Automatic selection prompt method and system for aircraft guided landing based on signal triggering

Abstract

The present application belongs to the technical field of aircraft guided landing design, and specifically relates to a signal-triggered automatic selection prompt method and system for aircraft guided landing. The design can display the corresponding information on whether to continue the automatic guided landing when controlling the aircraft to automatically land on the ship deck, and give a voice prompt, so as to facilitate the pilot to quickly make a decision on whether to continue the automatic guided landing. The design can also automatically select the applicable guidance signal to control the aircraft to automatically land on the ship deck, and automatically configure the frequency band applicable to data transmission between the ship-borne data transmission system and the airborne data transmission system, thereby effectively reducing the pilot's task load.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft guided landing design, and specifically relates to an automatic selection prompt method and system for aircraft guided landing based on signal triggering. Background Art

[0002] When an aircraft is guided to land on a ship deck, the shipboard guidance computer sends guidance signals such as the relative position and distance detected by the guidance equipment to the shipboard data transmission system, which is then transmitted 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 land automatically on the ship deck. Figure 1 shown.

[0003] In some cases, manual operation assistance is required for guided landing of aircraft on the deck of a ship. For example, guidance equipment usually includes satellites, radars, and optoelectronics. The three have different applicable scenarios, and manual operation is required to select the guidance signal 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 U-band and L-band for data transmission. The two also have different applicable scenarios, and manual operation is required to select the applicable transmission mode for transmitting the guidance signal according to the specific scenario. In addition, when the shipborne guidance computer, airborne control system, shipborne data transmission system or airborne data transmission system malfunctions, guided landing cannot be carried out, and the guided landing procedure needs to be terminated in time.

[0004] The automatic guided landing process of an aircraft on the ship deck is fast, but manual operation assistance increases the pilot's task load and is prone to misoperation, which can create dangers.

[0005] This application is proposed in view of the above-mentioned technical defects. Summary of the Invention

[0006] The purpose of this application is to provide a method and system for automatically selecting prompts for guided landing of an aircraft based on signal triggering, so as to overcome or alleviate at least one of the technical defects of the known ones.

[0007] The technical solution of this application is:

[0008] On the one hand, a method for automatically selecting and prompting an aircraft guided landing based on a signal trigger is provided, including a process for automatically selecting a guidance signal;

[0009] The automatic guidance signal selection process includes identifying the validity of satellite, radar, and electro-optical guidance signals; 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 and the radar guidance signal are invalid and the electro-optical guidance signal is valid, selecting to use the electro-optical guidance signal to control the aircraft to automatically land on the ship deck; and when the satellite guidance signal, the radar guidance signal, and the electro-optical guidance signal are invalid, terminating the control of the automatic landing of the aircraft on the ship deck;

[0010] 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, with an allowable distance deviation of ΔR.

[0011] Calculate the deviation ΔR12 between R1 and R2. If ΔR12≤ΔR, then determine that the satellite guidance signal and the radar guidance signal are valid. Then calculate the deviation ΔR23 between R2 and R3. If ΔR23≤ΔR, then determine that the photoelectric guidance signal is valid. Otherwise, determine that the photoelectric guidance signal is invalid.

[0012] If ΔR12>ΔR, 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 photoelectric 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 photoelectric guidance signal is valid.

[0013] 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.

[0014] Optionally, in the above-mentioned automatic selection prompt method based on signal triggering for guiding the landing of the aircraft, the accurate guidance distance range of the satellite is greater than 18,000 m;

[0015] The radar accurate guidance distance range is 100m~18000m;

[0016] The photoelectric accurate guidance distance range is less than 100m.

[0017] Optionally, the above-mentioned automatic selection prompt method for aircraft guided landing based on signal triggering further includes a frequency band transmission mode automatic configuration process;

[0018] 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 not effective, 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 not effective, then the control of automatic landing of the aircraft on the ship deck is terminated.

[0019] Optionally, in the above-mentioned automatic selection prompt method for aircraft guided landing based on signal triggering, during the automatic configuration of the frequency band transmission mode, 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 is detected and fails to meet the requirements, then 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.

[0020] Optionally, the above-mentioned automatic selection prompting method for guided landing of an aircraft based on signal triggering further includes an automatic prompting process for guided landing;

[0021] The automatic prompt process for guided landing 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 will be given "allowed to connect to the automatic guided landing". 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 will be given "terminate the automatic guided landing".

[0022] On the other hand, there is provided an automatic selection prompt system for aircraft guided landing based on signal triggering, comprising a guidance signal automatic selection module;

[0023] The guidance signal automatic selection module is embedded in the airborne control system, and identifies the validity of satellite, radar, and photoelectric guidance signals. When the satellite guidance signal is valid, the module selects 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, the module 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, the module selects to use the photoelectric guidance signal to control the aircraft to automatically land on the ship deck. When the satellite guidance signal, the radar guidance signal, and the photoelectric guidance signal are invalid, the module terminates the control of the aircraft's automatic landing on the ship deck.

[0024] 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 R2, and the relative distance between aircraft and ships in the photoelectric guidance signal is R3, and the allowable distance deviation is ΔR;

[0025] Calculate the deviation ΔR12 between R1 and R2. If ΔR12≤ΔR, then determine that the satellite guidance signal and the radar guidance signal are valid. Then calculate the deviation ΔR23 between R2 and R3. If ΔR23≤ΔR, then determine that the photoelectric guidance signal is valid. Otherwise, determine that the photoelectric guidance signal is invalid.

[0026] If ΔR12>ΔR, 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 photoelectric 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 photoelectric guidance signal is valid.

[0027] 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.

[0028] Optionally, in the above-mentioned automatic selection prompt system for aircraft guided landing based on signal triggering, the satellite accurate guidance distance range is greater than 18000m;

[0029] The radar accurate guidance distance range is 100m~18000m;

[0030] The photoelectric accurate guidance distance range is less than 100m.

[0031] Optionally, the above-mentioned automatic selection prompt system for aircraft guided landing based on signal triggering further includes a frequency band transmission mode automatic configuration module;

[0032] The frequency band transmission mode automatic configuration module is carried on the aircraft and uses a spectrum analyzer to detect the effectiveness of data transmission between the shipborne data transmission system and the airborne data transmission system using the U-band and L-band. 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 not effective, but data transmission using the L-band is effective, 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 L-band is not effective, the automatic landing control of the aircraft on the ship deck is terminated.

[0033] Optionally, in the above-mentioned automatic selection prompt system for aircraft guided landing based on signal triggering, in the frequency band transmission mode automatic configuration module, if the spectrum analyzer detects that the strength 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 L-band cannot meet the requirements, then 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.

[0034] Optionally, the above-mentioned automatic selection prompting system for guided landing of an aircraft based on signal triggering further includes a guided landing automatic prompting module;

[0035] 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 voice prompter;

[0036] When controlling the aircraft to automatically land 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".

[0037] This application has at least the following beneficial technical effects:

[0038] Provided are a signal-triggered automatic selection prompt method and system for guided landing of an aircraft. The system is designed to display the corresponding information on whether to continue the automatic guided landing and give a voice prompt when controlling the automatic landing of an aircraft on a ship deck, thereby facilitating the pilot to quickly make a decision on whether to continue the automatic guided landing. The system is also designed to automatically select an appropriate guidance signal to control the automatic landing of the aircraft on the ship deck, and automatically configure a frequency band suitable for data transmission between a ship-borne data transmission system and an airborne data transmission system, thereby effectively reducing the pilot's task load. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 This is a schematic diagram of the existing system for guiding aircraft to land on a ship deck;

[0040] Figure 2 1 is a schematic diagram of an automatic selection prompt method for guided landing of an aircraft based on signal triggering provided in an embodiment of the present application;

[0041] Figure 3 is a schematic diagram illustrating the effectiveness of identifying satellite, radar, and optoelectronic guidance signals provided by an embodiment of the present application;

[0042] Figure 4 This is a schematic diagram of an automatic selection prompt system for aircraft guided landing based on signal triggering provided in an embodiment of the present application.

[0043] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0044] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0045] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application means that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0046] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0047] An automatic selection prompt method for aircraft landing guidance based on signal triggering, such as Figure 2 As shown, it includes the automatic prompt process of guided landing, the automatic selection process of guidance signal, and the automatic configuration process of frequency band transmission mode.

[0048] The automatic prompt process for guided landing is to obtain and display the fault conditions of the shipboard guidance computer, airborne control system, shipboard data transmission system, and 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, airborne control system, shipboard data transmission system, and airborne data transmission system, a voice prompt of "allow connection of automatic guided landing" will be given; if there is a fault in the shipboard guidance computer, airborne control system, shipboard data transmission system, or airborne data transmission system, a voice prompt of "terminate automatic guided landing" will be given. The pilot can make a quick decision on whether to continue the automatic guided landing based on this.

[0049] The automatic selection process of the guidance signal is to identify the validity of satellite, radar, and optoelectronic guidance signals. When the satellite guidance signal is valid, the satellite guidance signal is selected 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, the radar guidance signal is selected 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, the optoelectronic guidance signal is selected to control the aircraft to automatically land on the ship deck, thereby fully utilizing 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, the control of the aircraft's automatic landing on the ship deck is terminated, thereby reducing the pilot's task load.

[0050] During the automatic selection of guidance signals, the relative distances between aircraft and ships in satellite guidance signals, radar guidance signals, and optoelectronic guidance signals are used, combined with the distance ranges within which satellites, radars, and optoelectronics can accurately guide, to quickly and efficiently identify the effectiveness of satellite, radar, and optoelectronic guidance signals. Figure 3 shown.

[0051] 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. The allowable distance deviation is ΔR, and ΔR can be specifically taken as 5m.

[0052] Calculate the deviation ΔR12 of R1 and R2. If ΔR12≤ΔR, then the satellite guidance signal and the radar guidance signal are judged to be valid. Then calculate the deviation ΔR23 of R2 and R3. If ΔR23≤ΔR, then the photoelectric guidance signal is judged to be valid. Otherwise, the photoelectric guidance signal is judged to be invalid.

[0053] If ΔR12>ΔR, then calculate the deviation ΔR23 of R2 and R3. If ΔR23≤ΔR, then judge 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, then judge that the satellite guidance signal is valid, the radar guidance signal is invalid, and the photoelectric guidance signal is valid.

[0054] 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.

[0055] The satellite accurate guidance distance range can be greater than 18,000m, the radar accurate guidance distance range can be 100m~18,000m, and the optoelectronic accurate guidance distance range can be less than 100m.

[0056] The automatic configuration process of the frequency band transmission mode is to detect 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 valid, 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, thereby reducing the task load of the pilot.

[0057] 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 L-band fails to 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.

[0058] An automatic selection prompt system for aircraft landing based on signal triggering, such as Figure 4 As shown, it includes an automatic prompt module for guided landing, an automatic selection module for guidance signals, and an automatic configuration module for frequency band transmission mode.

[0059] The guided landing automatic prompt module is carried on the aircraft. It 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.

[0060] When controlling the aircraft to automatically land 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". The pilot can make a quick decision on whether to continue the automatic guidance landing based on this.

[0061] The guidance signal automatic selection module can be embedded in the airborne control system to identify the validity of satellite, radar, and optoelectronic guidance signals. When the satellite guidance signal is valid, the module chooses 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, the module chooses 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, the module chooses to use the optoelectronic guidance signal to control the aircraft to automatically land on the ship deck, thereby fully utilizing 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, the control of the aircraft's automatic landing on the ship deck is terminated, thereby reducing the pilot's task load.

[0062] The guidance signal automatic selection module is connected to the guidance landing automatic prompt module, and the display shows in real time whether the satellite guidance signal is invalid, the radar guidance signal is invalid, and the effectiveness of the photoelectric guidance signal.

[0063] The guidance signal automatic selection module uses the relative distances between aircraft and ships in satellite guidance signals, radar guidance signals, and optoelectronic guidance signals, combined with the distance ranges within which satellites, radars, and optoelectronics can accurately guide, to quickly and efficiently identify the effectiveness of satellite, radar, and optoelectronic guidance signals step by step.

[0064] 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. The allowable distance deviation is ΔR, and ΔR can be specifically taken as 5m.

[0065] Calculate the deviation ΔR12 of R1 and R2. If ΔR12≤ΔR, then the satellite guidance signal and the radar guidance signal are judged to be valid. Then calculate the deviation ΔR23 of R2 and R3. If ΔR23≤ΔR, then the photoelectric guidance signal is judged to be valid. Otherwise, the photoelectric guidance signal is judged to be invalid.

[0066] If ΔR12>ΔR, then calculate the deviation ΔR23 of R2 and R3. If ΔR23≤ΔR, then judge 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, then judge that the satellite guidance signal is valid, the radar guidance signal is invalid, and the photoelectric guidance signal is valid.

[0067] 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.

[0068] The satellite accurate guidance distance range can be greater than 18,000m, the radar accurate guidance distance range can be 100m~18,000m, and the optoelectronic accurate guidance distance range can be less than 100m.

[0069] The frequency band transmission mode automatic configuration module is carried on the aircraft and uses a spectrum analyzer to detect the effectiveness of data transmission between the shipborne data transmission system and the airborne data transmission system using the U-band and L-band. 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 L-band is invalid, the automatic landing control of the aircraft on the ship deck is terminated, thereby reducing the pilot's task load.

[0070] The frequency band transmission mode automatic configuration module is connected to the guided landing automatic prompt module, and the display shows in real time the effectiveness of data transmission between the shipborne data transmission system and the airborne data transmission system using the U band and L band.

[0071] 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 the L-band detected by the spectrum analyzer fails to 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.

[0072] The above-mentioned embodiment discloses a method and system for automatically selecting and prompting an aircraft for guided landing based on a signal trigger. The system is designed to display a corresponding indication of whether to continue the automatic guided landing when controlling the aircraft to automatically land on the ship deck, and to give a voice prompt. This facilitates the pilot to quickly make a decision on whether to continue the automatic guided landing. The system is also designed to automatically select an applicable guidance signal to control the aircraft to automatically land on the ship deck, and to automatically configure a frequency band applicable to data transmission between the shipborne data transmission system and the airborne data transmission system, thereby effectively reducing the pilot's task load.

[0073] In addition, those skilled in the art should also be able to realize that the various modules of the signal-triggered automatic selection prompt system for aircraft guided landing disclosed in the embodiments of the present application can be implemented by electronic hardware, computer software, or a combination of the two. In order to clearly illustrate the interchangeability of hardware and software, this application generally describes them according to their functions. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can choose to adopt different methods to implement the described functions for each specific application and its actual constraints, but such implementation should not be considered to be beyond the scope of this application.

[0074] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A method for automatically selecting and prompting an aircraft to guide landing based on a signal trigger, characterized in that: Including the automatic selection process of the guidance signal; The automatic guidance signal selection process includes identifying the validity of satellite, radar, and electro-optical guidance signals; 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 and the radar guidance signal are invalid and the electro-optical guidance signal is valid, selecting to use the electro-optical guidance signal to control the aircraft to automatically land on the ship deck; and when the satellite guidance signal, the radar guidance signal, and the electro-optical guidance signal are 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, with an allowable distance deviation of ΔR. Calculate the deviation ΔR12 between R1 and R2. If ΔR12≤ΔR, then determine that the satellite guidance signal and the radar guidance signal are valid. Then calculate the deviation ΔR23 between R2 and R3. If ΔR23≤ΔR, then determine that the photoelectric guidance signal is valid. Otherwise, determine that the photoelectric guidance signal is invalid. If ΔR12>ΔR, 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 photoelectric 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 photoelectric guidance signal is valid. If ΔR12>ΔR, and ΔR23>ΔR, and ΔR13>ΔR, then determine whether R1 is within the accurate satellite guidance 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 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 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 invalid. The accurate guidance distance range of satellite is greater than 18000m; The radar accurate guidance distance range is 100m to 18000m; The photoelectric accurate guidance distance range is less than 100m.

2. The method for automatically selecting and prompting an aircraft landing based on a signal trigger according to claim 1, 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 not effective, 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 not effective, then the control of automatic landing of the aircraft on the ship deck is terminated.

3. The method for automatically selecting and prompting an aircraft landing based on a signal trigger according to claim 2, 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 L-band fails to 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 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 L-band is valid.

4. The method for automatically selecting and prompting an aircraft landing based on a signal trigger according to claim 3, characterized in that: It also includes the automatic prompting process for guided landing; The automatic prompting process for guided landing 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 of "allowing to connect the automatic guided 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 of "terminating the automatic guided landing" will be given.

5. An automatic selection prompt system for aircraft landing guidance based on signal triggering, characterized in that: Including guidance signal automatic selection module; The guidance signal automatic selection module is embedded in the airborne control system, and identifies the validity of satellite, radar, and photoelectric guidance signals. When the satellite guidance signal is valid, the module selects 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, the module 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, the module selects to use the photoelectric guidance signal to control the aircraft to automatically land on the ship deck. When the satellite guidance signal, the radar guidance signal, and the photoelectric guidance signal are invalid, the module terminates the control of the aircraft's automatic landing on the ship deck. 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 R2, and the relative distance between aircraft and ships in the photoelectric guidance signal is R3, and the allowable distance deviation is ΔR; Calculate the deviation ΔR12 between R1 and R2. If ΔR12≤ΔR, then determine that the satellite guidance signal and the radar guidance signal are valid. Then calculate the deviation ΔR23 between R2 and R3. If ΔR23≤ΔR, then determine that the photoelectric guidance signal is valid. Otherwise, determine that the photoelectric guidance signal is invalid. If ΔR12>ΔR, 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 photoelectric 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 photoelectric guidance signal is valid. If ΔR12>ΔR, and ΔR23>ΔR, and ΔR13>ΔR, then determine whether R1 is within the accurate satellite guidance 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 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 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 invalid. The accurate guidance distance range of satellite is greater than 18000m; The radar accurate guidance distance range is 100m to 18000m; The photoelectric accurate guidance distance range is less than 100m.

6. The automatic selection prompting system for aircraft guided landing based on signal triggering according to claim 5, characterized in that: It also includes a module for automatic configuration of frequency band transmission modes; The frequency band transmission mode automatic configuration module is carried on the aircraft and uses a spectrum analyzer to detect the effectiveness of data transmission between the shipborne data transmission system and the airborne data transmission system using the U-band and L-band. 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 not effective, but data transmission using the L-band is effective, 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 L-band is not effective, the automatic landing control of the aircraft on the ship deck is terminated.

7. The automatic selection prompting system for guided landing of an aircraft based on signal triggering according to claim 6, characterized in that: In the frequency band transmission mode automatic configuration module, if the spectrum analyzer detects that the data transmission strength or signal-to-noise ratio between the shipborne data transmission system and the airborne data transmission system using the U-band and L-band does not 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 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 L-band is valid.

8. The automatic selection prompting system for guided landing of an aircraft based on signal triggering according to claim 7, characterized in that: It also includes a guided landing automatic prompting module; 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 voice prompter; When controlling the aircraft to automatically land 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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