Signal-triggering-based automatic selection prompting method and system for guiding landing of airplane

Abstract

The invention belongs to the technical field of aircraft guided landing design, and particularly relates to an aircraft guided landing automatic selection prompting method and system based on signal triggering, and the design can correspondingly display whether to continue automatic guided landing or not when an aircraft is controlled to automatically land on a ship deck, and gives a voice prompt. In this way, a pilot can quickly make a decision on whether to continue to automatically guide landing or not, a suitable guide signal can be automatically selected to control an aircraft to automatically land on a ship deck, and a frequency band suitable for data transmission between a ship-borne data transmission system and an airborne data transmission system is automatically configured. Therefore, the task load of the pilot can be effectively reduced.

Description

Technical Field

[0001] This application belongs to the technical field of aircraft landing guidance design, and particularly relates to an aircraft landing guidance automatic selection and prompt method and system based on signal triggering. Background Art

[0002] When an aircraft is guided to land on the deck of a ship, the shipborne guidance computer sends guidance signals such as the relative position distance detected by the guidance equipment to the shipborne data transmission system, and uses the shipborne data transmission system to transmit to the airborne data transmission system. The airborne control system uses the guidance signals received by the airborne data transmission system to control the aircraft to automatically land on the deck of the ship, as Figure 1 shown.

[0003] In some cases, manual operation assistance is required for an aircraft to be guided to land on the deck of a ship. For example, the guidance equipment usually includes satellites, radars, and optoelectronics, and the three have different applicable scenarios. It is necessary for humans to select the guidance signals of the applicable guidance equipment according to the specific scenario. The shipborne data transmission system and the airborne data transmission system are usually configured to use the U band and the L band for data transmission, and the two also have different applicable scenarios. It is necessary for humans to select the applicable transmission mode to transmit the guidance signals according to the specific scenario. Moreover, when the shipborne guidance computer, the airborne control system, the shipborne data transmission system, or the airborne data transmission system fails abnormally, the guided landing cannot be carried out, and the guided landing procedure needs to be terminated in a timely manner.

[0004] The automatic guided landing process of an aircraft on the deck of a ship is fast. Manual operation assistance increases the task load of the pilot and is prone to misoperation, thus causing danger.

[0005] In view of the existence of the above technical defects, this application is proposed. Summary of the Invention

[0006] The purpose of this application is to provide an aircraft landing guidance automatic selection and prompt method and system based on signal triggering to overcome or mitigate at least one aspect of the known technical defects.

[0007] The technical solution of this application is as follows: On the one hand, an aircraft landing guidance automatic selection and prompt method based on signal triggering is provided, including an automatic selection process of guidance signals; The automatic selection process of the guidance signal includes identifying the effectiveness of satellite, radar, and optoelectronic guidance signals. When the satellite guidance signal is effective, it is selected to use the satellite guidance signal to control the aircraft to automatically land on the ship's deck. When the satellite guidance signal is invalid and the radar guidance signal is effective, it is selected to use the radar guidance signal to control the aircraft to automatically land on the ship's deck. When the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is effective, it is selected to use the optoelectronic guidance signal to control the aircraft to automatically land on the ship's deck. When the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is invalid, the control of the aircraft automatically landing on the ship's deck is terminated; During the automatic selection process of the guidance signal, the relative distance between the aircraft and the ship in the satellite guidance signal is defined as R1, the relative distance R2 between the aircraft and the ship in the radar guidance signal, and the relative distance R3 between the aircraft and the ship in the optoelectronic guidance signal. The allowable distance deviation is ΔR; Calculate the deviation ΔR12 between R1 and R2. If ΔR12 ≤ ΔR, it is determined that the satellite guidance signal is effective and the radar guidance signal is effective. Then, calculate the deviation ΔR23 between R2 and R3. If ΔR23 ≤ ΔR, it is determined that the optoelectronic guidance signal is effective; otherwise, it is determined that the optoelectronic guidance signal is invalid; If ΔR12 > ΔR, calculate the deviation ΔR23 between R2 and R3. If ΔR23 ≤ ΔR, it is determined that the satellite guidance signal is invalid, the radar guidance signal is effective, and the optoelectronic guidance signal is effective; otherwise, calculate the deviation ΔR13 between R1 and R3. If ΔR13 ≤ ΔR, it is determined that the satellite guidance signal is effective, the radar guidance signal is invalid, and the optoelectronic guidance signal is effective; If ΔR12 > ΔR, and ΔR23 > ΔR, ΔR13 > ΔR, it is determined whether R1 is within the satellite accurate guidance distance range. If so, it is determined that the satellite guidance signal is effective, the radar guidance signal is invalid, and the optoelectronic guidance signal is invalid; otherwise, it is determined whether R2 is within the radar accurate guidance distance range. If so, it is determined that the satellite guidance signal is invalid, the radar guidance signal is effective, and the optoelectronic guidance signal is invalid; otherwise, it is determined whether R3 is within the optoelectronic accurate guidance distance range. If so, it is determined that the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is effective; otherwise, it is determined that the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is invalid.

[0008] Optionally, in the above method for automatically selecting and prompting based on signal triggering for aircraft guidance and landing, the satellite accurate guidance distance range is taken to be greater than 18000m; The radar accurate guidance distance range is taken to be 100m - 18000m; The optoelectronic accurate guidance distance range is taken to be less than 100m.

[0009] Optionally, in the above method for automatically selecting and prompting aircraft landing guidance based on signal triggering, it further includes an automatic configuration process for the frequency band transmission mode; The automatic configuration process for the frequency band transmission mode includes detecting the effectiveness of data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band. If the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band is effective, then configure the shipborne data transmission system and the airborne data transmission system to use the U frequency band for data transmission. If the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band is ineffective and the data transmission using the L frequency band is effective, then configure the shipborne data transmission system and the airborne data transmission system to use the L frequency band for data transmission. If the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band is ineffective, then terminate the control of the aircraft's automatic landing on the ship's deck.

[0010] Optionally, in the above method for automatically selecting and prompting aircraft landing guidance based on signal triggering, during the automatic configuration process for the frequency band transmission mode, if the intensity or signal-to-noise ratio of the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band cannot meet the requirements, then it is determined that the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band is ineffective. Otherwise, it is determined that the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band is effective.

[0011] Optionally, in the above method for automatically selecting and prompting aircraft landing guidance based on signal triggering, it further includes an automatic prompting process for landing guidance; The automatic prompting process for landing guidance includes obtaining and displaying the fault situations of the shipborne guidance computer, the airborne control system, the shipborne data transmission system, and the airborne data transmission system. When controlling the aircraft to automatically land on the ship's deck, when there are no faults in the shipborne guidance computer, the airborne control system, the shipborne data transmission system, and the airborne data transmission system, a voice prompt of "Allow to connect for automatic landing guidance" is given. When there are faults in the shipborne guidance computer, the airborne control system, the shipborne data transmission system, or the airborne data transmission system, a voice prompt of "Terminate automatic landing guidance" is given.

[0012] On the other hand, there is provided a system for automatically selecting and prompting aircraft landing guidance based on signal triggering, including an automatic selection module for guidance signals; The automatic guidance signal selection module is embedded in the airborne control system to identify the effectiveness of satellite, radar, and optoelectronic guidance signals. When the satellite guidance signal is effective, it selects to use the satellite guidance signal to control the aircraft to automatically land on the ship's deck. When the satellite guidance signal is invalid and the radar guidance signal is effective, it selects to use the radar guidance signal to control the aircraft to automatically land on the ship's deck. When the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is effective, it selects to use the optoelectronic guidance signal to control the aircraft to automatically land on the ship's deck. When the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is invalid, it terminates the control of the aircraft's automatic landing on the ship's deck; In the automatic guidance signal selection module, the relative distance between the aircraft and the ship in the satellite guidance signal is defined as R1, the relative distance R2 between the aircraft and the ship in the radar guidance signal, and the relative distance R3 between the aircraft and the ship in the optoelectronic guidance signal. The allowable distance deviation is ΔR; Calculate the deviation ΔR12 between R1 and R2. If ΔR12 ≤ ΔR, it is determined that the satellite guidance signal is effective and the radar guidance signal is effective. Then calculate the deviation ΔR23 between R2 and R3. If ΔR23 ≤ ΔR, it is determined that the optoelectronic guidance signal is effective; otherwise, it is determined that the optoelectronic guidance signal is invalid; If ΔR12 > ΔR, calculate the deviation ΔR23 between R2 and R3. If ΔR23 ≤ ΔR, it is determined that the satellite guidance signal is invalid, the radar guidance signal is effective, and the optoelectronic guidance signal is effective; otherwise, calculate the deviation ΔR13 between R1 and R3. If ΔR13 ≤ ΔR, it is determined that the satellite guidance signal is effective, the radar guidance signal is invalid, and the optoelectronic guidance signal is effective; If ΔR12 > ΔR, and ΔR23 > ΔR, ΔR13 > ΔR, then determine whether R1 is within the satellite accurate guidance distance range. If so, it is determined that the satellite guidance signal is effective, the radar guidance signal is invalid, and the optoelectronic guidance signal is invalid; otherwise, determine whether R2 is within the radar accurate guidance distance range. If so, it is determined that the satellite guidance signal is invalid, the radar guidance signal is effective, and the optoelectronic guidance signal is invalid; otherwise, determine whether R3 is within the optoelectronic accurate guidance distance range. If so, it is determined that the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is effective; otherwise, it is determined that the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is invalid.

[0013] Optionally, in the above aircraft guidance landing automatic selection prompt system based on signal triggering, the satellite accurate guidance distance range is greater than 18000m; The radar accurate guidance distance range is 100m - 18000m; The optoelectronic accurate guidance distance range is less than 100m.

[0014] Optionally, in the above-mentioned aircraft guided landing signal-triggered automatic selection prompt system, there is also a frequency band transmission mode automatic configuration module; The frequency band transmission mode automatic configuration module is carried on the aircraft. It detects the effectiveness of data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band through a spectrum analyzer. If the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band is effective, it configures the shipborne data transmission system and the airborne data transmission system to use the U frequency band for data transmission. If the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band is ineffective and the data transmission using the L frequency band is effective, it configures the shipborne data transmission system and the airborne data transmission system to use the L frequency band for data transmission. If the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band is ineffective, it terminates the control of the aircraft's automatic landing on the ship's deck.

[0015] Optionally, in the above-mentioned aircraft guided landing signal-triggered automatic selection prompt system, in the frequency band transmission mode automatic configuration module, if the intensity or signal-to-noise ratio of the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band cannot meet the requirements, it is determined that the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band is ineffective. Otherwise, it is determined that the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band is effective.

[0016] Optionally, in the above-mentioned aircraft guided landing signal-triggered automatic selection prompt system, there is also a guided landing automatic prompt module; The guided landing automatic prompt module is carried on the aircraft. It obtains the fault situations of the shipborne guidance computer, the airborne control system, the shipborne data transmission system, and the airborne data transmission system through the fault detection devices of the shipborne guidance computer, the airborne control system, the shipborne data transmission system, and the airborne data transmission system, and is equipped with a display and a voice prompt device; When controlling the aircraft to automatically land on the ship's deck, the display shows the fault situations of the shipborne guidance computer, the airborne control system, the shipborne data transmission system, and the airborne data transmission system. When there is no fault in the shipborne guidance computer, the airborne control system, the shipborne data transmission system, and the airborne data transmission system, the voice prompt device gives a voice prompt of "Allow to connect to automatic guided landing". When there is a fault in the shipborne guidance computer, the airborne control system, the shipborne data transmission system, or the airborne data transmission system, the voice prompt device gives a voice prompt of "Terminate automatic guided landing".

[0017] The present application has at least the following beneficial technical effects: Provided is a method and system for automatically selecting prompts based on signal triggering for aircraft guided landing, which are designed to display whether to continue automatic guided landing and give voice prompts when controlling an aircraft to automatically land on a ship deck, so as to facilitate the pilot to quickly make a decision on whether to continue automatic guided landing, and are designed to automatically select applicable guidance signals to control the aircraft to automatically land on the ship deck, and automatically configure the applicable frequency bands for data transmission between the shipborne data transmission system and the airborne data transmission system, thereby effectively reducing the pilot's task load. Brief Description of the Drawings

[0018] Figure 1 It is a schematic diagram of an existing system for guiding the landing of an aircraft on a ship deck; Figure 2 It is a schematic diagram of a method for automatically selecting prompts based on signal triggering for aircraft guided landing provided by an embodiment of the present application; Figure 3 It is a schematic diagram of identifying the effectiveness of satellite, radar, and optoelectronic guidance signals provided by an embodiment of the present application; Figure 4 It is a schematic diagram of a system for automatically selecting prompts based on signal triggering for aircraft guided landing provided by an embodiment of the present application.

[0019] To better illustrate this embodiment, some components in the drawings are omitted, enlarged, or reduced, which do not represent the dimensions of actual products. In addition, the drawings are only for illustrative purposes and cannot be construed as a limitation to the present application. Detailed Embodiments

[0020] To make the technical solutions and their advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in detail below with reference to the drawings. It can be understood that the specific embodiments described herein are only partial embodiments of the present application, which are only used to explain the present application and are not intended to limit the present application. It should be noted that for the sake of description, only the parts related to the present application are shown in the drawings, and other related parts can refer to the general design.

[0021] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the present application should be the ordinary meanings understood by those of ordinary skill in the art to which the present application belongs. The terms indicating directions used in the description of the present application are only used to represent relative directions or position relationships. When the absolute position of the object being described changes, its relative position relationship may also change accordingly. The "including" used in the description of the present application means that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0022] In addition, it should be noted that, unless otherwise clearly specified and limited, terms such as "installation" and "connection" used in the description of this application should be understood in a broad sense. For example, connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to specific circumstances.

[0023] An automatic selection and prompt method for aircraft guided landing based on signal triggering, as Figure 2 shown, includes an automatic prompt process for guided landing, an automatic selection process for guidance signals, and an automatic configuration process for frequency band transmission modes.

[0024] The automatic prompt process for guided landing is to obtain and display the fault situations of the shipborne guidance computer, the airborne control system, the shipborne data transmission system, and the airborne data transmission system. When controlling the aircraft to automatically land on the ship's deck, when there are no faults in the shipborne guidance computer, the airborne control system, the shipborne data transmission system, and the airborne data transmission system, a voice prompt of "Allow to connect to automatic guided landing" is given. When there are faults in the shipborne guidance computer, the airborne control system, the shipborne data transmission system, or the airborne data transmission system, a voice prompt of "Terminate automatic guided landing" is given. The pilot can make a decision on whether to continue automatic guided landing quickly based on this.

[0025] The automatic selection process for guidance signals is to identify the effectiveness of satellite, radar, and optoelectronic guidance signals. When the satellite guidance signal is effective, select to use the satellite guidance signal to control the aircraft to automatically land on the ship's deck. When the satellite guidance signal is invalid and the radar guidance signal is effective, select to use the radar guidance signal to control the aircraft to automatically land on the ship's deck. When the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is effective, select to use the optoelectronic guidance signal to control the aircraft to automatically land on the ship's deck, so as to make full use of the advantages of satellite, radar, and optoelectronic guidance equipment. When the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is invalid, terminate the control of the aircraft to automatically land on the ship's deck, which can reduce the pilot's task load in this way.

[0026] In the automatic selection process for guidance signals, the relative distance between the aircraft and the ship in the satellite guidance signal, the radar guidance signal, and the optoelectronic guidance signal is used, combined with the distance range that can be accurately guided by the satellite, radar, and optoelectronic, to quickly and efficiently complete the identification of the effectiveness of the satellite, radar, and optoelectronic guidance signals step by step, as Figure 3 shown.

[0027] Define the relative distance between the aircraft and the ship in the satellite guidance signal as R1, the relative distance between the aircraft and the ship in the radar guidance signal as R2, and the relative distance between the aircraft and the ship in the optoelectronic guidance signal as R3. The allowable distance deviation is ΔR, and ΔR can specifically take 5m.

[0028] Calculate the deviation ΔR12 of R1 and R2. If ΔR12 ≤ ΔR, then determine that the satellite guidance signal is valid and the radar guidance signal is valid. Furthermore, calculate the deviation ΔR23 of R2 and R3. If ΔR23 ≤ ΔR, then determine that the optoelectronic guidance signal is valid; otherwise, determine that the optoelectronic guidance signal is invalid.

[0029] If ΔR12 > ΔR, then calculate the deviation ΔR23 of R2 and R3. If ΔR23 ≤ ΔR, then determine that the satellite guidance signal is invalid, the radar guidance signal is valid, and the optoelectronic guidance signal is valid; otherwise, calculate the deviation ΔR13 of R1 and R3. If ΔR13 ≤ ΔR, then determine that the satellite guidance signal is valid, the radar guidance signal is invalid, and the optoelectronic guidance signal is valid.

[0030] If ΔR12 > ΔR, and ΔR23 > ΔR and ΔR13 > ΔR, then determine whether R1 is within the satellite accurate guidance distance range. If so, then determine that the satellite guidance signal is valid, the radar guidance signal is invalid, and the optoelectronic guidance signal is invalid; otherwise, determine whether R2 is within the radar accurate guidance distance range. If so, then determine that the satellite guidance signal is invalid, the radar guidance signal is valid, and the optoelectronic guidance signal is invalid; otherwise, determine whether R3 is within the optoelectronic accurate guidance distance range. If so, then determine that the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is valid; otherwise, determine that the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is invalid.

[0031] The satellite accurate guidance distance range can be taken as greater than 18000m, the radar accurate guidance distance range can be taken as 100m - 18000m, and the optoelectronic accurate guidance distance range can be taken as less than 100m.

[0032] The automatic configuration process of the frequency band transmission mode is as follows: Detect the effectiveness of data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band. If the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band is effective, then configure the data transmission between the shipborne data transmission system and the airborne data transmission system to use the U frequency band. If the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band is invalid and the data transmission using the L frequency band is effective, then configure the data transmission between the shipborne data transmission system and the airborne data transmission system to use the L frequency band. If the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band is invalid, then terminate the control of the aircraft automatically landing on the ship's deck, which can reduce the pilot's task load.

[0033] If the intensity or signal-to-noise ratio of data transmission between the shipborne data transmission system and the airborne data transmission system using the U band and the L band cannot meet the requirements, it is determined that the data transmission between the shipborne data transmission system and the airborne data transmission system using the U band and the L band is invalid; otherwise, it is determined that the data transmission between the shipborne data transmission system and the airborne data transmission system using the U band and the L band is valid.

[0034] An aircraft landing guidance signal-triggered automatic selection prompt system, as Figure 4 shown, includes a landing guidance automatic prompt module, a guidance signal automatic selection module, and a frequency band transmission mode automatic configuration module.

[0035] The landing guidance automatic prompt module is carried on the aircraft. Through the fault detection devices of the shipborne guidance computer, the airborne control system, the shipborne data transmission system, and the airborne data transmission system, the fault situations of the shipborne guidance computer, the airborne control system, the shipborne data transmission system, and the airborne data transmission system are obtained, and a display and a voice prompt are configured.

[0036] When controlling the aircraft to automatically land on the ship's deck, the display shows the fault situations of the shipborne guidance computer, the airborne control system, the shipborne data transmission system, and the airborne data transmission system. When there is no fault in the shipborne guidance computer, the airborne control system, the shipborne data transmission system, and the airborne data transmission system, the voice prompt gives a voice prompt of "Permission to connect to automatic landing guidance". When there is a fault in the shipborne guidance computer, the airborne control system, the shipborne data transmission system, or the airborne data transmission system, the voice prompt gives a voice prompt of "Terminate automatic landing guidance", and the pilot can make a decision on whether to continue automatic landing guidance quickly based on this.

[0037] The guidance signal automatic selection module can be embedded in the airborne control system to identify the effectiveness of satellite, radar, and optoelectronic guidance signals. When the satellite guidance signal is effective, it selects to use the satellite guidance signal to control the aircraft to automatically land on the ship's deck. When the satellite guidance signal is invalid and the radar guidance signal is effective, it selects to use the radar guidance signal to control the aircraft to automatically land on the ship's deck. When the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is effective, it selects to use the optoelectronic guidance signal to control the aircraft to automatically land on the ship's deck, realizing the full utilization of the advantages of satellite, radar, and optoelectronic guidance equipment. When the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is invalid, it terminates the control of the aircraft to automatically land on the ship's deck, thereby reducing the pilot's task load.

[0038] The guidance signal automatic selection module is connected to the landing guidance automatic prompt module, and the display shows the effectiveness of the satellite guidance signal being invalid, the radar guidance signal being invalid, and the optoelectronic guidance signal in real time.

[0039] The automatic guidance signal selection module uses the relative distance between the aircraft and the ship in the satellite guidance signal, radar guidance signal, and optoelectronic guidance signal, and combines the distance ranges that the satellite, radar, and optoelectronic can accurately guide to quickly and efficiently complete the identification of the effectiveness of the satellite, radar, and optoelectronic guidance signals step by step.

[0040] Define the relative distance between the aircraft and the ship in the satellite guidance signal as R1, the relative distance between the aircraft and the ship in the radar guidance signal as R2, and the relative distance between the aircraft and the ship in the optoelectronic guidance signal as R3. The allowable distance deviation is ΔR, and ΔR can specifically take 5m.

[0041] Calculate the deviation ΔR12 between R1 and R2. If ΔR12 ≤ ΔR, then it is judged that the satellite guidance signal is valid and the radar guidance signal is valid. Then calculate the deviation ΔR23 between R2 and R3. If ΔR23 ≤ ΔR, then it is judged that the optoelectronic guidance signal is valid; otherwise, it is judged that the optoelectronic guidance signal is invalid.

[0042] If ΔR12 > ΔR, then calculate the deviation ΔR23 between R2 and R3. If ΔR23 ≤ ΔR, then it is judged that the satellite guidance signal is invalid, the radar guidance signal is valid, and the optoelectronic guidance signal is valid; otherwise, calculate the deviation ΔR13 between R1 and R3. If ΔR13 ≤ ΔR, then it is judged that the satellite guidance signal is valid, the radar guidance signal is invalid, and the optoelectronic guidance signal is valid.

[0043] If ΔR12 > ΔR, and ΔR23 > ΔR, ΔR13 > ΔR, then judge whether R1 is within the accurate guidance distance range of the satellite. If so, then it is judged that the satellite guidance signal is valid, the radar guidance signal is invalid, and the optoelectronic guidance signal is invalid; otherwise, judge whether R2 is within the accurate guidance distance range of the radar. If so, then it is judged that the satellite guidance signal is invalid, the radar guidance signal is valid, and the optoelectronic guidance signal is invalid; otherwise, judge whether R3 is within the accurate guidance distance range of the optoelectronic. If so, then it is judged that the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is valid; otherwise, it is judged that the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is invalid.

[0044] The accurate guidance distance range of the satellite can be taken as greater than 18000m, the accurate guidance distance range of the radar can be taken as 100m - 18000m, and the accurate guidance distance range of the optoelectronic can be taken as less than 100m.

[0045] The automatic configuration module for the frequency band transmission mode is installed on the aircraft. It detects the effectiveness of data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band through a spectrum analyzer. If the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band is effective, it configures the data transmission between the shipborne data transmission system and the airborne data transmission system to use the U frequency band. If the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band is ineffective and the data transmission using the L frequency band is effective, it configures the data transmission between the shipborne data transmission system and the airborne data transmission system to use the L frequency band. If the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band is ineffective, it terminates the control of the aircraft's automatic landing on the ship's deck, thereby reducing the pilot's task load.

[0046] The automatic configuration module for the frequency band transmission mode is connected to the automatic prompt module for guiding the landing. The display real-time displays the effectiveness of data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band.

[0047] If the intensity or signal-to-noise ratio of the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band detected by the spectrum analyzer cannot meet the requirements, it is determined that the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band is ineffective. Otherwise, it is determined that the data transmission between the shipborne data transmission system and the airborne data transmission system using the U frequency band and the L frequency band is effective.

[0048] The above-mentioned method and system for automatically selecting and prompting based on signal triggering for aircraft guided landing disclosed in the embodiment are designed to display whether to continue automatic guidance during the automatic landing of the aircraft on the ship's deck and give voice prompts, thereby facilitating the pilot to quickly make a decision on whether to continue automatic guidance. And it is designed to automatically select the applicable guidance signal to control the aircraft's automatic landing on the ship's deck, and automatically configure the applicable frequency band for data transmission between the shipborne data transmission system and the airborne data transmission system, so as to effectively reduce the pilot's task load.

[0049] In addition, those skilled in the art should also be able to realize that each module of the automatic selection prompt system for aircraft guided landing based on signal triggering disclosed in the embodiments of the present application can be implemented by electronic hardware, computer software, or a combination of both. To clearly illustrate the interchangeability of hardware and software, in the present application, it is generally described according to functions. Whether these functions are executed in a hardware or software manner depends on the specific application and design constraints of the technical solution. Those skilled in the art can choose different methods to implement the described functions for each specific application and its actual constraints. However, such implementation should not be considered to exceed the scope of the present application.

[0050] So far, the technical solutions of the present application have been described in conjunction with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features. After these changes or substitutions, the technical solutions will fall within the protection scope of the present application.

Claims

1. An automatic selection prompting method for guiding an aircraft to land based on a signal trigger, characterized in that: Including automatic selection process of guidance signal; The automatic guidance signal selection process includes identifying the validity of satellite, radar, and optoelectronic guidance signals, and when the satellite guidance signal is valid, selecting to use the satellite guidance signal to control the aircraft to automatically land on the ship deck; when the satellite guidance signal is invalid and the radar guidance signal is valid, selecting to use the radar guidance signal to control the aircraft to automatically land on the ship deck; when the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is valid, selecting to use the optoelectronic guidance signal to control the aircraft to automatically land on the ship deck; when the satellite guidance signal is invalid, the radar guidance signal is invalid, and the optoelectronic guidance signal is invalid, terminating the control of the automatic landing of the aircraft on the ship deck; During the automatic selection of guidance signals, the relative distance between aircraft and ships in satellite guidance signals is defined as R1, the relative distance between aircraft and ships in radar guidance signals is defined as R2, and the relative distance between aircraft and ships in optoelectronic guidance signals is defined as R3, and the allowable distance deviation is ΔR; Calculate the deviation ΔR12 of R1 and R2. If ΔR12≤ΔR, it is determined that the satellite guidance signal and the radar guidance signal are valid. Then calculate the deviation ΔR23 of R2 and R3. If ΔR23≤ΔR, it is determined that the photoelectric guidance signal is valid. Otherwise, it is determined that the photoelectric guidance signal is invalid. If ΔR12>ΔR, calculate the deviation ΔR23 of R2 and R3. If ΔR23≤ΔR, it is judged that the satellite guidance signal is invalid, the radar guidance signal is valid, and the photoelectric guidance signal is valid. Otherwise, calculate the deviation ΔR13 of R1 and R3. If ΔR13≤ΔR, it is judged that the satellite guidance signal is valid, the radar guidance signal is invalid, and the photoelectric guidance signal is valid. If ΔR12>ΔR, and ΔR23>ΔR, ΔR13>ΔR, then determine whether R1 is within the accurate satellite guidance distance range. If so, determine that the satellite guidance signal is valid, the radar guidance signal is invalid, and the photoelectric guidance signal is invalid. Otherwise, determine whether R2 is within the accurate radar guidance distance range. If so, determine that the satellite guidance signal is invalid, the radar guidance signal is valid, and the photoelectric guidance signal is invalid. Otherwise, determine whether R3 is within the accurate photoelectric guidance distance range. If so, determine that the satellite guidance signal is invalid, the radar guidance signal is invalid, and the photoelectric guidance signal is valid. Otherwise, determine that the satellite guidance signal is invalid, the radar guidance signal is invalid, and the photoelectric guidance signal is valid. Otherwise, determine that the satellite guidance signal is invalid, the radar guidance signal is invalid, and the photoelectric guidance signal is invalid.

2. The method for automatically selecting and prompting an aircraft to guide landing based on a signal trigger according to claim 1, characterized in that: The accurate satellite guidance distance range is greater than 18000m; The radar accurate guidance distance range is 100m~18000m; The photoelectric accurate guidance distance range is less than 100m.

3. The method for automatically selecting and prompting an aircraft to guide landing based on a signal trigger according to claim 2, characterized in that: It also includes the automatic configuration process of the frequency band transmission mode; The automatic configuration process of the frequency band transmission mode includes detecting the effectiveness of data transmission between the shipborne data transmission system and the airborne data transmission system using the U band and the L band. If data transmission between the shipborne data transmission system and the airborne data transmission system using the U band is effective, then the shipborne data transmission system and the airborne data transmission system are configured to use the U band for data transmission. If data transmission between the shipborne data transmission system and the airborne data transmission system using the U band is invalid, and data transmission using the L band is effective, then the shipborne data transmission system and the airborne data transmission system are configured to use the L band for data transmission. If data transmission between the shipborne data transmission system and the airborne data transmission system using the U band and the L band is invalid, the control of automatic landing of the aircraft on the ship deck is terminated.

4. The method for automatically selecting and prompting an aircraft to guide landing based on a signal trigger according to claim 3, characterized in that: During the automatic configuration of the frequency band transmission mode, if the strength or signal-to-noise ratio of the data transmission between the shipborne data transmission system and the airborne data transmission system using the U-band and the L-band cannot meet the requirements, it is judged that the data transmission between the shipborne data transmission system and the airborne data transmission system using the U-band and the L-band is invalid; otherwise, it is judged that the data transmission between the shipborne data transmission system and the airborne data transmission system using the U-band and the L-band is valid.

5. The method for automatically selecting and prompting an aircraft to guide landing based on a signal trigger according to claim 4, characterized in that: It also includes the process of guiding the automatic cueing of landing; The automatic guidance landing prompt process includes acquiring and displaying the fault conditions of the shipboard guidance computer, the airborne control system, the shipboard data transmission system and the airborne data transmission system. When controlling the automatic landing of the aircraft on the ship deck, if there is no fault in the shipboard guidance computer, the airborne control system, the shipboard data transmission system and the airborne data transmission system, a voice prompt "allow connection of automatic guidance landing" will be given; if there is a fault in the shipboard guidance computer, the airborne control system, the shipboard data transmission system or the airborne data transmission system, a voice prompt "terminate automatic guidance landing" will be given.

6. An automatic selection prompting system for aircraft guided landing based on signal triggering, characterized in that: Including a guidance signal automatic selection module; The guidance signal automatic selection module is embedded in the airborne control system, identifies the validity of satellite, radar, and photoelectric guidance signals, and selects to use the satellite guidance signal to control the aircraft to automatically land on the ship deck when the satellite guidance signal is valid; when the satellite guidance signal is invalid and the radar guidance signal is valid, selects to use the radar guidance signal to control the aircraft to automatically land on the ship deck; when the satellite guidance signal is invalid, the radar guidance signal is invalid, and the photoelectric guidance signal is valid, selects to use the photoelectric guidance signal to control the aircraft to automatically land on the ship deck; when the satellite guidance signal is invalid, the radar guidance signal is invalid, and the photoelectric guidance signal is invalid, the control of the automatic landing of the aircraft on the ship deck is terminated; In the guidance signal automatic selection module, the relative distance between aircraft and ships in the satellite guidance signal is defined as R1, the relative distance between aircraft and ships in the radar guidance signal is defined as R2, and the relative distance between aircraft and ships in the photoelectric guidance signal is defined as R3, and the allowable distance deviation is ΔR; Calculate the deviation ΔR12 of R1 and R2. If ΔR12≤ΔR, it is determined that the satellite guidance signal and the radar guidance signal are valid. Then calculate the deviation ΔR23 of R2 and R3. If ΔR23≤ΔR, it is determined that the photoelectric guidance signal is valid. Otherwise, it is determined that the photoelectric guidance signal is invalid. If ΔR12>ΔR, calculate the deviation ΔR23 of R2 and R3. If ΔR23≤ΔR, it is judged that the satellite guidance signal is invalid, the radar guidance signal is valid, and the photoelectric guidance signal is valid. Otherwise, calculate the deviation ΔR13 of R1 and R3. If ΔR13≤ΔR, it is judged that the satellite guidance signal is valid, the radar guidance signal is invalid, and the photoelectric guidance signal is valid. If ΔR12>ΔR, and ΔR23>ΔR, ΔR13>ΔR, then determine whether R1 is within the accurate satellite guidance distance range. If so, determine that the satellite guidance signal is valid, the radar guidance signal is invalid, and the photoelectric guidance signal is invalid. Otherwise, determine whether R2 is within the accurate radar guidance distance range. If so, determine that the satellite guidance signal is invalid, the radar guidance signal is valid, and the photoelectric guidance signal is invalid. Otherwise, determine whether R3 is within the accurate photoelectric guidance distance range. If so, determine that the satellite guidance signal is invalid, the radar guidance signal is invalid, and the photoelectric guidance signal is valid. Otherwise, determine that the satellite guidance signal is invalid, the radar guidance signal is invalid, and the photoelectric guidance signal is valid. Otherwise, determine that the satellite guidance signal is invalid, the radar guidance signal is invalid, and the photoelectric guidance signal is invalid.

7. The automatic selection prompting system for aircraft guided landing based on signal triggering according to claim 6, characterized in that: The accurate satellite guidance distance range is greater than 18000m; The radar accurate guidance distance range is 100m~18000m; The photoelectric accurate guidance distance range is less than 100m.

8. The automatic selection prompting system for aircraft guided landing based on signal triggering according to claim 7, characterized in that: It also includes a frequency band transmission mode automatic configuration module; The frequency band transmission mode automatic configuration module is carried on the aircraft, and detects the effectiveness of data transmission between the shipborne data transmission system and the airborne data transmission system using the U band and the L band through a spectrum analyzer. If data transmission between the shipborne data transmission system and the airborne data transmission system using the U band is effective, the shipborne data transmission system and the airborne data transmission system are configured to use the U band for data transmission. If data transmission between the shipborne data transmission system and the airborne data transmission system using the U band is invalid, and data transmission using the L band is valid, the shipborne data transmission system and the airborne data transmission system are configured to use the L band for data transmission. If data transmission between the shipborne data transmission system and the airborne data transmission system using the U band and the L band is invalid, the control of automatic landing of the aircraft on the ship deck is terminated.

9. The automatic selection prompting system for aircraft guided landing based on signal triggering according to claim 8, characterized in that: In the frequency band transmission mode automatic configuration module, if the intensity or signal-to-noise ratio of the data transmission between the shipborne data transmission system and the airborne data transmission system using the U-band and L-band detected by the spectrum analyzer cannot meet the requirements, it is judged that the data transmission between the shipborne data transmission system and the airborne data transmission system using the U-band and L-band is invalid; otherwise, it is judged that the data transmission between the shipborne data transmission system and the airborne data transmission system using the U-band and L-band is valid.

10. The automatic selection prompting system for aircraft guided landing based on signal triggering according to claim 9, characterized in that: It also includes a module for guiding the landing and automatically prompting; The guided landing automatic prompt module is carried on the aircraft, and obtains the fault conditions of the shipboard guidance computer, airborne control system, shipboard data transmission system, and airborne data transmission system through the fault detection equipment of the shipboard guidance computer, airborne control system, shipboard data transmission system, and airborne data transmission system, and is equipped with a display and a voice prompter; When controlling the aircraft to land automatically on the deck of a ship, the display shows the fault conditions of the shipboard guidance computer, the airborne control system, the shipboard data transmission system and the airborne data transmission system. When there are no faults in the shipboard guidance computer, the airborne control system, the shipboard data transmission system and the airborne data transmission system, the voice prompter gives a voice prompt of "allowing to connect the automatic guidance landing". When there are faults in the shipboard guidance computer, the airborne control system, the shipboard data transmission system or the airborne data transmission system, the voice prompter gives a voice prompt of "terminating the automatic guidance landing".

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