KR102420984B1 - Method for analyzing performance of gps antenna and method for determining install location of gps antenna of aircraft - Google Patents

Abstract

The present invention relates to a performance analyzing method and a mounting location determining method of an aircraft GPS antenna. More specifically, provided are the performance analyzing method and a mounting location determining method of a GPS antenna mounted on an aircraft. According to an embodiment of the present invention, the performance analyzing method of an aircraft GPS antenna is the performance analyzing method of a GPS antenna mounted on an aircraft, which may include a process of reverse-engineering the GPS antenna to be mounted on the aircraft, and a process of analyzing the performance of the GPS antenna by simulating a case where the reverse-engineered GPS antenna is mounted on the aircraft.

Description

Method for analyzing the performance of an aircraft GPS antenna and determining the mounting location

The present invention relates to a method for analyzing the performance of an aircraft GPS antenna and a method for determining a mounting position, and more particularly, to a method for analyzing the performance of a GPS antenna mounted on an aircraft and a method for determining a mounting position.

Along with the rapid development of aircraft electronic equipment, the demand related to aircraft modification to improve the performance of existing aircraft communication equipment or navigation equipment is continuously increasing. In particular, due to the specificity of military operation, strengthening the secret function of aircraft electronic equipment and securing anti-jamming performance are the biggest issues.

Recently, in order to relieve the limitation of Mode 4 operation of Identification Friend or Foe (IFF) equipment for distinguishing between the enemy and the friendly forces and to improve the performance of the ROK-U.S. joint operation, Mode 5 (Mode 5) with enhanced secret function ) to improve the performance of peer identification equipment and to develop anti-jamming GPS (Global Positioning System) projects to escape from the increase in the threat of jamming. In addition, public communication radio performance improvement by replacing the existing analog hopping method UHF (Ultra High Frequency) radio with SATURN (Second Generation Anti-jam Tactical UHF Radio for NATO) radio, a digital communication method with enhanced anti-jamming and security functions The business is also active.

For smooth transmission and reception of electronic equipment between aircraft performance improvement, RF signal radiation is very important, and performance analysis considering the impact of aircraft structure and other RF equipment is essential. When the international standards for RF performance are not met due to the performance limitations of antennas developed 20 to 30 years ago, or when the existing antenna operation is limited and additional antenna installation is required, the optimal location of the antenna becomes a very important design factor. Accordingly, in addition to analyzing the structural integrity and aerodynamics of the antenna mounted on the outside of the aircraft, an overall design that minimizes the interference between the pre-installed antenna and the communication navigation equipment interworking should be carried out. In particular, the analysis of the influence of interference between equipment according to the antenna mounting position at the design time must be preceded along with the radiation pattern analysis. However, until now, the provision of information from the original aircraft and equipment manufacturers has been limited in the process of aircraft performance improvement, so derivation of the optimal antenna location through systematic analysis at the time of design has been limited. There was a problem in that manpower and cost were required.

US 10-1559933 B1

The present invention provides a method for analyzing the performance of an aircraft GPS antenna and a method for determining a mounting position, which can be applied to a remodeling business of an aircraft.

A method for analyzing the performance of an aircraft GPS antenna according to an embodiment of the present invention is a method for analyzing the performance of a GPS antenna mounted on an aircraft, the method comprising: reverse engineering a GPS antenna to be mounted on an aircraft; and a process of analyzing the performance of the GPS antenna by simulating a case in which the reverse-engineered GPS antenna is mounted on the aircraft.

In addition, the method for determining the mounting position of an aircraft GPS antenna according to an embodiment of the present invention is a method for determining a mounting position of a GPS antenna for determining a position for mounting a GPS antenna on an aircraft, comprising reverse engineering a GPS antenna to be mounted on an aircraft process; determining a preliminary location for mounting the GPS antenna on the aircraft; analyzing the performance of the GPS antenna by simulating a case in which the reverse-engineered GPS antenna is mounted in the preliminary position; and determining the preliminary position as a position for mounting the GPS antenna when the analyzed performance of the GPS antenna satisfies a setting condition.

The reverse engineering of the GPS antenna may include: measuring performance of the GPS antenna; designing the GPS antenna; and comparing the performance of the designed GPS antenna with the measured performance of the GPS antenna, and modeling the GPS antenna.

In the process of measuring the performance of the GPS antenna, a reflection coefficient and a radiation pattern of the GPS antenna may be measured.

The designing of the GPS antenna may include: acquiring external information of the GPS antenna; and acquiring internal structural information of the GPS antenna, wherein the acquiring of internal structural information of the GPS antenna includes capturing the GPS antenna with X-rays to obtain internal structural information of the GPS antenna. can

The modeling of the GPS antenna may include adjusting a shape of a GPS antenna designed to match the measured performance of the GPS antenna.

The process of determining the preliminary position is to analyze at least one of a cable structure connected to the GPS antenna, a change in aerodynamic coefficient depending on whether the GPS antenna is mounted, and structural soundness according to the installation of the GPS antenna, to install the GPS antenna. The process of identifying a plurality of possible locations; and determining at least one of the identified plurality of positions as the preliminary position.

The GPS antenna may include at least one reception antenna, and the process of determining the preliminary position may determine a preliminary position in which at least one reverse-engineered reception antenna will be mounted.

The process of analyzing the performance of the GPS antenna may include: analyzing a radiation pattern of the GPS antenna at the preliminary location; and analyzing whether there is interference between the GPS equipment including the GPS antenna and the avionics equipment mounted on the aircraft.

The avionics equipment includes the transmitting equipment, and in the process of analyzing the interference, if the final received power value of the GPS equipment calculated by Equation 1 below is less than the lowest reception sensitivity, it can be analyzed that there is no interference. .

[Equation 1]

(where TTP is the final received power value of the GPS device, TP is the transmission output of the transmitting device, TFR is the internal filter attenuation value of the transmitting device, SG is the GPS spreading gain, and S _21(R) is the transmission coefficient in the GPS band. it means.)

The method may further include a process of reanalyzing the performance of the GPS antenna by changing the preliminary location among the plurality of locations when the analyzed performance of the GPS antenna does not satisfy the setting condition.

According to the method for analyzing the performance of an aircraft GPS antenna and the method for determining the mounting position according to an embodiment of the present invention, the performance of the GPS antenna is effectively analyzed during the aircraft remodeling project, and structural problems and RF interference between equipment do not occur. The mounting location can be determined.

1 is a view showing a position where an antenna and a sensor are mounted on an aircraft;
2 is a diagram schematically illustrating a method for analyzing performance of an antenna according to an embodiment of the present invention;
3 is a diagram schematically illustrating a method for determining a mounting position of an antenna according to an embodiment of the present invention.
4 is a view showing an overview for analyzing whether interference between a transmitting device and a receiving device.
5 is a diagram showing a result of reverse design of an antenna;
6 is a view showing a position in which an antenna can be mounted on an aircraft;
7 is a view showing a radiation pattern of an antenna mounted on an aircraft.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below, but will be implemented in various different forms, and only the embodiments of the present invention allow the disclosure of the present invention to be complete, and the scope of the invention to those of ordinary skill in the art It is provided to fully inform In order to explain the invention in detail, the drawings may be exaggerated, and like reference numerals refer to like elements in the drawings.

In order to additionally install an antenna on an existing aircraft, that is, a legacy aircraft, it is essential to secure structure and cable interlocking and RF performance. Structural soundness such as aerodynamics, vibration, and dynamic analysis according to the antenna installation and optimization of the RF cable route inside the aircraft should be preceded. In addition, it is necessary to design the antenna in an optimal position where radiation pattern performance for RF transmission and reception is satisfied and occurrence between equipments through a pre-installed antenna does not occur.

1 is a view showing a position where an antenna and a sensor are mounted on an aircraft.

As exemplarily shown in FIG. 1 , various antennas and sensors such as a navigation and radar sensor dedicated to communication for RF transmission and reception and reception from a peer identification antenna may be mounted on an air force transport aircraft as illustrated in FIG. 1 . The antenna and the sensor each have independent RF lines, and it is necessary to derive the optimal position of the antenna to be mounted in consideration of the communication navigation system and the antenna.

2 is a diagram schematically illustrating a method for analyzing the performance of an antenna according to an embodiment of the present invention, and FIG. 3 is a diagram schematically illustrating a method for determining a mounting position of an antenna according to an embodiment of the present invention.

2 and 3 , the method for analyzing the performance of an antenna according to an embodiment of the present invention is a method for analyzing the performance of an antenna to be mounted on an aircraft. and a process of analyzing the performance of the antenna by simulating the case where the antenna is mounted on the aircraft (S300).

On the other hand, the method for determining the mounting position of an antenna according to an embodiment of the present invention is a method for determining a mounting position of an antenna for determining a position for mounting an antenna on an aircraft, the process of reverse engineering an antenna to be mounted on an aircraft (S100); The process of determining the preliminary position for mounting the antenna in the aircraft (S200), the process of analyzing the performance of the antenna by simulating the case where the reverse engineered antenna is mounted in the preliminary position (S300), and the analyzed performance of the antenna is set When the condition is satisfied, the process of determining the preliminary position as a position for mounting the antenna (S400) may be included.

Here, the antenna may be a wireless communication antenna having both a transmission function and a reception function, and such a wireless communication antenna is a peer identification device for identifying a friend or a radio equipment for exchanging information between friendly forces, for example, a public communication radio. It may be an antenna included in the back. Meanwhile, the antenna may be a Global Positioning System (GPS) antenna having only a reception function.

In the process of reverse-engineering the antenna ( S100 ), the antenna to be mounted on the aircraft is reverse-engineered. Before the process of reverse-engineering the antenna ( S100 ), the process of examining the pre-installed system and the antenna may be performed first.

Detailed information on the communication navigation system and antenna installed on the aircraft is limited to the information possessed by the aircraft or equipment manufacturer. Therefore, it is necessary to secure data by using the operator's manual and maintenance manual through the support of the unit that operates the military aircraft. The system needs information related to RF performance, such as the transmit power of the device, the lowest reception sensitivity, and the filter performance inside the device. do. However, since the antenna is limited in securing detailed performance data of the desired antenna with published standard data of the manufacturer, after the process of examining the pre-installed system and antenna, the process of reverse engineering the antenna ( S100 ) is performed.

Here, the process of reverse engineering the antenna (S100) includes measuring the performance of the antenna, designing the antenna, comparing the designed performance with the measured performance of the antenna, and modeling the antenna can do.

The process of measuring the performance of the antenna may include the process of examining the standard data of the antenna, and the performance measurement of the antenna is performed by measuring the reflection coefficient and the three-dimensional radiation pattern for the operating frequency using an authorized antenna measurement facility. can be

The process of designing an antenna includes a process of acquiring external shape information of the antenna and a process of acquiring internal structural information of the antenna, and in the process of acquiring internal structural information of the antenna, the antenna is X-rayed By photographing, information on the internal structure of the antenna may be obtained.

That is, after obtaining the external shape information of the antenna through the observation of the standard data or the appearance of the antenna, the shape of the antenna feeding part and the radiating part is checked through X-ray imaging, and this is performed using the EM simulation tool. (Electro Magnetic simulation tool) can be used to design the antenna. Thereafter, the final antenna shape may be derived by comparing the antenna performance measurement result and the EM simulation result to confirm the performance accuracy, and to increase the accuracy by adjusting the antenna shape.

In this case, in the process of modeling the antenna, the shape of the designed antenna may be adjusted to match the measured performance of the antenna. In this process, even if the antenna shape does not match 100%, it is important to improve the measurement performance and consistency, and since it is impossible to check the antenna material through X-ray imaging, in the EM simulation process, the material of the antenna is perfect conductor (PEC; Perfect Electric). Conductor) to perform the analysis. Through this process, EM modeling of the antenna can be performed by comparing antenna performance such as reflection coefficient, 3D radiation pattern, and isolation degree.

When the reverse design of the single antenna is completed, a process ( S200 ) of determining a preliminary position for mounting the antenna to the aircraft may be performed. Here, in the process of determining the preliminary position, at least one of a cable structure connected to the antenna, a change in aerodynamic coefficient depending on whether the antenna is mounted, and structural soundness according to the mounting of the antenna, is analyzed, and determining the position of at least one of the identified plurality of positions as the preliminary position.

Since the antenna has a large separation distance from the avionics bay where the communication and navigation equipment is installed, a cable harness design that can minimize the RF loss of the cable must be carried out. In the case of a specific communication navigation system, it is necessary to select a cable and design a cable harness that meets the RF loss standard required by domestic and foreign standards or equipment.

Next, the antenna is a structure mounted on the outside of the aircraft, and it is necessary to derive a location that satisfies the structural characteristics. Aerodynamics analysis is a process of determining the effect of modification through analysis of changes in the aerodynamic coefficient when the antenna is not mounted and when it is mounted, and the drag coefficient and directional stability change are derived and analyzed. Structural soundness analysis proceeds with static analysis and dynamic analysis. In the case of static analysis, it is derived by applying a structural soundness evaluation model based on the tensile critical load, inertial load, and handling load due to the addition of an antenna. The dynamic analysis checks whether the design is designed by avoiding the intrinsic excitation frequency of the aircraft through the vibration analysis of the antenna. If the analysis result is limited in securing structural integrity, design is carried out so that there are no restrictions on mounting external attachments through structural reinforcement.

When the area of the aircraft in which the antenna can be mounted, that is, a plurality of positions is derived through the above procedure, the reverse engineering modeling of the antenna to be mounted is mounted on the preliminary position, which is at least one position among the plurality of positions, and the antenna radiation pattern is analyzed. In this case, when the antenna is a wireless communication antenna, the wireless communication antenna includes a transmission antenna and a reception antenna, and the process of determining the preliminary position may determine the preliminary position in which the reverse-engineered transmission antenna and the reception antenna are mounted, respectively. On the other hand, when the antenna is a GPS antenna, the GPS antenna includes a reception antenna, and the process of determining a preliminary position may determine a preliminary position in which at least one reception antenna that is reverse engineered is mounted.

The process of analyzing the performance of the antenna (S300) is a process of analyzing the radiation pattern of the antenna at a preliminary position and a wireless communication device including a wireless communication antenna for wireless communication or a GPS device for receiving a GPS signal and mounted on the aircraft It may include the process of analyzing whether there is interference between the avionics equipment.

In the process of analyzing the radiation pattern of the antenna, the radiation pattern requirements vary according to the characteristics of the equipment and the operation requirements as well as the antenna characteristics of directivity and omnidirectionality, and the performance is checked according to each requirement.

Thereafter, the reverse engineered antenna is designed at the aircraft mounting position to determine whether interference with other equipment is present, and S ₂₁ , which is an S-parameter corresponding to the transmission coefficient, is simulated. At this time, the avionics device generating the RF signal includes not only the RF signal of the frequency band of the corresponding device, that is, the RF signal of the transmitting frequency band in the case of the transmitting device or the RF signal of the receiving frequency band in the case of the receiving device, as well as the transmitting frequency band and the receiving frequency. Since the RF signal is generated in the entire frequency band including the band, S ₂₁ must be derived from the operating frequency of each equipment subject to interference analysis.

In the process of analyzing whether interference between a wireless communication device or a GPS device and the avionics device mounted on the aircraft, interference is analyzed using the characteristics of the onboard device and the analyzed transmission coefficient. The characteristics of the on-board equipment include the transmission output of the equipment, the filter performance inside the equipment, and the minimum reception sensitivity of the reception band. . In this case, not only the characteristics of the on-board equipment, but also the characteristics of the applied system and antenna should be considered.

For example, in the case of GPS equipment, a process of correcting the spread gain in the spread spectrum communication method should be included, and in the case of wireless communication equipment, since it is widely used as an integrated antenna, when analyzing the corresponding antenna, a diplexer or antenna internal/external filter The degree of isolation by Due to the nature of the system mounted on the aircraft, it emits high power when transmitting, and since it is impossible for avionics and antennas to completely block RF signals at frequencies other than the operating frequency, it can affect other avionics equipment. In addition, the reception sensitivity of the avionics equipment is very low, and when an RF signal having a high energy is radiated, the reception equipment can recognize the signal even though the signal strength is attenuated by the antenna characteristics and received. In particular, in the case of an aircraft, this phenomenon may occur more easily because the physical distance between the mounted antennas is close and the ground of the aircraft is shared.

4 is a diagram showing an outline for analyzing whether interference between a transmitting device and a receiving device.

Referring to FIG. 4 , inside the transmitting equipment (equipment-1), there is a transmit RF module generating a signal and an internal filter for attenuating signals other than the frequency of the transmit band, and inside the receiving equipment (equipment-2) there is a receiving band There is an internal filter that attenuates signals other than the frequency of , and there is a receiving RF module that receives the signal. With reference to this, the final received power due to interference of the receiving equipment may be derived from the RF characteristics of the avionics equipment and the analyzed transmission coefficient.

The process of analyzing whether there is interference between the wireless communication equipment and other avionics equipment mounted on the aircraft may be performed by Equation 1 below.

[Equation 1]

Referring to Equation 1, the process of analyzing whether interference between the wireless communication equipment and other avionics equipment mounted on the aircraft will be described in more detail. It can be divided into a process of analyzing and a process of analyzing whether there is interference between the wireless communication equipment and other receiving equipment. In the process of analyzing the interference between the wireless communication equipment and other transmitting equipment, the wireless communication equipment corresponds to equipment-2 illustrated in FIG. 4 , and the other transmitting equipment corresponds to equipment-1 illustrated in FIG. 4 . On the other hand, in the process of analyzing whether interference between the wireless communication equipment and the other receiving equipment is, the wireless communication equipment corresponds to equipment-1 shown in FIG. 4 and the other transmitting equipment corresponds to equipment-2 shown in FIG. 4 . .

Here, in the process of analyzing whether interference between the wireless communication equipment and other transmitting equipment, if the final received power value of the wireless communication equipment calculated by Equation 1 above is less than the lowest reception sensitivity, it can be analyzed that there is no interference, , where TTP is the final received power value of the wireless communication equipment, TP is the transmit output of the transmitting equipment, TFR is the internal filter attenuation value of the transmitting equipment, S _21(R) is the transfer coefficient in the receiving band, and S _21(T) is The transmission coefficient in the transmission band, RFD, means the attenuation value of the internal filter of the wireless communication equipment.

On the other hand, in the process of analyzing whether there is interference between the wireless communication equipment and other receiving equipment, if the final received power value of the receiving equipment calculated by Equation 1 above is smaller than the lowest receiving sensitivity, it can be analyzed as no interference, At this time, TTP is the final received power value of the receiving device, TP is the transmission output of the wireless communication device, TFR is the internal filter attenuation value of the wireless communication device, S _21(R) is the transmission coefficient in the reception band, and S _21(T) is The transmission coefficient in the transmission band, RFD, means the attenuation value of the internal filter of the receiving equipment.

In the process of analyzing interference, the final reception power of the receiving equipment (wireless communication equipment or other receiving equipment) due to interference was calculated by dividing the operating band of the receiving equipment and the operating band of the transmitting equipment (other transmitting equipment or wireless communication equipment). . The interference of the operating band of the receiving equipment (radio communication equipment or other receiving equipment) is transmitted to the transmitting equipment antenna after the RF signal generated inside the transmitting equipment (other transmitting equipment or wireless communication equipment) is attenuated by the internal filter to reduce the RF radiation. It is transmitted to the receiving RF module of the receiving equipment (wireless communication equipment or other receiving equipment) through the It is transmitted to the antenna of the transmitting equipment and flows into the antenna of the receiving equipment, and the RF signal is attenuated by the internal filter of the receiving equipment (wireless communication equipment or other receiving equipment) and then transferred to the receiving RF module.

On the other hand, the process of analyzing whether there is interference between the GPS equipment and other avionics equipment mounted on the aircraft may be performed by Equation 2 below.

[Equation 2]

In the process of analyzing whether there is interference between the GPS device and the other transmitting device, the GPS device corresponds to the device-2 shown in FIG. 4 , and the other transmitting device corresponds to the device-1 shown in FIG. 4 .

That is, in the process of analyzing whether interference between the GPS equipment and other transmitting equipment is present, if the final received power value of the GPS equipment calculated by Equation 2 is smaller than the lowest reception sensitivity, it can be analyzed that there is no interference. TTP is the final received power value of the GPS device, TP is the transmission power of the transmitting device, TFR is the internal filter attenuation value of the transmitting device, SG is the GPS spreading gain, S _21(R) is the transmission coefficient in the receiving band, that is, the GPS band means

In the case of receive-only equipment such as GPS equipment, the final received power value is calculated by considering only the interference caused by the receive frequency band. After receiving , the final reception power by the transmitting equipment is calculated by reflecting the GPS spreading gain (SG) through the process of being restored by the GPS equipment. Here, the GPS spreading gain SG may have a value of, for example, 53.11 dB.

As a result, when the final reception effort of the receiving equipment due to the operation of the transmitting equipment and the antenna radiation is equal to or greater than the minimum receiving sensitivity of the receiving equipment, interference occurs. If the performance of the analyzed antenna does not satisfy the setting conditions, the process of reanalyzing the performance of the antenna is performed by changing the preliminary position among a plurality of positions where the antenna can be mounted, confirmed in the process of determining the preliminary position, and performing the process of re-analyzing the An optimal location where interference does not occur is derived.

Hereinafter, a case in which the above-described method for determining the mounting position of an antenna is applied to an actual performance improvement project will be described.

In the case, the Pia identification antenna is newly installed in the upper and lower parts for an air force transport aircraft that requires additional antenna installation, and the GPS antenna is additionally mounted on the upper part, the antenna performance analysis method according to the embodiment of the present invention and An antenna mounting position determination method was used.

The peer identification antenna to be added is RAMI's AT-741B/B antenna operating in L-band, which satisfies the performance of polarization, bandwidth, VSWR, etc., and the average power of the antenna also satisfies the requirement with 100W. In order to confirm that the coverage radiation pattern of the corresponding antenna satisfies the requirements, the shape of the antenna was checked by applying the reverse engineering technique. 5 is a 1030 MHz radiation pattern of an L-band antenna additionally mounted on an air force transport aircraft, which is a result derived based on the reverse design process of the antenna according to an embodiment of the present invention, and simulation and measurement results for elevation and azimuth are very similar. and the gain was also at the 0.5dB level mentioned in the data sheet of the antenna.

In order to select the positions of the Pia identification antenna and the GPS antenna that can be installed on the Air Force transport aircraft, the effect of the cable harness and external installation on the airframe structure was analyzed, and the installation location was derived considering the convenience of operation for aircraft modification.

6(a) shows the area where the Pia identification antenna can be mounted on the upper and lower parts and the cable loss is judged to be within 3 dB in the form of a dotted line. Confirmed. In the case of the upper part, #1-2 was selected as a final candidate location considering the cable loss satisfaction and work convenience among the three possible installation positions in terms of structure. is the jacking area, and #2-3 is the final candidate location as the installation is limited considering the hydraulic line and other equipment sensitivities. On the other hand, in FIG. 6(b), as a position where the GPS antenna can be mounted, #2 was selected as the final candidate position in consideration of the increase in reinforcement structures, work convenience, aircraft structure, and the like.

It was analyzed whether the performance requirements were satisfied by analyzing the antenna radiation pattern for the candidate positions. 7(a) and (b) show that the 1090MHz transmission radiation pattern of the upper and lower peer identification antennas satisfies the coverage requirement. In the case of a GPS antenna, the universal antenna performance standard was analyzed based on the 3dB beamwidth, and as shown in FIG. It was confirmed that GPS signals can be normally received.

As the radiation pattern of the peer identification antenna and the GPS antenna satisfies the certification standards and system requirements, it was analyzed whether interference occurred due to the addition of the antenna, which is the final analysis step. The internal filter performance of the onboard equipment is the most common and modeled by applying a 5-stage 10th-order Chevyshev filter that can simulate the minimum internal filter response in all equipment.

In the table below, equipment using peer identification equipment and similar frequency bands such as TACAN, TCAS, and DME were excluded from interference analysis as a suppressor design was implemented to avoid simultaneous transmission between operations and to prevent misidentification of received signals.

The process of deriving interference between devices was performed through the process of analyzing whether interference according to an embodiment of the present invention, and the results of the interference analysis between devices calculated by adding an antenna are shown in the table below.

[Table 1]

Table 1 is the result of calculating the final received power received by other equipment when a 1090MHz signal is transmitted through the lower peer identification antenna. It was simulated by the inter-antenna radiation and derived as a transfer coefficient. Each final received power was calculated separately from the receiving equipment operating band interference and the transmitting equipment operating band interference, and by the suppressor design, the final received power in all equipment except for TACAN, TCAS and DME, except for interference analysis, is the lowest of the individual equipment. It was confirmed that it was lower than the reception sensitivity.

[Table 2]

In the same way, as shown in Table 2, the received power transmitted through the lower peer identification antenna was calculated when transmitting to other mounted equipment, and the final received power delivered by all transmitting equipment is the lowest reception sensitivity of the transponder included in the peer identification equipment - It was confirmed that it was lower than 88dBm.

[Table 3]

Table 3 shows the results of interference analysis of GPS equipment, and as the GPS spread gain generated by the spread spectrum modulation method is considered and analyzed, the final received power delivered from the onboard equipment is a very low value of -180 dBm or less. It was confirmed that it was lower than -79.89dBm, which is the lowest reception sensitivity of the GPS receiver.

Finally, it was confirmed that RF interference due to antenna radiation between the existing on-board equipment and the transponder of the peer identification equipment and the GPS receiver of the GPS equipment did not occur due to the addition of the air force transport type upper/lower peer identification antenna and GPS antenna.

Based on this antenna mounting location determination method, the remodeling of the air force transport aircraft was completed, and the function and performance evaluation of the modified air transport aircraft was performed. As a result of the evaluation, it was confirmed that there was no effect on the avionics system system according to the antenna installation, and it was confirmed that there were no restrictions on the operation of the peer identification equipment, etc.

As such, according to the method for analyzing the performance of the wireless communication antenna and the method for determining the mounting location according to the embodiment of the present invention, the performance of the wireless communication antenna is effectively analyzed during the aircraft remodeling project, and structural problems and RF interference between equipment do not occur. It is possible to determine the optimal antenna mounting position.

In the above, preferred embodiments of the present invention have been described and illustrated using specific terms, but such terms are only for clearly explaining the present invention, and the embodiments of the present invention and the described terms are the spirit of the following claims And it is obvious that various changes and changes can be made without departing from the scope. Such modified embodiments should not be individually understood from the spirit and scope of the present invention, but should be said to fall within the scope of the claims of the present invention.

Claims (11)

delete A method for determining a location for mounting a GPS antenna for determining a location for mounting a GPS antenna on an aircraft, the method comprising:
The process of reverse engineering the GPS antenna to be mounted on the aircraft;
determining a preliminary location for mounting the GPS antenna on the aircraft;
analyzing the performance of the GPS antenna by simulating a case in which the reverse-engineered GPS antenna is mounted in the preliminary position; and
When the analyzed performance of the GPS antenna satisfies a set condition, the process of determining the preliminary location as a location for mounting the GPS antenna;
The process of reverse engineering the GPS antenna is,
measuring the performance of the GPS antenna;
designing the GPS antenna; and
Comparing the performance of the designed GPS antenna with the measured performance of the GPS antenna, the process of modeling the GPS antenna;
The process of analyzing the performance of the GPS antenna is,
analyzing the radiation pattern of the GPS antenna at the preliminary location; and
The process of analyzing whether interference exists between a GPS device including a GPS antenna and an avionics device mounted on the aircraft and including a transmission device;
The process of analyzing the interference is,
When the final received power value of the GPS equipment calculated by Equation 1 below is less than the lowest reception sensitivity, the method for determining the mounting position of the GPS antenna of the aircraft is analyzed as having no interference.
[Equation 1]

(where TTP is the final received power value of the GPS device, TP is the transmission output of the transmitting device, TFR is the internal filter attenuation value of the transmitting device, SG is the GPS spreading gain, and S _21(R) is the transmission coefficient in the GPS band. it means.) delete 3. The method according to claim 2,
The process of measuring the performance of the GPS antenna is,
A method for determining a mounting position of an aircraft GPS antenna for measuring a reflection coefficient and a radiation pattern of the GPS antenna. 3. The method according to claim 2,
The process of designing the GPS antenna is,
obtaining external information of the GPS antenna; and
Including; acquiring internal structure information of the GPS antenna;
The process of obtaining the internal structure information of the GPS antenna is,
A method of determining a mounting position of an aircraft GPS antenna by photographing the GPS antenna with X-rays to obtain information on an internal structure of the GPS antenna. 3. The method according to claim 2,
The process of modeling the GPS antenna is,
A method for determining a mounting position of an aircraft GPS antenna, comprising: adjusting a shape of a GPS antenna designed to match the measured performance of the GPS antenna. 3. The method according to claim 2,
The process of determining the preliminary position is,
A process of analyzing at least one of a cable structure connected to the GPS antenna, a change in aerodynamic coefficient depending on whether the GPS antenna is mounted, and structural soundness according to the installation of the GPS antenna, and confirming a plurality of locations where the GPS antenna can be mounted ; and
Determining at least one of the identified plurality of positions as the preliminary position; 3. The method according to claim 2,
The GPS antenna comprises at least one receiving antenna;
The process of determining the preliminary position is,
A method for determining a mounting position of an aircraft GPS antenna for determining a preliminary position in which at least one reverse engineered receiving antenna is to be mounted. delete delete 8. The method of claim 7,
When the analyzed performance of the GPS antenna does not satisfy the setting condition, the process of re-analyzing the performance of the GPS antenna by changing the preliminary location among the plurality of locations; Method for determining the mounting location of the GPS antenna of an aircraft further comprising a.

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