KR100819130B1 - Landing method - Google Patents

Abstract

A method for landing aircraft is provided to enhance the integrity of satellite navigation system by checking the integrity of a navigation receiver of the aircraft using aircraft position information and transmitting the checked content to a control office. Navigation signals of plural navigation satellites are received and navigation signals of plural pseudo satellites, which are installed at a landing route of an aircraft, are received(S401,S402). The integrity of the navigation and pseudo satellites is estimated by using the navigation signals and then the estimated result is sent to the aircraft. Aircraft position information from the aircraft is received and aircraft position information from a control office is received(S403). The integrity of a navigation receiver of the aircraft is estimated by using the aircraft position information and then the estimated result is sent to the control office(S405).

Description

How to land an aircraft {LANDING METHOD}

1 is a schematic conceptual diagram of an aircraft landing system according to an exemplary embodiment of the present invention.

2 is a block diagram showing the configuration of an aircraft landing system according to an embodiment of the present invention.

3 is a flowchart illustrating a method of landing an aircraft in a ground station according to an exemplary embodiment of the present invention.

4 is a flowchart illustrating a positioning operation in an aircraft according to an embodiment of the present invention.

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method for landing an aircraft, and more particularly, to an aircraft landing method for landing an aircraft using a satellite navigation system and topographic information.

The study of the satellite navigation system, which began with the Pentagon's partial opening of GPS (Global Positioning System) signals to the private sector, is now in commercialization. Various receivers exist and are widely used in various fields such as vehicles and aircrafts.

However, navigation satellites cannot be used in areas where satellite signals are blocked or areas where navigation signal errors are large. In particular, high integrity of the navigation satellite system is required in areas requiring high precision such as landing of aircraft, and if it is not secured, the navigation satellite may not be used for future automatic landing.

When the GPS, which is the current satellite navigation system, is used alone, the horizontal accuracy is around 20 m. However, when the DGPS (Differential Global Positioning System) for error correction is used, accurate positioning of several m units is possible.

As a precision positioning technique using DGPS in the aerospace field, a local area Augment System (LAAS) and a wide area Augment System (WAAS) are used. In particular, in order to improve the navigation performance near the airport, LAAS is currently used as a basic concept. LAAS is a DGPS method that corrects the included error when receiving GPS data, and has been proposed in aviation navigation. The LAAS generates an error correction value from GPS data and transmits it.

However, LASS does not warn users of malfunctions in real time by checking each other's system operation. Therefore, there is a problem in reliability of the system itself, and when such a problem occurs, the satellite navigation system cannot be used for landing an aircraft. That is, the prior art cannot check the integrity of the aircraft, and it is difficult to guarantee automatic landing unless the integrity of the aircraft is guaranteed.

Therefore, it is necessary to improve the integrity of the satellite navigation system for the automatic landing of the aircraft in the future. In addition, in the case of an aircraft, a large amount of human life and property damage is concerned when an accident occurs, so a system that requires high precision and significantly improves the integrity of the satellite navigation system is required.

The technical problem to be achieved by the present invention is to provide a method of landing an aircraft using a satellite navigation system and terrain information.

In addition, an object of the present invention is to improve the integrity of the satellite navigation system by using pseudo-satellite information, topographical information, and aircraft location information when landing the aircraft.

In order to solve this problem, according to the present invention, to implement the aircraft landing method and system to perform integrity monitoring (Monitering) based on the communication between the pseudo-satellite and the aircraft during landing. In this case, the present invention improves the performance of the navigation system of the aircraft by using information of pseudo satellites, terrain information, aircraft position information, and the like, and utilizes it in landing information of the aircraft.

In addition, the present invention provides a navigation system used to land the aircraft by accurately confirming the position of the user, accurately determine the position of the aircraft based on the signal from the navigation satellite and whether or not there is an error in the position information calculated in the aircraft Determination improves the integrity of the navigation system. In addition, the present invention not only uses the information of the navigation satellite, but also improves the precision of the position of the aircraft by using additional information (ie, information of pseudo-satellite, terrain information, aircraft position information, etc.) to the extent that automatic landing is possible. Ensure precision.

According to an aspect of the present invention, in a method for landing an aircraft at a ground station, receiving a plurality of navigation signals of a navigation satellite and receiving a plurality of pseudo-satellite navigation signals installed on a landing path of the aircraft, Checking the integrity of the navigation satellite and pseudosatellite using a navigation signal, notifying the aircraft of a test result, receiving aircraft position information from the aircraft, and receiving aircraft position information of a control station; and Inspecting the integrity of the navigation receiver of the aircraft using the aircraft location information, and providing the aircraft landing method comprising the step of notifying the control station.

The notifying of the inspection result to the aircraft comprises: detecting a fault satellite by analyzing a navigation signal of the navigation satellite and a navigation signal of the pseudo satellite, and a navigation signal of the navigation satellite and a navigation signal of the pseudo satellite. Comparing the step of generating error correction information, and transmitting the error correction information with the topographic information around the airport to the aircraft. The notifying of the inspection result to the control station may include determining whether the position of the aircraft is correct by comparing the aircraft position information of the aircraft with the aircraft position information of the control station, and accurately determining the position of the aircraft. If yes, determining whether the aircraft has landed automatically, and transmitting the determined automatic landing to the control station.

And the aircraft landing method further comprises the step of calculating the position of its own using the inspection result of the ground station in the aircraft, and transmitting the calculated aircraft position information to the ground station.

And the aircraft landing method further comprises the step of transmitting to the aircraft the status information on whether the landing permission of the aircraft on the basis of the inspection result of the ground station in the control station.

According to another aspect of the present invention, in a method of landing and landing its own position in the aircraft, receiving a plurality of navigation satellite navigation signals, and receiving a plurality of pseudo-satellite navigation signals installed on the landing path of the aircraft Receiving an error correction information on the navigation signal from a ground station, calculating the position of the aircraft itself using the navigation signal and the error correction information together with information of its own navigation sensor, and calculating the aircraft It provides a method for landing the aircraft comprising the step of transmitting the location information to the ground station.

The calculating of the position of the aircraft itself may include receiving terrain information around an airport from the ground station together with the error correction information, and not only the navigation signal and the error correction information but also the terrain information. Calculating the position of the aircraft itself with the information of the sensor.

According to still another aspect of the present invention, in a system for landing an aircraft using navigation signals of a plurality of navigation satellites, a plurality of pseudo satellites installed in a landing path of the aircraft to generate and transmit a navigation signal, A control station that transmits the position information of the aircraft, transmits the status information of the landing permission of the aircraft to the aircraft, and checks the integrity of the navigation satellite and pseudosatellite using the navigation signal, and the aircraft position It provides an aircraft landing system including a ground station that uses the information to check the integrity of the navigation receiver of the aircraft and notify the control station.

Here, the ground station compares the navigation signal of the navigation satellite and the navigation signal of the pseudo satellite to generate error correction information, and transmits the error correction information to the aircraft along with the terrain information around the airport, and the aircraft of the aircraft. The location information is compared with the aircraft location information of the control station to determine whether the location of the aircraft is correct, to determine whether or not the automatic landing of the aircraft, and transmits the determined automatic landing or not to the control station. In addition, the aircraft calculates the position of the aircraft itself by using the navigation signal of the navigation satellite, the navigation signal of the pseudo satellite, error correction information and terrain information of the ground station together with information of its own navigation sensor. The aircraft position information is transmitted to the ground station.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings so that those skilled in the art may easily implement the present invention. As those skilled in the art would realize, the described embodiments may be modified in various different ways, all without departing from the spirit or scope of the present invention. In the drawings, parts irrelevant to the description are omitted for simplicity of explanation, and like reference numerals designate like parts throughout the specification.

Throughout the specification, when a part is said to "include" a certain component, it means that it can further include other components, except to exclude other components unless otherwise stated. In addition, the terms “… unit”, “… unit”, “… module” described in the specification mean a unit that processes at least one function or operation, which may be implemented by hardware or software or a combination of hardware and software. Can be.

Now, the aircraft landing method and system according to an embodiment of the present invention will be described in detail with reference to the accompanying drawings.

1 is a conceptual diagram of an aircraft landing system using a satellite navigation system according to an embodiment of the present invention.

As shown in FIG. 1, an aircraft landing system using a satellite navigation system according to an embodiment of the present invention includes a plurality of navigation satellites 101 to 104, a plurality of pseudo satellites 105 to 108, a ground station 109, Control station 110, aircraft 111, runway 112. Here, the ground station 109 and the control station 110 exchanges the information of the aircraft 111 and drives closely, comparing the position of the aircraft 111 and generates a warning message when the error range exceeds the available value Immediately deliver to aircraft 111.

In the aircraft landing system using the satellite navigation system according to an embodiment of the present invention, a carrier wave carrying a navigation data message using the same frequency and code as that of the pseudo satellites 105 to 108 are also transmitted from the navigation satellites 101 to 104. It transmits a signal so that the aircraft 111 near the airport can receive it, and also increases the available navigation data message with more pseudo satellites in addition to the pseudo satellites 105 to 108 shown in FIG. There is a number. At this time, the aircraft landing system using the satellite navigation system according to an embodiment of the present invention, to further use the terrain information in the position measurement in order to determine the exact position of the aircraft (111).

In addition, the aircraft landing system using the satellite navigation system according to an embodiment of the present invention is a navigation system with increased integrity, and integrity of navigation data messages transmitted from the pseudo satellites 105 to 108 not only in the aircraft 111 but also near the airport. The ground station 109 that measures the signal to be received at the same time. Accordingly, in the aircraft landing system using the satellite navigation system according to the embodiment of the present invention, the ground station 109 combines the navigation data messages of the pseudo satellites 105 to 108 with the navigation data messages of the navigation satellites 101 to 104. The correction information is generated and transmitted to the aircraft 111. Accordingly, in the aircraft landing system using the satellite navigation system according to the embodiment of the present invention, the aircraft 111 transmits the position information calculated by using the correction information back to the ground station 109, and the ground station 109 manages it. After checking the integrity of the navigation receiver of the aircraft 111 by combining the aircraft position identified by the empire 110 and the aircraft position received from the aircraft 109, the check result information (ie, integrity information) is stored in the control station 110. In order to determine whether to automatically land the aircraft 111 by notifying the information), it is possible to secure the precision enough to enable automatic landing.

The navigation satellites 101 to 104 transmit a carrier signal carrying a navigation data message (hereinafter referred to as a navigation satellite signal) to the ground station 109 and the aircraft 111 near the airport.

Pseudosatellite (105 ~ 108) is installed in the landing path of the aircraft 111 and serves to increase the visible satellite to measure the exact position, and generates the same navigation signal as the navigation satellite (101 ~ 104). In other words, the pseudo satellites 105 to 108 are carrier signals carrying navigation data messages using the same frequency and code as the navigation satellite signals transmitted from the navigation satellites 101 to 104 (hereinafter, referred to as pseudo satellite signals). To the ground station 109 and the aircraft 111 near the airport.

The ground station 109 examines the navigation signals (i.e., the navigation satellite signals and the pseudo-satellite signals) received from the navigation satellites 101 to 104 and the pseudo satellites 105 to 108, and then the navigation satellites 101 to 104 and the pseudo satellite ( 105 to 108 to check the integrity, and transmits the test result (ie, integrity information) to the aircraft 111, and also transmits the topographical information near the airport to the aircraft 111 at the same time. At this time, the integrity of the ground station 109, navigation satellite signal, pseudo-satellite signal and the like are used for the integrity check. In addition, using the navigation signals of the pseudo satellites 105 to 108 is more effective in the integrity check than in the case of using only the navigation signals of the navigation satellites 101 to 104. The ground station 109 then evaluates the reliability of the navigation information of the navigation receiver of the aircraft 111 with the aircraft position received from the aircraft 111 and the aircraft position received from the control station 110. Then, the ground station 109 transmits this information (i.e., reliability evaluation information) to the control station 110 when there is no error component in the navigation information of the navigation receiver.

The control station 110 grasps the position of the aircraft 111 and transmits it to the ground station 109, and receives reliability evaluation information from the ground station 109 to receive information such as an automatic landing permission of the aircraft 111 (that is, a situation notification). Information) to the aircraft 111. In addition, the control station 110 may permit the automatic landing of the aircraft 111 to ensure the safety of the aircraft 111.

When the aircraft 111 approaches the airport (ie, the runway 112), the aircraft 111 receives not only the navigation signals of the navigation satellites 101 to 104 but also the navigation signals of the pseudo satellites 105 to 108, and receives the received navigation signals (i.e. The aircraft's position is determined using the navigation satellite signal and the pseudo-satellite signal. In this case, the navigation signal available in the aircraft 111 includes navigation signals of other pseudo satellites in addition to the navigation signals of the pseudo satellites 105 to 108, and when the number of available satellites increases, the accuracy of the navigation system is improved as much. .

The aircraft 111 calculates a more accurate position by correcting the navigation signals of the navigation satellites 101 to 104 and the pseudo satellites 105 to 108 using the integrity information received from the ground station 109, and also calculates the ground station 109. Calculate the position accuracy by using the topographic information. Thereafter, the aircraft 111 transmits its location information to the ground station 109 (or the control station 110). Here, it should be understood that the aircraft 111 not only performs correction of navigation signals by simply receiving the corrected information, but also verifies the integrity of the aircraft itself by transmitting its information to the ground station 109. .

2 is a block diagram showing the configuration of an aircraft landing system according to an embodiment of the present invention.

As shown in FIG. 2, an aircraft landing system according to an embodiment of the present invention includes N four satellites 201-1 generating and broadcasting a navigation signal (hereinafter, referred to as a pseudo-satellite signal) on the ground. 201-N), N navigation satellites 202-1 to 202-N generating and broadcasting actual navigation signals (hereinafter referred to as navigation satellite signals), and satellites 201-1 to 201-N and 202. Ground station 203 for monitoring the navigation signal of -1 to 202-N), transmitter 204 for transmitting error correction information and terrain information, receiver 205 for receiving position information of aircraft 206, aircraft 206 And control station 207. Here, during landing of the aircraft 206, each component reacts closely with each other to assist in landing of the aircraft 206.

And the precise aircraft landing system according to an embodiment of the present invention, to ensure the precise navigation system by performing the following integrity test operation. First, test the integrity of visible satellites near the airport. Second, in order to increase the number of visible satellites, a plurality of pseudo satellites 201-1 to 201-N are introduced, and pseudo satellites 201-1 to 201-N and navigation satellites (202-1 to 202-N). Select fault satellite using navigation signal of Since the pseudo-satellite 201-1-201-N and the ground station 203 know the exact position in the fault screening operation, detecting the faulty satellite uses only the navigation signals of the navigation satellites 202-1-202-N. The accuracy can be further improved than in the case. In addition, by analyzing the navigation signals of the pseudo-satellite (201-1 ~ 201-N) and navigation satellites (202-1 ~ 202-N) to generate the correction data corrected for various errors based on their position, The correction data is used as the reference value for the error occurrence term. Thus, the calculated values and the terrain data are transmitted to the aircraft 206, and the aircraft 206 obtains a correction position based on these contents. Third, the integrity of the navigation receiver of the aircraft 206 is ensured by transmitting the navigation signal of the aircraft 206 back to the ground (ie, ground station 203). At this time, the ground station 203 checks the integrity by using the signal of the aircraft 206 and the information of the control station 207, and the integrity for the landing of the aircraft is guaranteed when all of these series of operations match. In addition, the accuracy of such aircraft position is improved and can be used for automatic aircraft landing.

Pseudo-satellite 201-1-201-N broadcasts navigation signals similar to navigation satellites 202- 1-202-N, and improves the integrity and precision of navigation signals. At this time, the number of pseudo-satellite 201-1 ~ 201-N can be installed in consideration of the terrain characteristics of the airport, and if there is no significant difference in the terrain information of the airport, a virtual feature is installed to refer to the feature. This can determine the position of the aircraft 206. In addition, as the number of pseudo satellites 201-1 to 201 -N increases, the number of visible satellites increases to enable more accurate position measurement.

The ground station 203 checks the integrity information by monitoring the pseudo satellite signals received from the pseudo satellites 201-1 to 201 -N and the navigation satellite signals received from the navigation satellites 202-1 to 202-N. Detects the fault satellite and examines the navigation signals received from each of the satellites 201-1 to 201-N and 202-1 to 202-N to generate error correction information. That is, the ground station 203 receives several channels of navigation signals (i.e., pseudo satellite signals and navigation satellite signals) from the pseudo satellites 201-1 to 201-N and the navigation satellites 202-1 to 202-N. The controller analyzes the received navigation signal and generates correction data correcting various errors based on its position. In addition, the ground station 203 transmits the generated correction data to the transmitter 204 together with the topographical information around the airport, and then collects the position information of the aircraft 206 through the receiver 205 and collects the information of the aircraft 206. The location information and the information of the control station 207 are compared with each other, and the result of the comparison is transmitted to the control station 207.

The transmitter 204 transmits the correction data generated at the ground station 203 to the aircraft 206 along with the topographic information around the airport received from the ground station 203.

The receiver 205 receives the information calculated by the aircraft 206 (ie, aircraft position information) and transmits the information back to the ground station 203.

The aircraft 206 calculates its position using the calibration data received from the transmitter 204 and its satellite navigation system, and also receives the topographic information around the airport from the transmitter 204 to view its position. Used to calculate precisely. Here, the aircraft 206 calculates its position more precisely by using its own navigation sensor and terrain information, and transmits the calculated aircraft position information to the receiver 205.

The control station 207 transmits the position information of the aircraft 206 to the ground station 203, and permits the automatic landing of the aircraft 206 based on the information compared by the ground station 203. For example, the control station 207 notifies the aircraft 206 of the failure of the navigation system of the aircraft 206.

Hereinafter, a method of landing an aircraft in a ground station according to an embodiment of the present invention will be described in detail with reference to FIG. 3.

3 is a flowchart illustrating a method for landing an aircraft for improving the integrity of a ground station according to an exemplary embodiment of the present invention.

As shown in FIG. 3, the automatic takeoff and landing of the aircraft 26 requires high precision and requires very high integrity in that it leads to a large accident when an error occurs, so the embodiment of the present invention uses satellites. It is well understood that the integrity of the navigation system should be improved to ensure reliability during the automatic takeoff and landing of the aircraft 206. In addition, the embodiment of the present invention uses the terrain information to reduce the vertical error of the aircraft 206, by introducing a number of pseudo-satellite (201-1 ~ 201-N) multiplexing effect in case of failure occurs Consider.

First, a plurality of navigation satellites 202-1 to 202-N generate a carrier signal carrying a real navigation data message (hereinafter referred to as a navigation satellite signal) and transmit it to the ground station 203 near the airport.

In order to increase the visible satellites and to accurately measure the position, a plurality of pseudo satellites 201-1 to 201 -N are installed in the landing path of the aircraft 206. That is, as the number of pseudo satellites 201-1 to 201 -N increases, the number of visible satellites increases to enable more accurate position measurement, thereby improving the integrity and precision of the navigation signal.

Accordingly, similar to the navigation satellites 202-1 to 202-N, the pseudo satellites 201-1 to 201-N also have the same frequency as the navigation satellite signals transmitted by the navigation satellites 202-1 to 202-N. A carrier signal (hereinafter, referred to as a pseudo-satellite signal) carrying a navigation data message on the ground is generated using a and code and transmitted to the ground station 203.

Accordingly, as shown in FIG. 3, the ground station 203 receives a pseudo-satellite signal from the pseudo satellites 201-1 to 201-N in order to improve the integrity (S301), and also the navigation satellite 202-1. 202-N) a navigation satellite signal is received (S302).

The ground station 203 monitors the pseudo satellite signals received from the pseudo satellites 201-1 to 201 -N and the navigation satellite signals received from the navigation satellites 202-1 to 202-N. 201-N) and the integrity of the navigation satellites 202-1 through 202-N, and transmits the result of the inspection (ie, integrity information) to the aircraft 206.

In this case, the integrity check is more useful to use the navigation signals of the pseudo satellites 201-1 to 201 -N rather than the navigation signals of the navigation satellites 202-1 to 202-N. Various types of verification are also possible by using the navigation signals of the pseudo satellites 201-1 to 201-N as well as the navigation signals of 1 to 202-N. This compares the navigation signals of the navigation satellites 202-1 to 202-N with the navigation signals of the pseudo satellites 201-1 to 201-N and uses them for integrity verification. In addition, increasing the number of visible satellites (ie, pseudolites 201-1-201 -N) is also very useful for integrity monitoring of the ground station 203.

This integrity verification can be more useful when a large number of error terms are attached to the navigation signals of navigation satellites 202-1 to 202-N, and virtual features are used when there is no special feature because the plane is near the airport. Based on the feature, the altitude of the aircraft 206 can be accurately identified and a precise position error can be determined.

In other words, the ground station 203 detects a fault satellite by analyzing navigation signals of various channels received from each of the satellites 201-1 to 201 -N and 202-1 to 202 -N. In addition, the ground station 203 checks the navigation signals (i.e., pseudo-satellite signals and navigation satellite signals) received from the pseudo satellites 201-1 to 201-N and the navigation satellites 202-1 to 202-N. The correction information is generated (S303). At this time, the ground station 203 generates correction data correcting various errors based on its position.

The ground station 203 transmits the correction data generated in the above-described step S303 to the transmitter 204 together with the topographic information around the airport (that is, the ground topographical information), and the transmitter 204 from the ground station 203. The applied error correction information and the terrain information is transmitted to the aircraft 206 (S304).

The aircraft 206 then uses the integrity information (ie, error correction information) received from the ground station 203 from the pseudosatellite 201-1-201-N and the navigation satellites 202- 1-202-N. Compensate the received navigation signals (ie pseudo-satellite signal and navigation satellite signal) to calculate a more accurate position. In addition, the aircraft 206 calculates its position using the terrain information received from the ground station 203 to increase its own position accuracy. The aircraft 206 then sends its calculated location information to the receiver 205.

Accordingly, the receiver 205 receives the aircraft position information calculated by the aircraft 206 and transmits it to the ground station 203 again. At this time, the control station 207 also grasps the position of the aircraft 206 and transmits it to the ground station 203.

Accordingly, the ground station 203 collects the aircraft position information through the receiver 205 and at the same time receives the aircraft position information from the control station 207 (S305), and compares the received aircraft position information with each other to compare the aircraft ( The reliability of the navigation information of the navigation receiver of 206 is evaluated.

In other words, the ground station 203 determines whether the position of the aircraft 206 is correct based on the aircraft position information received from the aircraft 206 and the data received from the control station 207 (that is, the aircraft position information) ( S306).

At this time, when the position of the aircraft 206 is correctly determined in the above-described step S306, the ground station 203 determines whether or not the automatic landing (S307), and the corresponding determination contents (that is, the status notification of the aircraft 206) It transmits to the control station 207 (S308).

Thus, the control station 207 permits the automatic landing of the aircraft 206 based on the information compared in the ground station 203.

In addition, the series of operation processes as described above are performed periodically, and when an abnormality occurs in the operation process, the ground station 203 immediately transmits a command to the control station 207 to prohibit automatic landing.

Next, a positioning operation in an aircraft according to an embodiment of the present invention will be described in detail with reference to FIG. 4.

4 is a flowchart illustrating a positioning operation in an aircraft according to an embodiment of the present invention.

First, a plurality of navigation satellites 202-1 to 202-N generate a carrier signal carrying a real navigation data message (hereinafter referred to as a navigation satellite signal) and transmit it to an aircraft 206 near an airport.

In addition, similar to the navigation satellites 202-1 to 202-N, the plurality of pseudo satellites 201-1 to 201-N have the same frequency as the navigation satellite signals transmitted by the navigation satellites 202-1 to 202-N. A carrier signal (hereinafter, referred to as a pseudo-satellite signal) carrying a navigation data message on the ground is generated using and codes and transmitted to the aircraft 206.

The ground station 203 monitors the navigation signals (i.e., pseudo-satellite signals and navigation satellite signals) received from the pseudo satellites 201-1 to 201-N and the navigation satellites 202-1 to 202-N. Error correction information is generated by checking the integrity of the 201-1 to 201-N and the navigation satellites 202-1 to 202-N, and the generated error correction information is used to determine the topographic information around the airport (ie, the feature information). Together with the transmitter 204 to the aircraft 206. At this time, the ground station 203 not only generates the feature information as the information on the positioning of the aircraft 206, but also generates more virtual features as needed to make it more useful for positioning the aircraft 206. Help.

Accordingly, as shown in FIG. 4, the aircraft 206 receives a pseudo-satellite signal from the pseudo satellites 201-1 to 201-N to improve integrity (S401) and the navigation satellite 202-1. 202-N) a navigation satellite signal is received (S402). In addition, the aircraft 206 receives integrity information (ie, error correction information) and terrain information from the ground station 203 through the transmitter 204 (S403).

Accordingly, the aircraft 206 detects its position using the error correction information received through the transmitter 204 and its satellite navigation system. At this time, the aircraft 206 calculates a more accurate aircraft position using the topographic information around the airport received through the transmitter 204 (S404).

In other words, the aircraft 206 receives not only the navigation satellite signals received from the navigation satellites 202-1 through 202-N when approaching the airport, but also the pseudo-satellite signals received from the pseudo satellites 201-1 through 201-N. And, using the topographic information around the airport received by the transmitter 204 with its own navigation sensor (eg, altimeter, etc.) to determine the position of the aircraft more precise through integrity check. At this time, the navigation signal available to the aircraft 206 is a pseudo-satellite signal received from other pseudo-satellite in addition to the navigation signals of the navigation satellites (202-1 ~ 202-N) and pseudo-satellite (201-1 ~ 201-N). Include. It can be seen that as the number of available satellites increases, the accuracy of the navigation system increases as much.

The use of the feature information of the ground station 203 in the aircraft 206 is to predict the route of the aircraft 206 by measuring the speed and position of the aircraft 206 against the feature map to measure the precise position. .

Thereafter, the aircraft 206 transmits the aircraft position information calculated in the above-described step S404 to the ground station 203 through the receiver 205 (step S405). The ground station 203 then receives the aircraft position information from the aircraft 206 to check the integrity of the navigation receiver of the aircraft 206.

As such, the various information as described above is used to test the integrity of the satellite navigation system, which is not only the integrity of each satellite 201-1-201-N, 202-1-202-N, Integrity is also an important factor. Accordingly, the aircraft 206 receives the navigation satellite signal and the pseudo-satellite signal and measures the precise position by using the altimeter and the feature data of the aircraft. In addition, the aircraft 206 corrects the position information calculated using the correction data transmitted from the ground station 203, and transmits the integrity of the aircraft receiver by transmitting it to the ground station 203 in order to confirm the precise position measurement result again. Check it.

In the above, the embodiment of the present invention has proposed a method and system for enabling automatic takeoff and landing of the control station 207, the ground station 203, and the aircraft 206 by organic action. In addition, an embodiment of the present invention has been described to improve the availability of the satellite by increasing the number of visible satellites, and to determine the automatic landing by checking the integrity of the aircraft receiver to enable active error correction rather than passive error correction. .

In addition, the embodiment of the present invention is not implemented only through the above-described apparatus and / or method, but through a program for realizing a function corresponding to the configuration of the embodiment of the present invention, a recording medium on which the program is recorded, and the like. Such implementations may be readily implemented by those skilled in the art from the description of the above-described embodiments.

Although the embodiments of the present invention have been described in detail above, the scope of the present invention is not limited thereto, and various modifications and improvements of those skilled in the art using the basic concepts of the present invention defined in the following claims are also provided. It belongs to the scope of rights.

Thus, according to an embodiment of the present invention, by using a plurality of pseudo-satellite, topographical information, and aircraft location information when landing the aircraft, to improve the availability of the satellite, improve the accuracy of the aircraft position and improve the integrity of the satellite navigation system This improves reliability during automatic landing of the aircraft.

Claims (11)

In the ground station to land the aircraft, Receiving navigation signals of a plurality of navigation satellites, and receiving navigation signals of a plurality of pseudo satellites installed in a landing path of the aircraft; Checking the integrity of the navigation satellite and the pseudo-satellite using the navigation signal, and notifying the aircraft of a test result; Receiving aircraft position information from the aircraft, receiving aircraft position information of a control station, and Checking the integrity of the navigation receiver of the aircraft using the aircraft position information, and notifying the control station of the inspection result; Aircraft landing method comprising a. The method of claim 1, And the navigation signal is a carrier signal carrying a navigation data message. The method of claim 1, Informing the aircraft of the inspection result, Monitoring the navigation signal of the navigation satellite and the navigation signal of the pseudo satellite; Verifying the integrity by comparing the navigation signal of the navigation satellite with the navigation signal of the pseudo satellite; and Transmitting the result of the integrity verification to the aircraft Aircraft landing method comprising a. The method of claim 1, Informing the aircraft of the inspection result, Detecting fault satellites by analyzing the navigation signals of the navigation satellites and the navigation signals of the pseudo satellites; Generating error correction information by comparing the navigation signal of the navigation satellite and the navigation signal of the pseudo satellite; Transmitting the error correction information to the aircraft together with the topographic information around the airport. Aircraft landing method comprising a. The method of claim 4, wherein And the error correction information is correction data obtained by correcting an error based on the position of the ground station itself. The method of claim 1, And calculating the position of the ground station using the inspection result of the ground station in the aircraft, and transmitting the calculated aircraft position information to the ground station. The method of claim 1, Notifying the control station of the test result, Comparing the aircraft position information of the aircraft with the aircraft position information of the control station to determine whether the position of the aircraft is correct; Determining whether the aircraft lands automatically when the position of the aircraft is correctly determined; and Transmitting the determined automatic landing to the control station. Aircraft landing method comprising a. The method of claim 7, wherein Notifying the control station of the test result, If the position of the aircraft is not correctly determined, sending a command to prohibit automatic landing to the control station. The method of claim 1, And transmitting, by the control station, the situation information on the landing permission of the aircraft to the aircraft based on the inspection result of the ground station. In the method of landing and landing his position on the aircraft, Receiving navigation signals of a plurality of navigation satellites, and receiving navigation signals of a plurality of pseudo satellites installed in a landing path of the aircraft; Receiving error correction information on the navigation signal from a ground station; Calculating the position of the aircraft itself using the navigation signal and the error correction information together with information of its own navigation sensor, and Transmitting the calculated aircraft position information to the ground station. Aircraft landing method comprising a. The method of claim 10, Computing the position of the aircraft itself, Receiving terrain information around an airport from the ground station together with the error correction information; and Calculating the position of the aircraft itself using the terrain information as well as the navigation signal and the error correction information together with the information of the own navigation sensor; Aircraft landing method comprising a.

Images