A method of detecting antenna beamwidth and an out-of-field surveyor for a landing vehicle-mounted device

Abstract

The application provides a field checkout device for landing airborne equipment and an antenna beam width detection method. In the field checkout device, a digital baseband generation control unit can simulate output of a landing signal to be detected under control of a controller according to landing information of the landing signal to be detected received by a human-computer interaction device, a microwave conditioning unit can form a path for a corresponding processing path in the microwave conditioning unit under control of the controller, and an output antenna can output a signal, so that the field checkout device can simulate output of the landing signal to be detected. In addition, a positioning comparison unit can detect a spatial position of the output antenna under control of the controller, so that the field checkout device can check the beam width of the antenna on the landing airborne equipment, and the field checkout device has the function of detecting the beam width of the antenna on the landing airborne equipment.

Description

Technical Field

[0001] This invention relates to the field of airborne landing technology, and in particular to an instrument for field inspection of airborne landing equipment and a method for detecting antenna beamwidth. Background Technology

[0002] An automatic landing system is an automated control system that guides an aircraft to land. It consists of two parts: landing ground equipment and landing airborne equipment. Typically, the landing airborne equipment includes microwave landing airborne equipment, VOL landing airborne equipment, and instrument landing airborne equipment, so as to meet the requirements of aircraft landing performance in different regions and environments.

[0003] To ensure the safety of aircraft landing, it is often necessary to use field testing equipment to simulate landing signals and test whether the landing equipment can perform normal calculations. However, currently, field testing equipment cannot detect the beamwidth of the antennas on the landing equipment, which may result in the landing equipment not receiving the landing signal in time during the aircraft's landing process, potentially affecting the safety of the aircraft's landing.

[0004] Therefore, how to enable the field testing instrument to detect the beamwidth of the antenna on the landing airborne equipment is a technical problem that urgently needs to be solved. Summary of the Invention

[0005] In view of this, the present invention provides a field inspection instrument for landing airborne equipment and an antenna beamwidth detection method, so that the field inspection instrument has the function of detecting the beamwidth of the antenna on the landing airborne equipment.

[0006] To achieve the above objectives, the embodiments of the present invention provide the following technical solutions:

[0007] The first aspect of this application provides a field inspection instrument for landing airborne equipment, comprising: a positioning and comparison unit, a digital baseband generation and control unit, a microwave conditioning unit, a human-machine interface device, an output antenna, and a controller; wherein:

[0008] The input / output terminal of the human-machine interaction device is connected to the input / output terminal of the controller, and the output terminal of the human-machine interaction device is connected to the input terminal of the digital baseband generation and control unit. The human-machine interaction device is used to receive and output the landing information and operating frequency band of the landing signal to be detected.

[0009] The two output terminals of the digital baseband generation and control unit are respectively connected to the two input terminals of the microwave conditioning unit. The digital baseband generation and control unit is used to simulate and output the landing signal to be detected according to the landing information and the operating frequency band under the control of the controller.

[0010] The output terminals of the microwave conditioning units are all connected to the input terminals of the output antennas. The microwave conditioning units are used to form a path for the corresponding signal processing paths within themselves under the control of the controller.

[0011] The output terminal of the positioning comparison unit is connected to the input terminal of the controller. The positioning comparison unit is used to detect the spatial position of the output antenna and output it under the control of the controller.

[0012] Optionally, the positioning comparison unit includes: a comparison conversion module, a differential processor, and a receiving antenna whose spatial position always remains consistent with the output antenna; wherein:

[0013] The output terminal of the receiving antenna is connected to the input terminal of the differential processor. The receiving antenna is used to receive and output mobile communication signals and satellite positioning signals under the control of the controller.

[0014] The output of the differential processor is connected to the input of the comparison and conversion module. The differential processor is used to determine and output the time stamp, the latitude and longitude of the field inspection instrument, and the elevation data of the field inspection instrument based on the mobile communication signal and the satellite positioning signal.

[0015] The output of the comparison and conversion module serves as the output of the positioning comparison unit. The comparison and conversion module is used to determine and output the position of the receiving antenna based on the time stamp, the latitude and longitude of the field inspection instrument, and the elevation data of the field inspection instrument.

[0016] Optionally, the digital baseband generation control unit includes: a field-programmable gate array (FPGA) control module, a radio frequency transceiver module, and auxiliary circuitry; wherein:

[0017] The input terminal of the FPGA control module is connected to the output terminal of the human-machine interaction device, and the output terminal of the FPGA control module is connected to one input terminal of the radio frequency transceiver module. The FPGA control module is used to generate and output an analog signal of the landing signal to be detected based on the landing information under the control of the controller.

[0018] The other input terminal of the radio frequency transceiver module is connected to the output terminal of the human-machine interaction device to receive the working channel; the two output terminals of the radio frequency transceiver module are respectively connected to the two input terminals of the microwave conditioning unit; the radio frequency transceiver module is used to output the signal output by the FPGA control module in the working channel under the control of the controller.

[0019] The auxiliary circuit is connected to the FPGA control module.

[0020] Optionally, the FPGA control module includes: an IQ quadrature module, a gain adjustment module, a differential encoding module, a DA converter, and a first signal selection module; wherein:

[0021] The input terminal of the IQ quadrature module is connected to the output terminal of the human-computer interaction device, and the output terminal of the IQ quadrature module is connected to the input terminal of the gain adjustment module. The IQ quadrature module is used to quadraturely modulate the analog signal of the landing signal to be detected based on the landing information.

[0022] The output terminal of the gain adjustment module is connected to the input terminal of the first signal selection module;

[0023] The two output terminals of the first signal selection module are respectively connected to the input terminal of the DA converter and the input terminal of the differential encoding module. The first signal selection module is used to output the landing signal to be tested to the differential encoding module when the landing signal to be tested is a microwave landing signal, a Volt landing signal, or a beacon landing signal, under the control of the controller; and to output the landing signal to be tested to the DA converter when the landing signal to be tested is an instrument landing signal.

[0024] The output of the differential coding module is connected to the input of the DA converter;

[0025] The output of the DA converter serves as the output of the FPGA control module.

[0026] Optionally, the radio frequency transceiver module includes: a first filter, a first adjustable power attenuator, a mixer module, a broadband adjustable local oscillator, and a second signal selection module; wherein:

[0027] The input terminal of the first filter is connected to the output terminal of the FPGA control module in the digital baseband generation control unit, and the output terminal of the first filter is connected to the input terminal of the first adjustable power attenuator.

[0028] The output of the first adjustable power attenuator is connected to one input of the mixer module;

[0029] The input terminal of the broadband adjustable local oscillator is connected to the output terminal of the human-machine interaction device, and the output terminal of the broadband adjustable local oscillator is connected to another input terminal of the mixing module. The broadband adjustable local oscillator is used to generate a carrier signal with the same frequency as the received working channel.

[0030] The output terminal of the mixer module is connected to the input terminal of the second signal selection module. The mixer module is used to perform a mixing operation on the signal output by the FPGA control module and the signal output by the broadband adjustable local oscillator module.

[0031] The two output terminals of the second signal selection module serve as the two output terminals of the radio frequency transceiver module. Under the control of the controller, the second signal selection module outputs the landing signal to be tested from one of its output terminals when the landing signal to be tested is a microwave landing signal or a glide slope instrument landing signal among instrument landing signals. When the landing signal to be tested is a Vulcan landing signal, a beacon landing signal, or a heading instrument landing signal among instrument landing signals, the second signal selection module outputs the landing signal to be tested from its other output terminal.

[0032] Optionally, if the landing signal to be detected is a microwave landing signal, then the landing information includes: magnetic heading azimuth and magnetic heading elevation.

[0033] If the landing signal to be detected is a Voll landing signal, then the landing information includes: heading and azimuth angle;

[0034] If the landing signal to be tested is an instrument landing signal, then the landing information includes: heading azimuth and glide slope angle;

[0035] If the landing signal to be detected is a corresponding beacon landing signal, then the landing information includes: the specific frequency of the beacon landing signal.

[0036] Optionally, it may also include: a power management unit; wherein:

[0037] The output terminal of the power management unit is connected to the power supply terminal of the positioning comparison unit, the power supply terminal of the digital baseband generation control unit, the power supply terminal of the microwave conditioning unit, the power supply terminal of the human-machine interaction device, and the power supply terminal of the controller, respectively.

[0038] Another aspect of this application provides a method for detecting the antenna beamwidth of landing airborne equipment, applied to the controller of a field inspection instrument as described in any of the preceding aspects of this application; the detection method includes:

[0039] When the landing information of the landing signal to be inspected is received through the human-computer interaction device in the field inspection instrument, the positioning comparison unit in the field inspection instrument is controlled to detect the spatial position of the output antenna in the heterodyne inspection instrument in real time.

[0040] During the process of the output antenna continuously changing its position, each time the spatial position of the output antenna is the same as the boundary position of the standard range of the landing signal to be tested acquired by itself, the digital baseband generation and control unit in the field inspection instrument is controlled to simulate the output of the landing signal to be tested, and the corresponding signal processing path in the microwave conditioning unit in the field inspection instrument is controlled to form a path according to the landing signal to be tested.

[0041] If, through the human-computer interaction device, the spatial position of the output antenna is always the same as the boundary position of the standard range of the landing signal to be tested acquired by itself, and a signal indicating that the landing airborne equipment has received the landing signal to be tested is received, then it is determined that the beamwidth of the antenna on the landing airborne equipment conforms to the standard range.

[0042] Optionally, the landing onboard equipment receiving the landing signal to be detected includes:

[0043] At least one antenna on the landing airborne equipment that is used to receive the landing signal to be tested receives the landing signal to be tested.

[0044] Optionally, the landing signal to be detected is: microwave landing signal, VOL landing signal, instrument landing signal, or beacon landing signal.

[0045] As can be seen from the above technical solution, the present invention provides a field inspection instrument for landing airborne equipment. In this field inspection instrument, the digital baseband generation and control unit, under the control of the controller, can simulate and output the landing signal to be inspected based on the landing information of the landing signal to be inspected received by the human-machine interface device. In addition, the microwave conditioning unit, under the control of the controller, can form a path for its corresponding processing path, and the output antenna can output a signal. Therefore, the field inspection instrument can simulate the output of the landing signal to be inspected. Furthermore, since the positioning and comparison unit, under the control of the controller, can detect the spatial position of the output antenna, the field inspection instrument can detect the beamwidth of the antenna on the landing airborne equipment. Thus, the field inspection instrument has the function of detecting the beamwidth of the antenna on the landing airborne equipment. Attached Figure Description

[0046] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0047] Figures 1-3 These are schematic diagrams illustrating the structures of three embodiments of the field inspection instrument for landing airborne equipment provided in this application.

[0048] Figure 4 A schematic diagram of one embodiment of the FPGA control module provided in this application;

[0049] Figure 5 A schematic diagram of one embodiment of the radio frequency transceiver module provided in this application;

[0050] Figure 6 A schematic diagram of one embodiment of the microwave conditioning circuit provided in this application;

[0051] Figure 7 A schematic diagram of another embodiment of the field inspection instrument for landing airborne equipment provided in this application;

[0052] Figure 8 A schematic diagram of another embodiment of the field inspection instrument for landing airborne equipment provided in this application;

[0053] Figure 9 A flowchart illustrating the antenna beamwidth detection method for landing airborne equipment provided in this application. Detailed Implementation

[0054] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0055] In this application, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0056] To enable the field inspection instrument to detect the beamwidth of antennas on landing airborne equipment, this application provides a field inspection instrument for landing airborne equipment, the specific structure of which is as follows: Figure 1 As shown, it specifically includes: a positioning and comparison unit, a digital baseband generation and control unit, a microwave conditioning unit, a human-machine interface device, an output antenna, and a controller; the connection relationships between the various components are described below:

[0057] The input / output terminals of the human-machine interface device are connected to the input / output terminals of the controller, and the output terminal of the human-machine interface device is connected to the input terminal of the digital baseband generation and control unit. The human-machine interface device is used to receive the landing information and operating frequency band of the landing signal to be tested and output them to the controller and the digital baseband generation and control unit.

[0058] Optionally, the human-computer interaction device can be a display and keyboard unit, that is, including a display screen and a keyboard. In practical applications, it may include, but is not limited to, this application. It is not specifically limited here and can be determined according to the specific circumstances. All of these are within the protection scope of this application.

[0059] Optionally, the controller can be a microprocessor. In practical applications, it may include, but is not limited to, other types of microprocessors. No specific limitation is made here. It may be determined according to the specific circumstances, and all of them are within the protection scope of this application.

[0060] Optionally, the landing signal to be tested can be a microwave landing signal, a VOL landing signal, a heading instrument landing signal or a glide slope instrument landing signal from the instrument landing signals, or even any kind of beacon landing signal. In practical applications, it may include, but is not limited to, these, and can be determined according to the specific circumstances, all of which are within the protection scope of this application.

[0061] It should be noted that, typically, there are three types of beacon landing signals, which are standard sinusoidal signals of 400Hz, 1300Hz, and 3000Hz, respectively.

[0062] If the landing signal to be tested is a microwave landing signal, the landing information of the landing signal to be tested includes: magnetic heading azimuth and magnetic heading elevation; if the landing signal to be tested is a Vortex landing signal, the landing information of the landing signal to be tested includes: heading azimuth; if the landing signal to be tested is an instrument landing signal, the landing information of the landing signal to be tested includes: heading azimuth and glide slope; if the landing signal to be tested is a corresponding beacon landing signal, the landing information of the landing signal to be tested includes: the specific frequency of the beacon landing signal.

[0063] The two output terminals of the digital baseband generation and control unit are connected to the two input terminals of the microwave conditioning unit, respectively. The control terminal of the digital baseband generation and control unit is connected to the controller. Under the control of the controller, the digital baseband generation and control unit is used to simulate and output the landing signal to be tested based on the landing information and operating frequency band of the landing signal to be tested.

[0064] Analog output of the landing signal under test means not only ensuring that the output signal is consistent with the landing signal under test, but also ensuring that the output mode of the signal is consistent with the output mode of the landing signal under test. Here, the output mode can be understood as the working channel of the landing signal under test or the carrier frequency when the landing signal under test is output.

[0065] The output terminals of the microwave conditioning unit are all connected to the input terminals of the output antenna. The control terminal of the microwave conditioning unit is connected to the controller. Under the control of the controller, the microwave conditioning unit is used to form a path for the corresponding signal processing path within itself. In other words, under the control of the controller, the microwave conditioning unit is used to process the signal output by the digital baseband generation control unit in a corresponding processing mode.

[0066] In a specific example, the output antenna includes a first wideband antenna for detecting the Volt landing function and the instrument landing function, a second wideband antenna for detecting the pointing beacon function, and a hemispherical pattern built-in microstrip antenna for checking the microwave landing function; wherein, the hemispherical pattern built-in microstrip antenna for checking the microwave landing function is located inside the back of the field inspection instrument; in addition, the output antenna uses a standard TNC connector.

[0067] The above example only illustrates one specific implementation of the output antenna. In practical applications, it includes, but is not limited to, this example. It is not specifically limited here, but can be determined according to the specific circumstances, and all are within the protection scope of this application.

[0068] The output of the positioning comparison unit is connected to the input of the controller, and the control end of the positioning comparison unit is connected to the controller. The positioning comparison unit is used to detect and output the spatial position of the output antenna under the control of the controller.

[0069] It should be noted that after receiving the spatial position of the output antenna from the positioning comparison unit, the controller will output the spatial position of the output antenna to the human-computer interaction device and display the spatial position of the output antenna using the human-computer interaction device.

[0070] As described above, under the control of the controller, the digital baseband generation control unit can simulate and output the landing signal to be tested based on the landing information of the landing signal to be tested received from the human-machine interface device. In addition, under the control of the controller, the microwave conditioning unit can form a path for the corresponding processing path within itself, and the output antenna can output a signal. Therefore, the field inspection instrument can simulate the output of the landing signal to be tested. Furthermore, since the positioning comparison unit can detect the spatial position of the output antenna under the control of the controller, the field inspection instrument can detect the beamwidth of the antenna on the landing airborne equipment. Thus, the field inspection instrument has the function of detecting the beamwidth of the antenna on the landing airborne equipment.

[0071] Another embodiment of this application provides a specific implementation of the positioning comparison unit, the specific structure of which is as follows: Figure 2 As shown, it specifically includes: a comparison and conversion module, a differential processor, and a receiving antenna whose spatial position always remains consistent with the output antenna; the connection relationships between the various components are described below:

[0072] The output of the receiving antenna is connected to the input of the differential processor, and the control terminal of the receiving antenna is connected to the controller. The receiving antenna is used to receive and output mobile communication signals and satellite positioning signals under the control of the controller.

[0073] Optionally, the mobile communication signal can be a 5G signal. In practical applications, this may include, but is not limited to, 5G signals. The specific application may vary depending on the circumstances and is within the scope of protection of this application.

[0074] Optionally, the satellite positioning signal can be a BeiDou satellite signal. In practical applications, it may include, but is not limited to, BeiDou satellite signals. It is not specifically limited here and can be determined according to the specific circumstances. All of these are within the protection scope of this application.

[0075] The output of the differential processor is connected to the input of the comparison and conversion module. The differential processor is used to determine and output the time stamp, latitude and longitude of the field inspection instrument, and elevation data of the field inspection instrument based on the mobile communication signal and satellite positioning signal.

[0076] It should be noted that in practical applications, the differential processor provides 100 data records per second, and after removing outliers, the average value is used as the final data.

[0077] The output of the comparison and conversion module serves as the output of the positioning comparison unit and is connected to the input of the controller. The comparison and conversion module is used to determine and output the position of the receiving antenna based on the time stamp, the latitude and longitude of the field inspection instrument, and the elevation data of the field inspection instrument.

[0078] The above is only one specific implementation of the positioning and comparison unit. In practical applications, it includes, but is not limited to, this one. It can be determined according to the specific situation and is within the protection scope of this application.

[0079] Another embodiment of this application provides a specific implementation of a digital baseband generation control unit, the specific structure of which is as follows: Figure 3 As shown, it specifically includes: a Field-Programmable Gate Array (FPGA) control module, an RF transceiver module, and auxiliary circuitry; the connection relationships between the various components are described below:

[0080] The input terminal of the FPGA control module is connected to the output terminal of the human-machine interface device, the output terminal of the FPGA control module is connected to one input terminal of the radio frequency transceiver module, and the control terminal of the FPGA control module is connected to the controller. The FPGA control module is used to generate and output the analog signal of the landing signal to be tested based on the landing information of the landing signal to be tested received by itself under the control of the controller.

[0081] Another input terminal of the RF transceiver module is connected to the output terminal of the human-machine interface device to receive the working channel of the landing signal under test; the two output terminals of the RF transceiver module are respectively connected to the two input terminals of the microwave conditioning unit; the control terminal of the RF transceiver module is connected to the controller; the RF transceiver module is used to output the signal output by the FPGA control module using the working channel of the landing signal under test under the control of the controller.

[0082] For example, when the landing signal to be tested is a microwave landing signal, its carrier frequency is 5031.0~5090.7MHz; when the landing signal to be tested is a VOL landing signal, its carrier frequency is 107.0MHz~117.95MHz, that is, its operating frequency band is 107.0MHz~117.95MHz; when the landing signal to be tested is an instrument landing signal, its heading signal carrier frequency is 108.0MHz~111.95MHz, that is, its operating frequency band is 108.0MHz~111.95MHz, and its glide slope signal carrier frequency is 329.15MHz~335.0MHz, that is, its operating frequency band is 329.15MHz~335.0MHz; when the landing signal to be tested is a beacon landing signal, the carrier frequency of all three beacon landing signals is 75MHz, that is, the operating frequency band of all three beacon landing signals is 75MHz.

[0083] Specifically, when the landing signal to be tested is a microwave landing signal or a glide slope instrument landing signal from instrument landing signals, the landing signal to be tested is output through the first output terminal of the radio frequency transceiver module; when the landing signal to be tested is a Vortex landing signal, a marker beacon landing signal, or a heading instrument landing signal from instrument landing signals, the landing signal to be tested is output through the second output terminal of the radio frequency transceiver module.

[0084] It should be noted that, under normal circumstances, the working channels of microwave landing signals, Volt landing signals, instrument landing signals, and beacon landing signals are all predetermined, so the working channels of each landing signal are pre-stored in the controller.

[0085] The auxiliary circuit is connected to the FPGA control module.

[0086] In a specific example, the auxiliary circuit includes: a peripheral interface module, DDR3 memory, FLASH flash memory, an eMMC storage chip, an RJ45 Ethernet interface, two power supply chips, and two crystal oscillators; the connection relationships between the components are as follows:

[0087] The FPGA control module is connected to DDR3 memory, FLASH flash memory, EMMC storage chip, RJ45 Ethernet interface, and two crystal oscillators.

[0088] The human-computer interaction device is connected to the input terminal of the FPGA control module through a peripheral interface. For example, if the human-computer interaction device includes an L2C keyboard, the peripheral interface module includes an I2C keyboard interface, and the L2C keyboard is connected to the input terminal of the FPGA control module through the I2C keyboard interface. In addition, the peripheral interface also includes I / O ports for simulating various types of serial ports to complete input / output functions, as well as a JATG communication interface for online programming.

[0089] The above is only one specific implementation of the digital baseband generation control unit. In practical applications, there are other implementations, including but not limited to this one. No specific limitation is made here. The implementation can be determined according to the specific circumstances, and all of them are within the protection scope of this application.

[0090] Another embodiment of this application provides a specific implementation of an FPGA control module, the specific structure of which is as follows: Figure 4 As shown, it specifically includes: an IQ quadrature module, a gain adjustment module, a differential coding module, a DA converter, and a first signal selection module; the specific connection relationships between each module are as follows:

[0091] The input of the IQ quadrature module is connected to the output of the human-machine interface device to receive the landing information of the landing signal to be tested; the output of the IQ quadrature module is connected to the input of the gain adjustment module; the IQ quadrature module is used to quadraturely modulate the analog signal of the landing signal to be tested based on the landing information of the landing signal to be tested.

[0092] If the landing signal to be detected is a microwave landing signal, the IQ orthogonal module generates an IQ orthogonal signal. Then, the IQ orthogonal module uses the IQ orthogonal signal to generate a microwave landing azimuth angle signal and a microwave landing elevation angle signal based on the magnetic heading azimuth angle and the magnetic heading elevation angle, respectively. Finally, the two are combined.

[0093] If the landing signal to be detected is the Voll landing signal, the IQ quadrature module generates an IQ quadrature signal. Then, the IQ quadrature module uses the IQ quadrature signal to generate a 30Hz amplitude-modulated signal and a 9960Hz subcarrier frequency frequency-modulated signal based on the heading azimuth angle. Finally, the two are combined.

[0094] If the landing signal to be tested is an instrument landing signal, the IQ quadrature module generates an IQ quadrature signal. Then, the IQ quadrature module uses the IQ quadrature signal to generate a 90Hz heading signal and a 150Hz heading signal according to the heading azimuth angle, and generates a 90Hz glide slope signal and a 150Hz glide slope signal according to the glide slope angle.

[0095] It should be noted that, under normal circumstances, both the heading instrument landing signal and the glide slope instrument landing signal consist of a 90Hz signal and a 150Hz signal. To distinguish them, the 90Hz signal in the heading instrument landing signal is called the 90Hz heading signal and the 150Hz signal is called the 150Hz heading signal. Similarly, the 90Hz signal in the glide slope instrument landing signal is called the 90Hz glide slope signal and the 150Hz signal is called the 150Hz glide slope signal.

[0096] If the landing signal to be tested is any type of beacon landing signal, the IQ quadrature module generates an IQ quadrature signal, and then the IQ quadrature module uses the Q quadrature signal to generate a standard sine signal of a specific frequency.

[0097] It should be noted that the landing information of the landing signal to be tested has been described in detail in the above embodiments, and will not be repeated here.

[0098] The output of the gain adjustment module is connected to the input of the first signal selection module; the gain adjustment module is used to amplify the signal output by the IQ quadrature module.

[0099] The two output terminals of the first signal selection module are connected to the input terminal of the DA converter and the input terminal of the differential encoding module, respectively. The control terminal of the first signal selection module is connected to the controller. Under the control of the controller, the first signal selection module outputs the landing signal to be tested to the differential encoding module when the landing signal to be tested is a microwave landing signal, a Volt landing signal, or a beacon landing signal, and outputs the landing signal to be tested to the DA converter when the landing signal to be tested is an instrument landing signal.

[0100] In practical applications, the controller determines the type of the landing signal to be detected by the landing information of the landing signal to be detected, and then issues corresponding control commands to the first signal selection module according to the type of the landing signal to be detected to control it.

[0101] The output of the differential coding module is connected to the input of the DA converter; the output of the DA converter serves as the output of the FPGA control module and is connected to the RF transceiver module; the differential coding module is used to differentially encode the received signal.

[0102] If the landing signal to be detected is a microwave landing signal, the differential coding module performs differential phase shift keying encoding on the received signal to achieve differential coding; if the landing signal to be detected is a Vortex landing signal, the differential coding module performs binary amplitude shift keying encoding on the received signal to achieve differential coding; if the landing signal to be detected is any type of beacon landing signal, the differential coding module performs binary amplitude shift keying encoding on the received signal to achieve differential coding.

[0103] It should be noted that the IQ quadrature module, gain adjustment module, differential coding module and DA converter all adopt a very mature structure in the existing technology, and will not be described in detail here.

[0104] The above is only one specific implementation of the FPGA control module. In practical applications, there are other implementations, including but not limited to this one. No specific limitation is made here. The implementation can be determined according to the specific circumstances, and all of them are within the protection scope of this application.

[0105] Another embodiment of this application provides a specific implementation of a radio frequency transceiver module, the specific structure of which is as follows: Figure 5 As shown, it specifically includes: a first filter, a first adjustable power attenuator, a mixer module, a broadband adjustable local oscillator, and a second signal selection module; the connections between the components are as follows:

[0106] The input of the first filter is connected to the output of the FPGA control module in the digital baseband generation control unit, and the output of the first filter is connected to the input of the first adjustable power attenuator. The first filter is used to filter out interference signals during signal transmission.

[0107] The output of the first adjustable power attenuator is connected to one input of the mixer module.

[0108] The input of the broadband adjustable local oscillator is connected to the output of the human-machine interface device, and the output of the broadband adjustable local oscillator is connected to the other input of the mixer module. The broadband adjustable local oscillator is used to generate a carrier signal with the same frequency as the working channel of the received landing signal to be tested.

[0109] The output of the mixer module is connected to the input of the second signal selection module. The mixer module is used to perform a mixing operation on the signal output by the FPGA control module and the signal output by the broadband adjustable local oscillator module.

[0110] The two outputs of the second signal selection module serve as the two outputs of the RF transceiver module, and are respectively connected to the two inputs of the microwave conditioning circuit.

[0111] The control terminal of the second signal selection module is connected to the controller. Under the control of the controller, the second signal selection module is used to output the landing signal to be tested from its first output terminal when the landing signal to be tested is a microwave landing signal or a glide slope instrument landing signal among instrument landing signals. When the landing signal to be tested is a Vortex landing signal, a beacon landing signal, or a heading instrument landing signal among instrument landing signals, the second signal selection module is used to output the landing signal to be tested from its second output terminal.

[0112] In practical applications, the controller determines the type of the landing signal to be detected by the landing information of the landing signal to be detected, and then issues corresponding control commands to the second signal selection module according to the type of the landing signal to be detected to control it.

[0113] It should be noted that the first filter, the first adjustable power attenuator, the mixer module, the broadband adjustable local oscillator, and the second signal selection module all adopt mature structures in the existing technology, and will not be described in detail here.

[0114] The above is only one specific implementation of the radio frequency transceiver module. In practical applications, there are other implementations, including but not limited to this one. No specific limitation is made here. The implementation can be determined according to the specific circumstances, and all of them are within the protection scope of this application.

[0115] Another embodiment of this application provides a specific implementation of a microwave conditioning circuit, the specific structure of which is as follows: Figure 6 As shown, it specifically includes: two power amplifiers, two adjustable power attenuators, a controllable switch, and four filters; the connection relationships between the components are as follows:

[0116] The input terminal of the first power amplifier is connected to the first output terminal of the RF transceiver module. The first power amplifier is used to amplify the signal output from the first output terminal of the RF transceiver module.

[0117] The input terminal of the second adjustable power attenuator is connected to the output terminal of the first power amplifier, and the output terminal of the second adjustable power attenuator is connected to the input terminals of the first low-pass filter and the second low-pass filter, respectively.

[0118] If the output antenna includes a first wideband antenna for detecting Volt landing and instrument landing functions, a second wideband antenna for detecting pointing beacon functions, and a hemispherical pattern built-in microstrip antenna for checking microwave landing functions, then the output of the second filter is connected to the hemispherical pattern built-in microstrip antenna, and the output of the third filter is connected to the first wideband antenna.

[0119] The second filter is used to filter out signals other than the microwave landing signal, and the filtering range of the second filter is set according to the carrier frequency of the microwave landing signal; the third filter is used to filter out signals other than the glide slope instrument landing signal in the instrument landing signal, and the filtering range of the third filter is set according to the carrier frequency of the glide slope instrument landing signal in the instrument landing signal.

[0120] The input terminal of the second power amplifier is connected to the second output terminal of the RF transceiver module. The second power amplifier is used to amplify the signal output from the second output terminal of the RF transceiver module.

[0121] The input terminal of the third adjustable power attenuator is connected to the output terminal of the second power amplifier, the output terminal of the third adjustable power attenuator is connected to the first terminal of the controllable switch, and the second terminal of the controllable switch is connected to the fourth filter and the fifth filter respectively.

[0122] If the output antenna includes a first wideband antenna for detecting Volt landing and instrument landing functions, a second wideband antenna for detecting pointing beacon functions, and a hemispherical pattern built-in microstrip antenna for checking microwave landing functions, then the output of the fourth filter is connected to the first wideband antenna, the fifth filter is connected to the first wideband antenna, and the third terminal of the controllable switch is connected to the second wideband antenna.

[0123] The control terminal of the controllable switch is connected to the controller. The controller determines the type of the landing signal to be tested based on the landing information of the landing signal to be tested. If the landing signal to be tested is a beacon landing signal, the first terminal and the third terminal of the controllable switch are connected. If the landing signal to be tested is a Vortex landing signal or a heading instrument landing signal among instrument landing signals, the first terminal and the second terminal of the controllable switch are connected.

[0124] The fourth filter is used to filter out signals other than the Voll landing signal; that is, the filtering range of the fourth filter is set according to the carrier frequency of the Voll landing signal. The fifth filter is used to filter out signals other than the heading instrument landing signal in the instrument landing signal; that is, the filtering range of the fifth filter is set according to the carrier frequency of the heading instrument landing signal in the instrument landing signal.

[0125] It should be noted that the first power amplifier, the second adjustable power attenuator, the second filter, the third filter, the second power amplifier, the third adjustable power attenuator, the controllable switch, the fourth filter, and the fifth filter all adopt a very mature structure in the existing technology, and will not be described in detail here.

[0126] The above is only one specific implementation of the microwave conditioning circuit. In practical applications, there are other implementations, including but not limited to this one. No specific limitation is made here. The specific implementation can be determined according to the specific situation, and all of them are within the protection scope of this application.

[0127] Another embodiment of this application provides another implementation of a field inspection instrument for landing airborne equipment, the specific structure of which can be found in [reference needed]. Figure 7 ( Figure 7 Only Figure 1 Based on the above implementation method, the method further includes a power management unit.

[0128] The output of the power management unit is connected to the power supply terminals of the positioning and comparison unit, the digital baseband generation and control unit, the microwave conditioning unit, the human-machine interface device, and the controller, respectively, and supplies them with power.

[0129] It should be noted that the power management unit adopts the power management topology in the existing technology. Since the power management topology in the existing technology is already very mature, it will not be described in detail here.

[0130] Another embodiment of this application provides another implementation of the digital baseband generation control unit, the specific structure of which can be found in [reference needed]. Figure 8 (Image only) Figure 3 As shown in the example (using two voltage conversion modules), this implementation also includes a power supply chip and at least one voltage conversion module, based on the above implementation.

[0131] The input terminal of the power supply chip is connected to the output terminal of the power management unit, and the output terminal of the power supply chip is connected to the input terminal of each voltage conversion module.

[0132] The output of each voltage conversion module is connected to the power supply terminals of each device in the FPGA control module and the power supply terminals of each device in the RF transceiver module, respectively.

[0133] For example, the digital baseband generation control unit includes six voltage conversion modules, and the output voltages of the six voltage conversion modules are 1.0V, 1.3V, 1.5V, 1.8V, 2.5V, and 3.3V, respectively.

[0134] Another embodiment of this application provides a method for detecting the antenna beamwidth of landing airborne equipment, applied to the controller of the field inspection instrument provided in the above embodiment; the specific process of this detection method is as follows: Figure 9 As shown, the specific steps include:

[0135] S110. When the landing information of the landing signal to be inspected is received through the human-machine interaction device in the field inspection instrument, the positioning comparison unit in the field inspection instrument is controlled to detect the spatial position of the output antenna in the heterodyne inspection instrument in real time.

[0136] Optionally, the landing signal to be tested can be a microwave landing signal, a Vortex landing signal, an instrument landing signal, or a beacon landing signal. In practical applications, it may include, but is not limited to, these, and is not specifically limited here. It can be determined according to the specific circumstances, and all of them are within the protection scope of this application.

[0137] It should be noted that if the landing signal to be tested is a beacon landing signal, the field inspection instrument should be placed below the antenna on the landing equipment used to receive the beacon landing signal; if the landing signal to be tested is a microwave landing signal, VOL landing signal, or instrument landing signal, the field inspection instrument should be placed in front of the aircraft at a distance of 15 meters or more.

[0138] S120. During the continuous change of position of the output antenna, when the spatial position of the output antenna is the same as the boundary position of the standard range of the landing signal to be tested acquired by itself, the digital baseband generation control unit in the field inspection instrument is controlled to simulate the output of the landing signal to be tested, and the corresponding signal processing path in the microwave conditioning unit in the field inspection instrument is controlled to form a path according to the landing signal to be tested.

[0139] S130. Determine whether, through the human-computer interaction device, when the spatial position of the output antenna is the same as the boundary position of the standard range of the landing signal to be tested acquired by itself, it can always receive the signal that represents the landing airborne equipment receiving the landing signal to be tested.

[0140] If, through the human-computer interaction device, the spatial position of the output antenna is always the same as the boundary position of the standard range of the landing signal to be tested acquired by itself, and a signal indicating that the landing airborne equipment has received the landing signal to be tested is received, then step S140 is executed; if, through the human-computer interaction device, the spatial position of the output antenna is always the same as the boundary position of the standard range of the landing signal to be tested acquired by itself, but a signal indicating that the landing airborne equipment has received the landing signal to be tested is not received, then step S150 is executed.

[0141] When the landing equipment receives the landing signal to be checked, it can be that one antenna on the landing equipment used to receive the landing signal to be checked receives the landing signal to be checked, or multiple antennas on the landing equipment used to receive the landing signal to be checked receive the landing signal to be checked. Of course, if more than one antenna is required to receive the landing signal to be checked, it is equivalent to the aircraft having a backup antenna, which can improve the safety performance of the aircraft.

[0142] S140. Determine that the beamwidth of the antenna on the landing airborne equipment meets the above-mentioned standard range.

[0143] S150. It is determined that the beamwidth of the antenna on the landing airborne equipment does not meet the above-mentioned standard range.

[0144] Since the controller can receive a signal indicating that the landing equipment has received the landing signal each time the spatial position of the output antenna is the same as the boundary position of the standard range of the landing signal to be tested, the controller can receive a signal indicating that the landing equipment has received the landing signal to be tested through the human-machine interface device. Therefore, when the spatial position of the output antenna is at any position within the standard range of the landing signal to be tested, the controller can receive a signal indicating that the landing equipment has received the landing signal to be tested. Thus, this detection method can detect whether the beamwidth of the landing equipment antenna is within the standard range, thereby improving the safety performance of the aircraft.

[0145] The features described above in the disclosed embodiments can be substituted or combined with each other, enabling those skilled in the art to implement or use this application. The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention in any way. Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any person skilled in the art can make many possible variations and modifications to the technical solutions of the present invention using the methods and techniques disclosed above, or modify them into equivalent embodiments with equivalent changes, without departing from the scope of the present invention. Therefore, any simple modifications, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the present invention's technical solutions still fall within the protection scope of the present invention.

Claims

1. A field inspection instrument for landing airborne equipment, characterized in that, include: Positioning and comparison unit, digital baseband generation and control unit, microwave conditioning unit, human-machine interface device, output antenna and controller; wherein: The input / output terminal of the human-machine interaction device is connected to the input / output terminal of the controller, and the output terminal of the human-machine interaction device is connected to the input terminal of the digital baseband generation and control unit. The human-machine interaction device is used to receive and output the landing information and operating frequency band of the landing signal to be detected. The two output terminals of the digital baseband generation and control unit are respectively connected to the two input terminals of the microwave conditioning unit. The digital baseband generation and control unit is used to simulate and output the landing signal to be detected according to the landing information and the operating frequency band under the control of the controller. The output terminals of the microwave conditioning units are all connected to the input terminals of the output antennas. The microwave conditioning units are used to form a path for the corresponding signal processing paths within themselves under the control of the controller. The output terminal of the positioning comparison unit is connected to the input terminal of the controller. The positioning comparison unit is used to detect the spatial position of the output antenna and output it under the control of the controller. The digital baseband generation and control unit includes: a field-programmable gate array (FPGA) control module, a radio frequency transceiver module, and auxiliary circuitry; wherein: The input terminal of the FPGA control module is connected to the output terminal of the human-machine interaction device, and the output terminal of the FPGA control module is connected to one input terminal of the radio frequency transceiver module. The FPGA control module is used to generate and output an analog signal of the landing signal to be detected based on the landing information under the control of the controller. The other input terminal of the RF transceiver module is connected to the output terminal of the human-machine interaction device to receive the working channel; the two output terminals of the RF transceiver module are respectively connected to the two input terminals of the microwave conditioning unit; the RF transceiver module is used to output the signal output by the FPGA control module using the working channel under the control of the controller. The auxiliary circuit is connected to the FPGA control module.

2. The field inspection instrument for landing airborne equipment according to claim 1, characterized in that, The positioning comparison unit includes: a comparison conversion module, a differential processor, and a receiving antenna whose spatial position is always consistent with the output antenna; wherein: The output terminal of the receiving antenna is connected to the input terminal of the differential processor. The receiving antenna is used to receive and output mobile communication signals and satellite positioning signals under the control of the controller. The output of the differential processor is connected to the input of the comparison and conversion module. The differential processor is used to determine and output the time stamp, the latitude and longitude of the field inspection instrument, and the elevation data of the field inspection instrument based on the mobile communication signal and the satellite positioning signal. The output of the comparison and conversion module serves as the output of the positioning comparison unit. The comparison and conversion module is used to determine and output the position of the receiving antenna based on the time stamp, the latitude and longitude of the field inspection instrument, and the elevation data of the field inspection instrument.

3. The field inspection instrument for landing airborne equipment according to claim 1, characterized in that, The FPGA control module includes: an IQ quadrature module, a gain adjustment module, a differential encoding module, a DA converter, and a first signal selection module; wherein: The input terminal of the IQ quadrature module is connected to the output terminal of the human-computer interaction device, and the output terminal of the IQ quadrature module is connected to the input terminal of the gain adjustment module. The IQ quadrature module is used to quadraturely modulate the analog signal of the landing signal to be detected based on the landing information. The output terminal of the gain adjustment module is connected to the input terminal of the first signal selection module; The two output terminals of the first signal selection module are respectively connected to the input terminal of the DA converter and the input terminal of the differential encoding module. The first signal selection module is used to output the landing signal to be tested to the differential encoding module when the landing signal to be tested is a microwave landing signal, a Volt landing signal, or a beacon landing signal, under the control of the controller; and to output the landing signal to be tested to the DA converter when the landing signal to be tested is an instrument landing signal. The output of the differential coding module is connected to the input of the DA converter; The output of the DA converter serves as the output of the FPGA control module.

4. The field inspection instrument for landing airborne equipment according to claim 1, characterized in that, The radio frequency transceiver module includes: a first filter, a first adjustable power attenuator, a mixer module, a broadband adjustable local oscillator, and a second signal selection module; wherein: The input terminal of the first filter is connected to the output terminal of the FPGA control module in the digital baseband generation control unit, and the output terminal of the first filter is connected to the input terminal of the first adjustable power attenuator. The output of the first adjustable power attenuator is connected to one input of the mixer module; The input terminal of the broadband adjustable local oscillator is connected to the output terminal of the human-machine interaction device, and the output terminal of the broadband adjustable local oscillator is connected to another input terminal of the mixing module. The broadband adjustable local oscillator is used to generate a carrier signal with the same frequency as the received working channel. The output terminal of the mixer module is connected to the input terminal of the second signal selection module. The mixer module is used to perform a mixing operation on the signal output by the FPGA control module and the signal output by the broadband adjustable local oscillator module. The two output terminals of the second signal selection module serve as the two output terminals of the radio frequency transceiver module. Under the control of the controller, the second signal selection module outputs the landing signal to be tested from one of its output terminals when the landing signal to be tested is a microwave landing signal or a glide slope instrument landing signal among instrument landing signals. When the landing signal to be tested is a Vulcan landing signal, a beacon landing signal, or a heading instrument landing signal among instrument landing signals, the second signal selection module outputs the landing signal to be tested from its other output terminal.

5. The field inspection instrument for landing airborne equipment according to any one of claims 1 to 4, characterized in that, If the landing signal to be detected is a microwave landing signal, then the landing information includes: magnetic heading azimuth and magnetic heading elevation. If the landing signal to be detected is a Voll landing signal, then the landing information includes: heading and azimuth angle; If the landing signal to be tested is an instrument landing signal, then the landing information includes: heading azimuth and glide slope angle; If the landing signal to be detected is a corresponding beacon landing signal, then the landing information includes: the specific frequency of the beacon landing signal.

6. The field inspection instrument according to any one of claims 1 to 4, characterized in that, Also includes: Power management unit; wherein: The output terminal of the power management unit is connected to the power supply terminal of the positioning comparison unit, the power supply terminal of the digital baseband generation control unit, the power supply terminal of the microwave conditioning unit, the power supply terminal of the human-machine interaction device, and the power supply terminal of the controller, respectively.

7. A method for detecting the antenna beamwidth of landing airborne equipment, characterized in that, A controller applied to the field inspection instrument as described in any one of claims 1 to 4; the detection method includes: When the landing information of the landing signal to be inspected is received through the human-computer interaction device in the field inspection instrument, the positioning comparison unit in the field inspection instrument is controlled to detect the spatial position of the output antenna in the field inspection instrument in real time. During the process of the output antenna continuously changing its position, each time the spatial position of the output antenna is the same as the boundary position of the standard range of the landing signal to be tested acquired by itself, the digital baseband generation and control unit in the field inspection instrument is controlled to simulate the output of the landing signal to be tested, and the corresponding signal processing path in the microwave conditioning unit in the field inspection instrument is controlled to form a path according to the landing signal to be tested. If, through the human-computer interaction device, the spatial position of the output antenna is always the same as the boundary position of the standard range of the landing signal to be tested acquired by itself, and a signal indicating that the landing airborne equipment has received the landing signal to be tested is received, then it is determined that the beamwidth of the antenna on the landing airborne equipment conforms to the standard range.

8. The detection method according to claim 7, characterized in that, The landing onboard equipment receives the landing signal to be checked, including: At least one antenna on the landing airborne equipment that is used to receive the landing signal to be tested receives the landing signal to be tested.

9. The detection method according to claim 7 or 8, characterized in that, The landing signal to be tested is: microwave landing signal, Volt landing signal, instrument landing signal, or beacon landing signal.

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