellite positioning device and a method thereof, and more specifically, two main / sub tracking TTC subsystems include satellite measurement signals (TM) including ranging packets. To calculate the pseudo distance from each to the satellites, and use the two pseudo distances to determine the distance from the TTC subsystem to the satellite and its position coordinates, thereby reducing the burden on the satellite signal processing, In addition, the present invention relates to a satellite positioning device using a satellite measurement signal, and a method for removing interference due to multiple modulation.

In order to determine the position of a satellite and to predict its orbit, it is necessary to determine the position of the satellite. In the case of a low orbit satellite, a GPS (Global Position System) satellite signal may be received, and thus the position of the satellite may be determined using the GPS signal received from the low orbit satellite. However, this method has a limitation in that it cannot be used in an orbital satellite that cannot receive GPS signals, that is, a geostationary satellite.

Therefore, a separate tracking system for satellite positioning is required. In order to obtain satellite position data in the TTC subsystem (Tracking, Telemetry and Command Subsystem) of the satellite control system, the following method is generally used.

The angular coordinates data for the satellites are calculated from the angle tracking data of the TTC antenna, and the satellite position is determined by calculating the distance data to the satellites using the ranging tone. Angle tracking for satellites measures the elevation and azimuth data for satellites and uses an antenna system that uses a monopulse tracking device to improve accuracy. In addition, the ranging tone method for calculating the distance data to the satellite can know the distance by comparing the phase difference of the tone transmitted to the satellite with the phase difference of the ranging tone signal returned from the satellite.

Here, the ranging tone method used to measure the distance from the TTC antenna to the satellite of the control system has the following problems.

First, the ranging tone method uses a method of transmitting a ranging tone signal using a TTC channel and comparing a phase difference between the same signal returned from a satellite and a transmitted signal. In satellite towers, it is necessary to provide the ability to switch ranging signals so that TTC channels can be used for ranging to satellites, which complicates the satellite payload structure and inherently The problem is that it can put a strain on satellites that have to perform a mission.

Second, since the ranging tone signal is transmitted with the satellite command signal through the TTC channel and received with the satellite measurement signal, the ranging tone signal should be transmitted and received using a multimodulation method. There is a problem that the complexity of the TTC transceiver equipment and the cost burden increases.

Third, since the multimodulation scheme is used, the ranging tone signal interferes with the satellite command signal or the satellite measurement signal transmitted together, thereby worsening the reception reduction.

The present invention has been proposed to solve the above problems, two primary and secondary TTC subsystems separately receive a satellite measurement signal (TM) containing a ranging packet to calculate the pseudo distance from each to the satellite, The two pseudoranges are used to determine the distance from the TTC subsystem to the satellite and its positional coordinates, thereby reducing the burden on the satellite signal processing and also eliminating interference due to multimodulation. It is an object of the present invention to provide a satellite positioning device and a method using the signal.

Other objects and advantages of the present invention can be understood by the following description, and will be more clearly understood by the embodiments of the present invention. Also, it will be readily appreciated that the objects and advantages of the present invention may be realized by the means and combinations thereof indicated in the claims.

)와, 다른 부(Backup) TTC 서브시스템으로부터 전송받은 상기 부(Backup) TTC 서브시스템에서 상기 GEO위성까지의 제 2 의사거리(

)를 이용하여 상기 TTC 서브시스템에서 상기 GEO위성까지의 거리(R_p)를 산출하고, 상기 GEO위성까지의 거리(R_p)를 이용하여 상기 GEO위성의 좌표상의 위치를 결정하는 위성위치 결정하기 위한 위성위치 결정 수단을 포함한다.The apparatus of the present invention for achieving the above object, in the satellite positioning device of the TTC subsystem (Tracking, Telemetry and Command Subsystem), receives a satellite measurement signal (TM) transmitted by geostationary orbit (GEO) satellite, Baseband TM data generation means for converting the satellite measurement signal TM including the ranging packet among the received satellite measurement signals TM into digital baseband TM data; Reference ranging packet generation means for generating a reference ranging packet of the same type as the ranging packet inserted into the satellite measurement signal TM in the GEO satellite; Ranging packet arrival time calculating means for calculating an arrival time of the ranging packet through correlation between the digital baseband TM data and the reference ranging packet; And a first pseudo distance from the GEO satellite to the TTC subsystem calculated using the ranging packet arrival time.

) And a second pseudo-range (from the Backup TTC Subsystem received from another Backup TTC Subsystem to the GEO satellite).

Calculate a distance (R _p ) from the TTC subsystem to the GEO satellite and determine the satellite position to determine the coordinate position of the GEO satellite using the distance (R _p ) to the GEO satellite. Satellite positioning means.

)를 계산하는 제1의사거리 계산 단계; 상기 GEO위성이 송출한 상기 위성측정신호(TM)를 수신하여, 상기 GEO위성까지의 제 2 의사거리를 계산한 다른 부(Backup) TTC 서브시스템으로부터 네트웍을 통하여 상기 제 2 의사거리(

)를 수신하는 제2의사거리 수신 단계; 및 상기 제 1 의사거리와 상기 제 2 의사거리를 이용하여 상기 TTC 서브시스템에서 상기 GEO위성까지의 거리(R_p)를 산출하고, 상기 GEO위성까지의 거리(R_p)를 이용하여 상기 GEO위성의 좌표상의 위치를 결정하는 위성위치 결정 단계를 포함한다.On the other hand, in the method for determining the position of the satellite applied to the TTC subsystem, the digital baseband TM data for the satellite measurement signal (TM) including the ranging packet received from geostationary orbit (GEO) satellite, and the reference lane A ranging packet arrival time calculating step of calculating a ranging PAT of the ranging packet using a ranging packet; A first pseudo distance from the GEO satellite to the TTC subsystem using the ranging packet arrival time

Calculating a first range; Receiving the satellite measurement signal TM transmitted by the GEO satellite and calculating the second pseudo distance to the GEO satellite from the second Backup TTC subsystem via the network, the second pseudo distance (

Receiving a second range; And calculating the distance R _p from the TTC subsystem to the GEO satellite using the first pseudorange and the second pseudorange, and using the distance R _p to the GEO satellite. And a satellite positioning step of determining the position on the coordinate of the.

The above objects, features and advantages will become more apparent from the following detailed description taken in conjunction with the accompanying drawings, whereby those skilled in the art may easily implement the technical idea of the present invention. There will be. In addition, in describing the present invention, when it is determined that the detailed description of the known technology related to the present invention may unnecessarily obscure the gist of the present invention, the detailed description thereof will be omitted. Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings.

1 is a configuration diagram of a satellite communication system to which the present invention is applied.

The satellite control system performs the functions of controlling the satellite and monitoring the status. For this purpose, the TTC sub-system (Tracking, Telemetry and Command Subsystem), which performs the communication function with the satellite link, is installed.

The TTC subsystems 120 and 130 transmit satellite command signals and receive satellite measurement signals. To this end, the TTC subsystems 120 and 130 track the satellite reception signals, and also the geostationary trajectories of the TTC subsystems 120 and 130 to determine the position of the satellites. It performs a function of measuring the distance to a satellite (Geo-synchronous Orbit Satellite) (GEO satellite) (100).

Since the TTC subsystems 120 and 130 have an important task of performing a communication function with the satellite link, the primary TTC subsystem 120 and the backup TTC subsystem 130 are generally redundant. Is installed. In addition, the primary TTC subsystem 120 and the backup TTC subsystem 130 may be connected to each other via an Ethernet 140 to exchange information with each other.

The location of the primary TTC subsystem 120 and the location of the backup TTC subsystem 130 are preset to (x _P , y _P, z _P ) and (x _b , y _b, z _b ), respectively. It is already known from the measurement. The primary TTC subsystem 120 and the backup TTC subsystem 130 each receive a GPS signal from the GPS satellite 110 and operate with a high precision clock, and the primary TTC subsystem 120 Time synchronization is maintained between the backup TTC subsystem 130.

The antenna of the primary TTC subsystem 120 and the antenna of the backup TTC subsystem 130 receive a satellite measurement signal 101 (hereinafter referred to as TM) from the GEO satellite 100. The GEO satellite 100 is tracked, and since the angular coordinates data for the satellites are calculated from the angle tracking data of the antenna of the TTC subsystem, the azimuth and elevation can be known. have.

Range, azimuth, from the position (x _P , y _P, z _P ) of the primary TTC subsystem 120 to the GEO satellite (x _S , y _S, z _S ) 110 And elevation may be expressed as (R _P , A _P, E _P ).

The important thing here is to calculate the distance R _p from the antenna of the TTC sub system to the satellite. To this end, the present invention uses a method for calculating a pseudorange in the GPS satellites 110. First, the pseudoranges from the primary TTC subsystem 120 and the backup TTC subsystem 130 to the GEO satellite 100 are respectively calculated, and the generated two equations are used. It is to calculate the distance to the GEO satellite.

The GEO satellite 100 transmits its state as a satellite measurement signal TM, and constructs and transmits a unique ranging packet of the satellite in the satellite measurement signal TM, and transmits a primary TTC sub The system 120 and the backup TTC subsystem 130 generate a satellite measurement signal corresponding to a unique ranging packet of the GEO satellite, which is already known, and then receive the satellite measurement signal. (TM) and auto-correlation to measure lock-on time and errors caused by inconsistent visual synchronization between the GEO satellite and the Primary / Backup TTC subsystem are unknown. Set it as T _S and solve the equation.

In short, the GEO satellite constructs a unique ranging packet and transmits it using satellite measurement, and in the primary / backup TTC subsystem, the unique ranging packet of the satellite Built-in satellite measurement signal for Ranging Packet, and when receiving satellite measurement signal, time when receiving satellite measurement signal for satellite's unique ranging packet Calculate On the other hand, the bias component of the clock generated due to the inability to maintain time synchronization between the GEO satellite and the TTC subsystem of the control system is the primary TTC subsystem and the backup TTC receiving the GPS signal to maintain time synchronization. The solution is to use the subsystem to measure the distance between the TTC subsystem and the GEO satellite, and consequently determine the position of the satellite.

2 is a configuration diagram of a satellite positioning device using satellite measurement signals according to the present invention.

As shown in the drawing, the satellite positioning apparatus according to the present invention includes a baseband TM data generator 200, a reference ranging packet generator 210, a ranging packet arrival time calculator 220, and a satellite position. It includes a determination unit 230.

First, a general description of the satellite positioning device is as follows.

The baseband TM data generation unit 200 receives the satellite measurement signal TM transmitted by the geostationary orbit (GEO) satellite 100, and the satellite measurement including the ranging packet among the received satellite measurement signals TM. The signal TM is converted into digital baseband TM data, and the reference ranging packet generation unit 210 is the same type of reference as the ranging packet inserted into the satellite measurement signal TM by the GEO satellite 100. Generate a ranging packet.

Then, the ranging packet arrival time calculation unit 220 calculates the arrival time of the reference ranging packet through a correlation process between the digital baseband TM data and the reference ranging packet. In addition, the satellite positioning unit 230 is a pseudo distance from the GEO satellite 100 calculated from the ranging packet arrival time to the main TTC subsystem 120 and from the backup TTC subsystem 130. Using the pseudo distance from the received Backup TTC subsystem 130 to the GEO satellite 100, the distance R _p from the main TTC subsystem 120 to the GEO satellite 100 is calculated. The position R on the coordinates of the GEO satellite 100 is determined using the distance R _p to the GEO satellite.

Hereinafter, it demonstrates in detail as follows.

The satellite measurement signal TM including ranging packet data may be generated by a satellite command signal transmitted by the TTC subsystem to control the satellite, or may be periodically generated. Here, the ranging packet included in the satellite measurement signal TM is a unique packet, which should be known to both the main TTC subsystem and the secondary TTC subsystem on the ground.

The primary TTC subsystem 120 receives a 10 MHz, 1 PPS signal using a GPS signal and generates a clock frequency and time through a time base 205.

The process of generating a ranging packet arrival time (Ranging Packet Arrival Time) in the primary TTC subsystem 120 is as follows.

When the receiver 201 of the primary TTC subsystem 120 receives the satellite measurement signal TM, the frequency down converter (D / C) 202 down-converts to an IF (intermediate frequency) signal. do. The demodulator 203 demodulates the IF signal to generate a baseband TM signal, and the FEC decoder 204 decodes the baseband TM signal to TM. Generate data.

When the demodulator 203 receives a satellite measurement signal 101 including a ranging packet, the demodulator 203 converts a baseband TM signal into an analog-to-digital converter (ADC) 206. )

The analog-to-digital converter (ADC) 206 converts the baseband TM signal, which is the output of the demodulator 203, into baseband TM data, which is a digital value, and converts it into sample storage 207. Save it.

On the other hand, since the primary TTC subsystem 120 already knows a ranging packet and an encoding (encoding) scheme transmitted from the GEO satellite 100, the ranging packet generator 211 is a GEO satellite. Generates a ranging packet of the same type as a ranging packet included in the satellite measurement signal TM transmitted by the 100, and the encoding unit 212 generates the ranging packet. Encode with satellite encoding.

The ranging packet arrival time calculation unit 220 takes a correlation between the digital baseband TM data stored in the sample storage unit 207 and a ranging packet encoded by the encoding unit 212, Time mapping of the point at which the correlation becomes a peak may be performed, and as a result, a ranging packet arrival time may be calculated. That is, the ranging packet arrival time calculation unit 220 takes a correlation and obtains a point in time at which the correlation value becomes a peak, and then arrives at the ranging packet using a current time, a starting point generated during data mapping, and a ranging peak point. Calculate the ranging PAT.

The correlation unit correlates the baseband TM data stored in the sample storage unit 207 with a ranging packet encoded by the encoding unit 212 to determine a time at which a peak is generated. Time mapping can be used to calculate the ranging packet arrival time.

The satellite positioning unit 230 obtains the position of the GEO satellite by using the ranging packet arrival time (Ranging PAT) obtained through the above process, which will be described in detail with reference to FIG. 3.

3 is a flowchart illustrating a satellite positioning method using satellite measurement signals according to the present invention.

A baseband TM data sequence is generated by mapping the baseband TM data stored in the sample storage unit 207 (step 301), mapping a ranging packet (302), and encoding (303). When a ranging packet sequence is generated through the process, the two sequences are correlated (304).

Then, the peak position (ie, the maximum value of the correlation result) is obtained from the correlation result through the peak finder (305), and interpolation is performed to obtain a more accurate value. Find the peak peak position (306).

As a result, the ranging packet arrival time (Ranging PAT) is calculated through a time mapping process using a current time, a start position generated during data mapping, and an exact peak point.

를 계산 할 수 있다(308). 또한, 유사한 방법으로 부(Backup) TTC 서브시스템(130)에서도 GEO위성(100)까지의 의사거리 (Pseudorange),

를 계산할 수 있다(308).Then, using the ranging packet arrival time, the pseudorange from the primary TTC subsystem 120 to the GEO satellite 100,

Can be calculated (308). In a similar manner, the pseudorange to the GEO satellite 100 in the Backup TTC subsystem 130,

May be calculated (308).

와, 부(Backup) TTC 서브시스템(130)으로부터 수신한 부(Backup) TTC 서브시스템(130)에서도 GEO위성(100)까지의 의사거리(Pseudorange)

(309)를 이용하여, 주(Primary) TTC 서브시스템 (120)에서 GEO위성(100)까지의 거리(R_p)를 구한 후(310), 이를 이용하여 GEO위성(100)의 좌표상에서의 위치를 구하는 과정(311)을 상세히 설명하기로 한다.Hereinafter, the pseudorange from the primary TTC subsystem 120 to the GEO satellite 100 from the primary TTC subsystem 120 obtained by the primary TTC subsystem 120.

Pseudorange from the backup TTC subsystem 130 to the GEO satellite 100 also in the backup TTC subsystem 130 received from the backup TTC subsystem 130.

Using 309, after obtaining the distance R _p from the primary TTC subsystem 120 to the GEO satellite 100 (310), use this to locate the coordinates of the GEO satellite 100. The process of obtaining 311 will be described in detail.

In the Geocentric Cartesian coordinate system, the radius of the earth, R _e = 6378.155 [Km], is the longitude at θ _L (west diameter: θ _L > 0 , longitude θ _L <0 ), latitude θ _l at the location of the primary TTC subsystem 120 (North: θ _l > 0 , south: θ _l <0 ), ranging from primary TTC subsystem 120 to GEO satellite 100, ranging, azimuth, and elevation. If (R _p , A _p , E _p ), the position (x _S , y _S, z _S ) of the GEO satellite 100 can be expressed by the following equation (1).

Here, A _p 'is obtained from the azimuth angle A _p and the following relational expression.

In the northern hemisphere, A _p '= 180 °-A _{p when the} primary TTC subsystem is located west of the satellite, and A _p ' = A _p -when the primary TTC subsystem is located east of the satellite. 180 °. On the other hand, in the southern hemisphere, A _p '= A _{p when the} primary TTC subsystem is located west of the satellite, and A _p ' = 360 ° when the primary TTC subsystem is located east of the satellite. -A _p .

In addition, at the position of the Backup TTC subsystem 130, the hardness is θ _{L, b} (West diameter : θL, b,> 0 , Tokyo: θ _{L, b} <0 ), Latitude is θ _{l, b} (North: θ _{l, b} > 0 , South: θ _{l, b} <0 ) Backup) The position (x _b , y _b, z _b ) of the TTC subsystem 130 may be expressed by the following Equation 2.

는 위성에서 레인징 패킷(raging packet)을 전송한 시간(T_sat)과 주(Primary) TTC 서브시스템(120)에서 레인징 패킷(raging packet)을 수신한 시간(T_primary)의 차를 이용해서 계산할 수 있고, GEO 위성(100)과 주(Primary) TTC 서브시스템(120) 간에 시각적으로 동기되지 않음으로 인한 오차가 발생하므로 위성의 시각오차성분(ΔT_S)과 주(Primary) TTC의 시각오차성분(ΔT_P)을 고려해서 표현하면 다음의 [수학식 3]으로 정리된다.On the other hand, the pseudorange from the primary TTC subsystem 120 to the GEO satellite 100

Is based on the difference between the time T _sat at which the satellite transmits a ranging packet and the time T _{primary at} which the _primary TTC subsystem 120 receives the ranging packet. And visual errors of the satellite's visual error component (ΔT _S ) and primary TTC due to errors caused by visually out of synchronization between the GEO satellite 100 and the primary TTC subsystem 120. When the component (ΔT _P ) is considered and expressed, it is summarized as the following [Equation 3].

는 최종적으로 다음의 [수학식 4]으로 정리된다.Ignoring the ionosphere error and troposphere error components in Equation 3, c (T _S -T _P ) = _P = pseudorange from primary TTC subsystem 120 to GEO satellite 100

Is finally summarized by Equation 4 below.

는 다음의 [수학식 5]로 정리된다. In a method similar to the above Equation 4, the actual distance from the backup TTC subsystem 130 to the GEO satellite 100 is set to R _b , and the visual error of the backup TTC subsystem is obtained. Considering the component ΔT _b , the pseudorange from the backup TTC subsystem 130 to the GEO satellite 100

Is summarized by Equation 5 below.

Primary / Backup TTC subsystems 120 and 130 receive GPS signals and operate with a high precision clock to maintain time synchronization and ignore time error components. Therefore, when [Equation 4] and [Equation 5] are summarized, the following [Equation 6], [Equation 7].

Where c is the speed of light.

On the other hand, the position of the GEO satellite 100 at the position of the Backup TTC subsystem 130 (x _S , y _S , The distance R _b to z _S ) can be calculated by the following Equation 8.

[8] By substituting [Equation 1] and [Equation 2] into [Equation 8], in Equation 8, R _b is a function of R _P (that is, R _b = f (R _P )) And substituting it into Equation 7, Equation 7 becomes an equation for two unknowns R _P and ΔT _S.

As a result, Equations 6 and 7 are both equations of unknown R _P and ΔT _S , so this solution yields the distance from the primary TTC subsystem 120 to the GEO satellite 100. you can obtain an R _P (Ranging) and (310), by substituting it to the equation 1 can be calculated as a result the position of the GEO satellite 100, 311.

In short, the satellite positioning method consists of firstly a function of the distance (R _p ) from the main TTC subsystem to the GEO satellite, using the latitude, longitude, azimuth and elevation for the GEO satellite in the main TTC subsystem. Obtaining a coordinate point (x _S , y _S, z _S ) of a Cartesian coordinate system with respect to the position of the GEO satellite (Equation 1); Second, the backup TTC subsystem using the coordinate points (x _S , y _S, z _S ) of the GEO satellite and the coordinate points (x _b , y _b, z _b ) of the Backup TTC subsystem. Calculating the distance (R _b ) from the to GEO satellite (using Equation 8); Third, after calculating the distance (R _p ) from the main TTC subsystem to the GEO satellite using Equations (6) and (Equation 7), the GEO satellite is calculated using the distance (R _p ) to the GEO satellite. It is obtained through the process of determining the position on the coordinate of (using Equation 1 again).

The method described above is based on the primary TTC subsystem 120, ranging from the primary TTC subsystem 120 to the GEO satellite 100, the azimuth, and the elevation angle ( Elevation) was set to (R _P , A _P, E _P ), and R _P was calculated to calculate the position (x _S , y _S, z _S ) of the GEO satellite 100.

Similar to the above, with respect to the backup TTC subsystem 130, the ranging, azimuth, and elevation angles from the backup TTC subsystem 134 to the GEO satellite 100 are described. Let Elevation) be (R _b , A _b, E _b ), and calculate R _b to calculate the position (x _S , y _S, z _S ) of the GEO satellite 100.

As described above, two GEO satellite position data (x _S , y _S, z _S ) are calculated based on the primary TTC subsystem 120 and based on the backup TTC subsystem 130. Can be calculated, resulting in a more accurate position of the satellite.

As described above, the method of the present invention may be implemented as a program and stored in a recording medium (CD-ROM, RAM, ROM, floppy disk, hard disk, magneto-optical disk, etc.) in a computer-readable form. Since this process can be easily implemented by those skilled in the art will not be described in more detail.

The present invention described above is capable of various substitutions, modifications, and changes without departing from the technical spirit of the present invention for those skilled in the art to which the present invention pertains. It is not limited by the drawings.

As described above, in the present invention, a ranging signal is processed by a satellite payload by using a channel used as a satellite measurement signal without using a separate channel to transmit a ranging signal. There is no need for a function to reduce the burden on the satellite.

In addition, the present invention does not require the use of a multimodulation scheme by transmitting a satellite measurement signal (Telemetry) including a unique ranging packet of a satellite, without separately transmitting a ranging signal. It is possible to simplify the structure of the transmitting and receiving equipment of the satellite body or TTC, and also to solve the interference problem of the satellite command signal or the satellite measurement signal due to the multiple modulation.

Claims (9)

In the satellite positioning device of the TTC subsystem (Tracking, Telemetry and Command Subsystem), Receiving the satellite measurement signal TM transmitted by the geostationary orbit (GEO) satellite, and converting the satellite measurement signal (TM) including the ranging packet of the received satellite measurement signal (TM) to digital baseband TM data Baseband TM data generation means for; Reference ranging packet generation means for generating a reference ranging packet of the same type as the ranging packet inserted into the satellite measurement signal TM in the GEO satellite; Ranging packet arrival time calculating means for calculating an arrival time of the ranging packet through correlation between the digital baseband TM data and the reference ranging packet; And A first pseudo distance from the GEO satellite to the TTC subsystem calculated using the ranging packet arrival time

) And a second pseudo-range (from the Backup TTC Subsystem received from another Backup TTC Subsystem to the GEO satellite).

Calculate a distance (R _p ) from the TTC subsystem to the GEO satellite and determine the satellite position to determine the coordinate position of the GEO satellite using the distance (R _p ) to the GEO satellite. Satellite positioning means Satellite positioning device using a satellite measurement signal comprising a. The method of claim 1, The ranging packet arrival time calculating means, Correlation is performed on the digital baseband TM data and the reference ranging packet, and time mapping of a point at which a correlation value becomes a peak is used to calculate a ranging packet arrival time. Satellite positioning device using a satellite measurement signal, characterized in that. The method according to claim 1 or 2, The satellite positioning process in the satellite positioning means, Cartesian coordinate system for the position of the GEO satellite as a function of the distance (R _p ) from the TTC subsystem to the GEO satellite, using the latitude, longitude, azimuth, and elevation angle relative to the GEO satellite in the TTC subsystem. Find the coordinate points (x _S , y _S, z _S ) of, Distance (R _b ) from the backup TTC subsystem to the GEO satellite using coordinate points (x _S , y _S, z _S ) of the GEO satellite and coordinate points of the backup TTC subsystem. After calculating Equation 1 and Equation 2 are used to calculate the distance (R _p ) from the TTC subsystem to the GEO satellite, and then use the distance (R _p ) to the GEO satellite in the coordinate position of the GEO satellite. Satellite positioning device using a satellite measurement signal, characterized in that for determining. [Equation 1]

[Equation 2]

Where c is the speed of light and ΔT _S is the visual error component of the satellite. The method of claim 3, wherein The coordinate point of the Cartesian coordinate system with respect to the position of the GEO satellite is, Satellite positioning device using a satellite measurement signal to obtain by using the following equation (3). [Equation 3]

The method of claim 4, wherein The position on the coordinates of the GEO satellite is, And calculating the distance (R _p ) to the calculated GEO satellite by substituting Equation (3). A method of determining the position of a satellite applied to a TTC subsystem, Calculate a ranging PAT using the digital baseband TM data of the satellite measurement signal TM including the ranging packet received from the geostationary orbit (GEO) satellite and the reference ranging packet. A ranging packet arrival time calculating step; A first pseudo distance from the GEO satellite to the TTC subsystem using the ranging packet arrival time

Calculating a first range; Receiving the satellite measurement signal TM transmitted by the GEO satellite and calculating the second pseudo distance to the GEO satellite from the second Backup TTC subsystem via the network, the second pseudo distance (

Receiving a second range; And The distance R _p from the TTC subsystem to the GEO satellite is calculated using the first pseudo distance and the second pseudo distance, and the distance R _p to the GEO satellite is used to calculate the distance of the GEO satellite. Satellite positioning step of determining the position in coordinates Satellite positioning method using a satellite measurement signal comprising a. The method of claim 6, The ranging packet arrival time calculating step, Receiving a satellite measurement signal (TM) transmitted by the GEO satellite and converting the satellite measurement signal (TM) including a ranging packet among the received satellite measurement signals (TM) into digital baseband TM data; Generating a ranging packet inserted into the satellite measurement signal (TM) by the GEO satellite and a reference ranging packet having the same type; And Calculating an arrival time of the ranging packet through correlation between the digital baseband TM data and the reference ranging packet. Satellite positioning method using a satellite measurement signal comprising a. The method according to claim 6 or 7, The satellite positioning step, Orthogonal to the location of the GEO satellite, consisting of a function of the distance R _p from the TTC subsystem to the GEO satellite, using the latitude, longitude, azimuth, and elevation angle relative to the GEO satellite in the TTC subsystem. Obtaining coordinate points (x _S , y _S, z _S ) of the coordinate system; The distance (R _b ) from the backup TTC subsystem to the GEO satellite, using the coordinate points (x _S , y _S, z _S ) of the GEO satellite and the coordinate points of the backup TTC subsystem. Calculating c); And After calculating the distance R _p from the TTC subsystem to the GEO satellite using Equations 1 and 2, the distance R _p to the GEO satellite is used to determine the coordinates of the GEO satellite. Steps to determine location Satellite positioning method using a satellite measurement signal comprising a. The method of claim 8, The position on the coordinates of the GEO satellite is, And calculating the distance (R _p ) to the calculated GEO satellite by substituting the equation (3).

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