Method and system for guiding aircraft to land on steamship deck

Abstract

The invention belongs to the technical field of aircraft guided landing design, and particularly relates to a method and system for guided landing of an aircraft on a ship deck, and the method comprises the steps: dynamically adjusting fusion weights # imgabs3 #, # imgabs4 # and # imgabs5 # of guide deviations detected by satellites, radars and photoelectric guide equipment according to the relative sizes of the guide deviations # imgabs0 #, # imgabs1 # and # imgabs2 # detected by the satellites, the radars and the photoelectric guide equipment, and carrying out the dynamic adjustment of the fusion weights # imgabs3 #, # imgabs4 # and # imgabs5 # of the guide deviations detected by the satellites, the radars and the photoelectric guide equipment; the guiding deviations detected by satellites, radars and photoelectric guiding equipment are fused, the fused guiding deviations are used for automatically controlling an aircraft to land on a ship deck, non-similar three-redundancy configuration is carried out on the guiding deviations, the anti-interference capability and the measurement precision of the satellites, the radars and the photoelectric guiding equipment in different distance ranges can be fully utilized, and the accuracy of the aircraft landing is improved. The accuracy of calculating the fusion guiding deviation # imgabs6 # is ensured, accurate guiding of landing of an airplane on a ship deck is achieved, and the problems of unsmooth data switching and the like are solved.

Description

Technical Field

[0001] This application belongs to the technical field of aircraft landing guidance design, and particularly relates to a method and system for guiding an aircraft to land on a ship deck. Background Art

[0002] When guiding an aircraft to land on a ship deck, the shipborne guidance computer transmits the guidance deviation detected by the guidance equipment, usually including the altitude deviation and lateral deviation of the aircraft from the ideal glide path, to the airborne control computer through the data link transmission system. The airborne control computer automatically controls the aircraft to land on the ship deck based on the guidance deviation. As Figure 1 shown, it can greatly reduce the workload of the pilot and improve the safety of the aircraft landing on the ship deck.

[0003] For the guidance equipment for guiding an aircraft to land on a ship deck, there are usually satellites, radars, and optoelectronics. Currently, most designs use the guidance deviation detected by a single guidance equipment to automatically control the aircraft to land on the ship deck. However, within different distance ranges, different guidance equipment has different anti-interference capabilities and measurement accuracies. Using the guidance deviation detected by a single guidance equipment to control the aircraft to land on the ship deck is difficult to achieve accurate guidance for the aircraft to land on the ship deck. Therefore, in some technical solutions, the guidance deviation detected by different guidance equipment is switched and utilized within different distance ranges to control the aircraft to land on the ship deck. This technical solution has problems such as inappropriate switching timing of the guidance deviation detected by the guidance equipment and uneven data switching.

[0004] In addition, currently, in order to reduce the risk of data transmission between the shipborne guidance computer and the airborne control computer, a dual-redundancy design is adopted for the data link transmission system, but usually the same transmission frequency is used, which is a similar design and is easily interfered with simultaneously, and cannot effectively ensure the reliability of data transmission between the shipborne guidance computer and the airborne control computer.

[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 a method and system for guiding an aircraft to land on a ship deck 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, a method for guiding an aircraft to land on a ship deck is provided, including detecting the guidance deviation using satellite, radar, and optoelectronic guidance equipment, fusing the guidance deviation detected by the satellite, radar, and optoelectronic guidance equipment, and automatically controlling the aircraft to land on the ship deck using the fused guidance deviation; Fuse the guidance deviations detected by satellites, radars, and optoelectronic guidance devices, specifically as follows: ; Among them, is the fused guidance deviation; 、 、 are the guidance deviations detected by satellites, radars, and optoelectronic guidance devices; 、 、 are the fusion weights of the guidance deviations detected by satellites, radars, and optoelectronic guidance devices, and are dynamically adjusted according to the relative magnitudes of the guidance deviations 、 、 detected by satellites, radars, and optoelectronic guidance devices, specifically as follows: Calculate the difference between the guidance deviation detected by the satellite guidance device and the guidance deviation detected by the radar guidance device, calculate the difference between the guidance deviation detected by the satellite guidance device and the guidance deviation detected by the optoelectronic guidance device, and calculate the difference between the guidance deviation detected by the radar guidance device and the guidance deviation detected by the optoelectronic guidance device; If is less than 、 , then increase the fusion weights 、 of the guidance deviations detected by the satellite and radar guidance devices, and decrease the fusion weight of the guidance deviation detected by the optoelectronic guidance device; If is less than 、 , then increase the fusion weights 、 of the guidance deviations detected by the satellite and optoelectronic guidance devices, and decrease the fusion weight of the guidance deviation detected by the radar guidance device; If is less than 、 , then increase the fusion weights 、 of the guidance deviations detected by the radar and optoelectronic guidance devices, and decrease the fusion weight of the guidance deviation detected by the satellite guidance device.

[0008] Optionally, in the above method for guiding the landing of an aircraft on a ship deck, the fusion weights of the guiding deviations detected by the satellite, radar, and optoelectronic guiding devices , , , with an initial value of 1, a minimum value of 0, and a maximum value of 2.

[0009] Optionally, in the above method for guiding the landing of an aircraft on a ship deck, the fusion weights of the guiding deviations detected by the satellite, radar, and optoelectronic guiding devices , , , with a step size of 0.05 for each increase and a step size of 0.1 for each decrease.

[0010] On the other hand, a system for guiding the landing of an aircraft on a ship deck is provided, including an on-ship guiding computer, a data link transmission system, and an on-board control computer; The on-ship guiding computer uses the satellite, radar, and optoelectronic guiding devices to detect the guiding deviation, fuses the guiding deviations detected by the satellite, radar, and optoelectronic guiding devices, and transmits the fused guiding deviation to the on-board control computer through the data link transmission system. The on-board control computer automatically controls the aircraft to land on the ship deck based on the fused guiding deviation; The on-ship guiding computer fuses the guiding deviations detected by the satellite, radar, and optoelectronic guiding devices, specifically: ; Among them, is the fused guiding deviation; , , are the guiding deviations detected by the satellite, radar, and optoelectronic guiding devices, including the height deviation and lateral deviation between the aircraft and the ideal glide path; , , are the fusion weights of the guiding deviations detected by the satellite, radar, and optoelectronic guiding devices, and are dynamically adjusted according to the relative magnitudes of the guiding deviations , , detected by the satellite, radar, and optoelectronic guiding devices, specifically: Calculate the difference between the guiding deviation detected by the satellite guiding device and the guiding deviation detected by the radar guiding device; Calculate the difference between the guiding deviation detected by the satellite guiding device and the guiding deviation detected by the optoelectronic guiding device ; Calculate the guidance deviation detected by the radar guidance device and the guidance deviation detected by the optoelectronic guidance device difference ; If is less than , , then increase the fusion weight of the guidance deviation detected by the satellite and radar guidance devices , , and decrease the fusion weight of the guidance deviation detected by the optoelectronic guidance device ; If is less than , , then increase the fusion weight of the guidance deviation detected by the satellite and optoelectronic guidance devices , , and decrease the fusion weight of the guidance deviation detected by the radar guidance device ; If is less than , , then increase the fusion weight of the guidance deviation detected by the radar and optoelectronic guidance devices , , and decrease the fusion weight of the guidance deviation detected by the satellite guidance device .

[0011] In the above aircraft landing guidance system on the ship deck, the fusion weights of the guidance deviations detected by the satellite, radar, and optoelectronic guidance devices , , , the initial value is taken as 1, the minimum value is taken as 0, and the maximum value is taken as 2.

[0012] In the above aircraft landing guidance system on the ship deck, the fusion weights of the guidance deviations detected by the satellite, radar, and optoelectronic guidance devices , , , the step size for each increase is 0.05, and the step size for each decrease is 0.1.

[0013] In the above aircraft landing guidance system on the ship deck, the data link transmission system is configured with a first-band transmission data link and a second-band transmission data link. Among them, the first-band transmission data link transmits data in the first band, and the second-band transmission data link transmits data in the second band; When the data link transmission system transmits the data link effectively in the first frequency band, it automatically selects to transmit the data link in the first frequency band for data transmission between the shipborne guidance computer and the airborne control computer. When the data link transmission in the first frequency band is invalid and the data link transmission in the second frequency band is effective, it automatically selects to transmit the data link in the second frequency band for data transmission between the shipborne guidance computer and the airborne control computer; When the data link transmission in the first frequency band is invalid and the data link transmission in the second frequency band is invalid, the airborne control computer terminates the automatic control of the aircraft to land on the ship's deck.

[0014] In the above aircraft landing guidance system on the ship's deck, there are three airborne control computers, all of which transmit data with the shipborne guidance computer through the data link transmission system, and the three airborne control computers share data and resources and can work together.

[0015] The present application has at least the following beneficial technical effects: Provide a method and system for guiding the landing of an aircraft on the ship's deck, and design to dynamically adjust the fusion weights of the guidance deviations detected by the satellite, radar, and optoelectronic guidance devices according to the relative magnitudes of the guidance deviations detected by the satellite, radar, and optoelectronic guidance devices , , , dynamically adjust the fusion weights of the guidance deviations detected by the satellite, radar, and optoelectronic guidance devices, fuse the guidance deviations detected by the satellite, radar, and optoelectronic guidance devices, and use the fused guidance deviation to automatically control the aircraft to land on the ship's deck, realizing a non-similar triple redundancy configuration for the guidance deviation, making full use of the anti-interference ability and measurement accuracy of the satellite, radar, and optoelectronic guidance devices within different distance ranges, ensuring the accuracy of the calculated fused guidance deviation , , , and realizing accurate guidance for the aircraft to land on the ship's deck and improving problems such as uneven data switching. BRIEF DESCRIPTION OF THE DRAWINGS BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 is a schematic diagram of the existing aircraft landing guidance system on the ship's deck; Figure 2 is a schematic diagram of dynamically adjusting the fusion weights of the guidance deviations detected by the satellite, radar, and optoelectronic guidance devices provided by the embodiment of the present application; Figure 3 is a schematic diagram of the aircraft landing guidance system on the ship's deck provided by the embodiment of the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0017] To make the technical solutions and their advantages of this application clearer, the following will further clearly and completely describe the technical solutions of this application in conjunction with the accompanying drawings. It can be understood that the specific embodiments described herein are only partial embodiments of this application, which are only used to explain this application rather than limit this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design.

[0018] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The "including" used in the description of this application means that the concept appearing before this word covers the concepts listed after this word and their equivalents, without excluding other related concepts.

[0019] In addition, the words indicating directions used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that unless otherwise clearly specified and limited, the words 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 their specific meanings in this application according to the specific situation.

[0020] A method for guiding the landing of an aircraft on a ship deck, which uses satellite, radar, and optoelectronic guiding devices to detect guiding deviations, fuses the guiding deviations detected by the satellite, radar, and optoelectronic guiding devices, and automatically controls the aircraft to land on the ship deck using the fused guiding deviations.

[0021] The fusion of the guiding deviations detected by the satellite, radar, and optoelectronic guiding devices is specifically as follows: ; wherein, is the fused guiding deviation; , , are the guiding deviations detected by the satellite, radar, and optoelectronic guiding devices, including the height deviation and lateral deviation of the aircraft from the ideal glide path; , , are the fusion weights of the guiding deviations detected by the satellite, radar, and optoelectronic guiding devices.

[0022] Fusion weights of the guiding deviations detected by the satellite, radar, and optoelectronic guiding devices , , , according to the guidance deviations detected by satellite, radar, and optoelectronic guidance devices , , , perform dynamic adjustment based on the relative magnitudes among them, as shown in Figure 2 .

[0023] Calculate the difference between the guidance deviation detected by the satellite guidance device and the guidance deviation detected by the radar guidance device; Calculate the difference between the guidance deviation detected by the satellite guidance device and the guidance deviation detected by the optoelectronic guidance device; Calculate the difference between the guidance deviation detected by the radar guidance device and the guidance deviation detected by the optoelectronic guidance device; If is less than , , it indicates that the guidance deviation detected by the optoelectronic guidance device has a large deviation relative to the guidance deviations , detected by the satellite and radar guidance devices. At this time, it can be considered that the guidance deviation detected by the optoelectronic guidance device has a large error, then increase the fusion weights , of the guidance deviations detected by the satellite and radar guidance devices, and decrease the fusion weight of the guidance deviation detected by the optoelectronic guidance device; If is less than , , it indicates that the guidance deviation detected by the radar guidance device has a large deviation relative to the guidance deviations , detected by the satellite and optoelectronic guidance devices. At this time, it can be considered that the guidance deviation detected by the radar guidance device has a large error, then increase the fusion weights , of the guidance deviations detected by the satellite and optoelectronic guidance devices, and decrease the fusion weight of the guidance deviation detected by the radar guidance device; If is less than , , it indicates that the guidance deviation , relative to the guidance deviation detected by the satellite and optoelectronic guidance equipment and there is a large deviation. At this time, it can be considered that the guidance deviation detected by the satellite equipment has a large error, then increase the fusion weight of the guidance deviation detected by the radar and optoelectronic guidance equipment and , and reduce the fusion weight of the guidance deviation detected by the satellite guidance equipment .

[0024] In the method for guiding the landing of an aircraft on a ship deck disclosed in the above embodiment, it is designed to calculate the relative magnitudes of the guidance deviations detected by the satellite, radar, and optoelectronic guidance equipment , , , and dynamically adjust the fusion weights of the guidance deviations detected by the satellite, radar, and optoelectronic guidance equipment , , , fuse the guidance deviations detected by the satellite, radar, and optoelectronic guidance equipment, and automatically control the aircraft to land on the ship deck by using the fused guidance deviation, so as to achieve a non-similar triple redundancy configuration for the guidance deviation, make full use of the anti-interference ability and measurement accuracy of the satellite, radar, and optoelectronic guidance equipment within different distance ranges, ensure the accuracy of the calculated fused guidance deviation , achieve accurate guidance for the aircraft to land on the ship deck, and improve problems such as uneven data switching.

[0025] The fusion weights of the guidance deviations detected by the satellite, radar, and optoelectronic guidance equipment can be designed , , , with the initial value taken as 1, the minimum value taken as 0, and the maximum value taken as 2.

[0026] The fusion weights of the guidance deviations detected by the satellite, radar, and optoelectronic guidance equipment , , , the step size for each increase can be designed as 0.05, and the step size for each decrease can be designed as 0.1, so as to quickly reduce the influence of a large error on the fused guidance deviation , ensure the accuracy of the calculated fused guidance deviation , achieve accurate guidance for the aircraft to land on the ship deck, and ensure the smoothness of the data.

[0027] Based on the method for guiding the landing of an aircraft on a ship deck disclosed in the above embodiment, the present application further discloses an aircraft landing guidance system on a ship deck, including an on-board guidance computer, a data link transmission system, and an on-board control computer, as Figure 3 shown.

[0028] The shipborne guidance computer detects the guidance deviation using satellite, radar, and optoelectronic guidance devices, fuses the guidance deviations detected by the satellite, radar, and optoelectronic guidance devices, and transmits the fused guidance deviation to the airborne control computer through the data link transmission system. The airborne control computer automatically controls the aircraft to land on the ship's deck based on the fused guidance deviation.

[0029] The shipborne guidance computer fuses the guidance deviations detected by the satellite, radar, and optoelectronic guidance devices, specifically as follows: ; Among them, is the fused guidance deviation; , , are the guidance deviations detected by the satellite, radar, and optoelectronic guidance devices, including the altitude deviation and lateral deviation of the aircraft from the ideal glide path; , , are the fusion weights of the guidance deviations detected by the satellite, radar, and optoelectronic guidance devices.

[0030] The fusion weights of the guidance deviations detected by the satellite, radar, and optoelectronic guidance devices , , , are dynamically adjusted according to the relative magnitudes of the guidance deviations , , detected by the satellite, radar, and optoelectronic guidance devices, specifically as follows: Calculate the difference between the guidance deviation detected by the satellite guidance device and the guidance deviation detected by the radar guidance device; Calculate the difference between the guidance deviation detected by the satellite guidance device and the guidance deviation detected by the optoelectronic guidance device; Calculate the difference between the guidance deviation detected by the radar guidance device and the guidance deviation detected by the optoelectronic guidance device; If is less than , , it indicates that the guidance deviation detected by the optoelectronic guidance device , There is a large deviation. At this time, it can be considered that the guidance deviation detected by the optoelectronic guidance device has a large error, then increase the fusion weight of the guidance deviation detected by the satellite and radar guidance devices 、 , and decrease the fusion weight of the guidance deviation detected by the optoelectronic guidance device ; If is less than 、 , it indicates that the guidance deviation detected by the radar guidance device , relative to the guidance deviations detected by the satellite and optoelectronic guidance devices 、 has a large deviation. At this time, it can be considered that the guidance deviation detected by the radar guidance device has a large error, then increase the fusion weights of the guidance deviations detected by the satellite and optoelectronic guidance devices 、 , and decrease the fusion weight of the guidance deviation detected by the radar guidance device ; If is less than 、 , it indicates that the guidance deviation detected by the satellite device , relative to the guidance deviations detected by the satellite and optoelectronic guidance devices 、 has a large deviation. At this time, it can be considered that the guidance deviation detected by the satellite device has a large error, then increase the fusion weights of the guidance deviations detected by the radar and optoelectronic guidance devices 、 , and decrease the fusion weight of the guidance deviation detected by the satellite guidance device .

[0031] The fusion weights of the guidance deviations detected by the satellite, radar, and optoelectronic guidance devices 、 、 can be designed. The initial value is taken as 1, the minimum value is taken as 0, and the maximum value is taken as 2.

[0032] The fusion weights of the guidance deviations detected by the satellite, radar, and optoelectronic guidance devices 、 、 , the step size for each increase can be designed as 0.05, and the step size for each decrease can be designed as 0.1, so as to quickly reduce the influence of the large deviation on the fusion guidance deviation , ensure the accuracy of calculating the fusion guidance deviation , achieve accurate guidance for the aircraft to land on the ship's deck, and ensure the smoothness of the data.

[0033] The data link transmission system is configured with a first - band transmission data link and a second - band transmission data link. Among them, the first - band transmission data link transmits data in the first band, and the second - band transmission data link transmits data in the second band. Specifically, the first band can be the U band, and the second band can be the L band.

[0034] When the first - band transmission data link of the data link transmission system is valid, it automatically selects to use the first - band transmission data link to transmit data between the ship - borne guidance computer and the airborne control computer. When the first - band transmission data link is invalid and the second - band transmission data link is valid, it automatically selects to use the second - band transmission data link to transmit data between the ship - borne guidance computer and the airborne control computer, so as to realize the non - similar redundancy hot backup of the data link transmission system and effectively ensure the reliability of data transmission between the ship - borne guidance computer and the airborne control computer.

[0035] When the first - band transmission data link is invalid and the second - band transmission data link is invalid, the airborne control computer terminates the automatic control of the aircraft to land on the ship's deck.

[0036] The data link transmission system can use a spectrum analyzer to detect the effectiveness of the first - band transmission data link and the second - band transmission data link. If the spectrum analyzer detects that the intensity or signal - to - noise ratio of data transmission of the first - band transmission data link and the second - band transmission data link cannot meet the requirements, it is determined that the first - band transmission data link and the second - band transmission data link are invalid. Otherwise, it is determined that the first - band transmission data link and the second - band transmission data link are valid.

[0037] There are three airborne control computers, all of which transmit data with the ship - borne guidance computer through the data link transmission system, and the three airborne control computers share data and resources. The three airborne control computers can work together to realize the triple - redundancy design of the airborne control computer, avoid the failure of the entire system caused by the failure of a single airborne control computer, and improve the overall safety of the system.

[0038] The aircraft landing guidance system on the ship's deck disclosed in the above - mentioned embodiment is designed to implement the aircraft landing guidance method on the ship's deck disclosed in the above - mentioned embodiment. The description is relatively simple. For specific relevant parts, reference can be made to the relevant description in the part of the aircraft landing guidance method on the ship's deck. Its technical effects can also be referred to the technical effects of the relevant part of the aircraft landing guidance method on the ship's deck, which will not be elaborated here.

[0039] In addition, those skilled in the art should also be able to realize that the functions of the aircraft landing guidance system on the ship deck disclosed in the embodiments of the present application can be implemented by electronic hardware, computer software, or a combination of both. In the present application, only a general description of these functions is provided according to the 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.

[0040] So far, the technical solutions of the present application have been described in combination 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. A method for guiding an aircraft to land on a ship deck, characterized in that: It includes using satellites, radars, and optoelectronic guidance equipment to detect guidance deviations, fusing the guidance deviations detected by satellites, radars, and optoelectronic guidance equipment, and using the fused guidance deviations to automatically control the aircraft to land on the ship deck; The guidance deviations detected by satellites, radars, and optoelectronic guidance equipment are integrated, specifically: ； in, To guide the deviation for integration; , , Guidance deviations detected by satellites, radars, and optoelectronic guidance equipment; , , The fusion weight of the guidance deviation detected by satellite, radar, and optoelectronic guidance equipment is , , The relative size of the space is dynamically adjusted, specifically: Calculate guidance deviations detected by satellite guidance equipment Guidance deviation detected by radar guidance equipment The difference , calculate the guidance deviation detected by the satellite guidance equipment Guidance deviation detected by photoelectric guidance equipment The difference , calculate the guidance deviation detected by the radar guidance equipment Guidance deviation detected by photoelectric guidance equipment The difference ; like Less than , , then increase the fusion weight of satellite and radar guidance equipment detection guidance deviation , , and reduce the fusion weight of the optoelectronic guidance equipment to detect the guidance deviation ; like Less than , , then increase the fusion weight of satellite and optoelectronic guidance equipment detection and guidance deviation , , and reduce the fusion weight of radar guidance equipment detection guidance deviation ; like Less than , , then increase the fusion weight of radar and optoelectronic guidance equipment to detect guidance deviation , , and reduce the fusion weight of satellite guidance equipment detection guidance deviation .

2. The method for guiding an aircraft to land on a ship deck according to claim 1, characterized in that: Fusion weights of satellite, radar, and optoelectronic guidance equipment for detecting guidance deviations , , , the initial value is 1, the minimum value is 0, and the maximum value is 2.

3. The method for guiding an aircraft to land on a ship deck according to claim 2, characterized in that: Fusion weights of satellite, radar, and optoelectronic guidance equipment for detecting guidance deviations , , , the step size of each increase is 0.05, and the step size of each decrease is 0.

1.

4. A system for guiding an aircraft to land on a ship deck, characterized in that: Includes shipboard guidance computer, data link transmission system, and airborne control computer; The shipboard guidance computer detects guidance deviations using satellites, radars, and optoelectronic guidance equipment, fuses the guidance deviations detected by satellites, radars, and optoelectronic guidance equipment, and transmits the fused guidance deviations to the airborne control computer through a data link transmission system. The airborne control computer automatically controls the aircraft to land on the ship deck based on the fused guidance deviations. The shipboard guidance computer integrates the guidance deviations detected by satellite, radar, and optoelectronic guidance equipment, specifically: ； in, To guide the deviation for integration; , , Guidance deviations detected by satellite, radar, and optoelectronic guidance equipment include altitude deviation and lateral deviation between the aircraft and the ideal glide path; , , The fusion weight of the guidance deviation detected by satellite, radar, and optoelectronic guidance equipment is , , The relative size of the space is dynamically adjusted, specifically: Calculate guidance deviations detected by satellite guidance equipment Guidance deviation detected by radar guidance equipment The difference ; Calculate the guidance deviation detected by the satellite guidance equipment Guidance deviation detected by photoelectric guidance equipment The difference ; Calculate the guidance deviation detected by the radar guidance equipment Guidance deviation detected by photoelectric guidance equipment The difference ; like Less than , , then increase the fusion weight of satellite and radar guidance equipment detection guidance deviation , , and reduce the fusion weight of the optoelectronic guidance equipment to detect the guidance deviation ; like Less than , , then increase the fusion weight of satellite and optoelectronic guidance equipment detection and guidance deviation , , and reduce the fusion weight of radar guidance equipment detection guidance deviation ; like Less than , , then increase the fusion weight of radar and optoelectronic guidance equipment to detect guidance deviation , , and reduce the fusion weight of satellite guidance equipment detection guidance deviation .

5. The aircraft guided landing system on a ship deck according to claim 4, characterized in that: Fusion weights of satellite, radar, and optoelectronic guidance equipment for detecting guidance deviations , , , the initial value is 1, the minimum value is 0, and the maximum value is 2.

6. The aircraft guided landing system on a ship deck according to claim 5, characterized in that: Fusion weights of satellite, radar, and optoelectronic guidance equipment for detecting guidance deviations , , , the step size of each increase is 0.05, and the step size of each decrease is 0.

1.

7. The aircraft guided landing system on a ship deck according to claim 6, characterized in that: The data link transmission system is configured with a first frequency band transmission data link and a second frequency band transmission data link, wherein the first frequency band transmission data link performs data transmission in a first frequency band, and the second frequency band transmission data link performs data transmission in a second frequency band; When the data link transmission system of the first frequency band is valid, the data link transmission system automatically selects the data link transmission of the first frequency band to carry out data transmission between the shipboard guidance computer and the airborne control computer; when the data link transmission of the first frequency band is invalid and the data link transmission of the second frequency band is valid, the data link transmission system automatically selects the data link transmission of the second frequency band to carry out data transmission between the shipboard guidance computer and the airborne control computer; When the first frequency band transmission data link is invalid and the second frequency band transmission data link is invalid, the onboard control computer terminates automatic control of the aircraft to land on the ship deck.

8. The aircraft guided landing system on a ship deck according to claim 7, characterized in that: There are three onboard control computers, all of which transmit data with the shipboard guidance computer through the data link transmission system. The three onboard control computers share data and resources, and the three onboard control computers can work in coordination.

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