Method and system for guiding aircraft landing on ship deck

Abstract

The present application belongs to the technical field of aircraft guidance and landing design, and specifically relates to a method and system for guiding an aircraft to land on a ship deck. The method is designed to dynamically adjust the fusion weights #imgabs3#, #imgabs4#, and #imgabs5# of the guidance deviations detected by satellites, radars, and optoelectronic guidance equipment based on the relative sizes of the guidance deviations #imgabs0#, #imgabs1#, and #imgabs2# detected by satellites, radars, and optoelectronic guidance equipment. The guidance deviations detected by satellites, radars, and optoelectronic guidance equipment are fused, and the fused guidance deviations are used to automatically control the aircraft to land on the ship deck, thereby achieving non-similar triple-redundant configuration of the guidance deviations. The method can fully utilize the anti-interference capability and measurement accuracy of satellites, radars, and optoelectronic guidance equipment within different distance ranges to ensure the accuracy of the calculated fused guidance deviation #imgabs6#, achieve accurate guidance of the aircraft landing on the ship deck, and improve problems such as uneven data switching.

Description

Technical Field

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

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

[0003] The guidance equipment for guiding the landing of aircraft on the deck of a ship usually includes satellites, radars, and optoelectronics. Currently, most designs use the guidance deviation detected by a single guidance device to automatically control the aircraft to land on the ship deck. However, different guidance devices have different anti-interference capabilities and measurement accuracy within different distance ranges. It is difficult to accurately guide the aircraft to land on the ship deck by using the guidance deviation detected by a single guidance device. For this reason, some technical solutions are designed to switch the guidance deviations detected by different guidance devices 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 device and uneven data switching.

[0004] In addition, at present, in order to reduce the risk of data transmission between shipboard guidance computers and airborne control computers, a dual-redundancy design is adopted for the data link transmission system, but the same transmission frequency is often used. It is a similar design and is easily interfered with at the same time, and cannot effectively guarantee the reliability of data transmission between shipboard guidance computers and airborne control computers.

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

[0006] The purpose of the present application is to provide a method and system for guiding an aircraft to land on a ship deck, so as to overcome or alleviate at least one of the existing technical deficiencies.

[0007] The technical solution of this application is:

[0008] On the one hand, a method for guiding an aircraft to land on a ship deck is provided, comprising detecting guidance deviations using satellites, radars, and optoelectronic guidance equipment, fusing the guidance deviations detected by the satellites, radars, and optoelectronic guidance equipment, and automatically controlling the aircraft to land on the ship deck using the fused guidance deviations;

[0009] The guidance deviations detected by satellites, radars, and optoelectronic guidance equipment are integrated, specifically:

[0010] ;

[0011] in,

[0012] To guide the deviation for integration;

[0013] 、 、 Guidance deviations detected by satellites, radars, and optoelectronic guidance equipment;

[0014] 、 、 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:

[0015] 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 ;

[0016] 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 ;

[0017] 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 ;

[0018] 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 .

[0019] Optionally, in the above-mentioned method for guiding the landing of an aircraft on a ship deck, the fusion weight of the guidance deviation detected by the satellite, radar, and optoelectronic guidance equipment is 、 、 , the initial value is 1, the minimum value is 0, and the maximum value is 2.

[0020] Optionally, in the above-mentioned method for guiding the landing of an aircraft on a ship deck, the fusion weight of the guidance deviation detected by the satellite, radar, and optoelectronic guidance equipment is 、 、 , the step size of each increase is 0.05, and the step size of each decrease is 0.1.

[0021] On the other hand, a system for guiding an aircraft to land on a ship deck is provided, comprising a shipboard guidance computer, a data link transmission system, and an onboard control computer;

[0022] The shipboard guidance computer uses satellites, radars, and optoelectronic guidance equipment to detect guidance deviations, fuses the guidance deviations detected by satellites, radars, and optoelectronic guidance equipment, and transmits the fused guidance deviations to the onboard control computer via a data link transmission system. The onboard control computer automatically controls the aircraft to land on the ship's deck based on the fused guidance deviations.

[0023] The shipboard guidance computer integrates the guidance deviations detected by satellites, radars, and optoelectronic guidance equipment, specifically:

[0024] ;

[0025] in,

[0026] To guide the deviation for integration;

[0027] 、 、 Guidance deviations detected by satellite, radar, and optoelectronic guidance equipment include altitude deviation and lateral deviation between the aircraft and the ideal glide path;

[0028] 、 、 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:

[0029] 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 ;

[0030] 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 ;

[0031] 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 ;

[0032] 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 .

[0033] In the above-mentioned aircraft landing guidance system on the ship deck, the fusion weight of satellite, radar, and optoelectronic guidance equipment to detect guidance deviations 、 、 , the initial value is 1, the minimum value is 0, and the maximum value is 2.

[0034] In the above-mentioned aircraft landing guidance system on the ship deck, the fusion weight of satellite, radar, and optoelectronic guidance equipment to detect guidance deviations 、 、 , the step size of each increase is 0.05, and the step size of each decrease is 0.1.

[0035] In the above-mentioned aircraft guided landing system on the ship deck, 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 transmits data in the first frequency band, and the second frequency band transmission data link transmits data in the second frequency band;

[0036] When the data link transmission system in the first frequency band is valid, the data link transmission system automatically selects the first frequency band data link transmission to transmit data between the shipboard guidance computer and the airborne control computer; when the data link transmission system in the first frequency band is invalid and the data link transmission system in the second frequency band is valid, the data link transmission system automatically selects the second frequency band data link transmission to transmit data between the shipboard guidance computer and the airborne control computer;

[0037] 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.

[0038] In the above-mentioned aircraft guidance landing system on the ship deck, there are three onboard control computers, all of which transmit data with the ship-borne guidance computer through a data link transmission system. The three onboard control computers share data and resources, and the three onboard control computers can work together.

[0039] This application has at least the following beneficial technical effects:

[0040] Provides a method and system for guiding an aircraft to land on a ship deck, designed based on guidance deviations detected by satellite, radar, and optoelectronic guidance equipment 、 、 The relative size between them is used to dynamically adjust the fusion weight of satellite, radar and optoelectronic guidance equipment to detect and guide deviations. 、 、 , fuse the guidance deviations detected by satellites, radars, and optoelectronic guidance equipment, and use the fused guidance deviations to automatically control the aircraft to land on the ship deck, realizing non-similar three-redundant configuration of guidance deviations, which can make full use of the anti-interference ability and measurement accuracy of satellites, radars, and optoelectronic guidance equipment in different distance ranges to ensure the calculation of fused guidance deviations The accuracy of the system can be improved to achieve accurate guidance of the aircraft landing on the ship deck, and to improve the problems of uneven data switching. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 This is a schematic diagram of the existing aircraft guidance landing system on the ship deck;

[0042] Figure 2 This is a schematic diagram of dynamically adjusting the fusion weights of satellite, radar, and optoelectronic guidance equipment detection and guidance deviations provided by an embodiment of the present application;

[0043] Figure 3 This is a schematic diagram of a guided landing system for an aircraft on a ship deck provided in an embodiment of the present 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 or scientific terms used in the description of this application shall have the ordinary meanings understood by those skilled in the art to which this application belongs. The term "include" as used in the description of this application means that the concepts preceding the term include the concepts listed after the term and their equivalents, without excluding other related concepts.

[0046] In addition, the words used in the description of this application to indicate orientation 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 "installation", "connection" and similar words 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. Those skilled in the art can understand their specific meanings in this application based on the specific circumstances.

[0047] A method for guiding an aircraft to land on a ship deck utilizes satellites, radars, and optoelectronic guidance equipment to detect guidance deviations, fuses the guidance deviations detected by the satellites, radars, and optoelectronic guidance equipment, and utilizes the fused guidance deviations to automatically control the aircraft to land on the ship deck.

[0048] The guidance deviations detected by satellites, radars, and optoelectronic guidance equipment are integrated. The specific reference is as follows:

[0049] ;

[0050] in,

[0051] To guide the deviation for integration;

[0052] 、 、 Guidance deviations detected by satellite, radar, and optoelectronic guidance equipment include altitude deviation and lateral deviation between the aircraft and the ideal glide path;

[0053] 、 、 Fusion weights for detecting guidance deviations for satellites, radars, and optoelectronic guidance equipment.

[0054] Fusion weights of satellite, radar, and optoelectronic guidance equipment for detecting and guiding deviations 、 、 , based on guidance deviations detected by satellites, radars, and optoelectronic guidance equipment 、 、 The relative size between Figure 2 shown.

[0055] 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 ;

[0056] like Less than 、 , indicating the guidance deviation detected by the photoelectric guidance equipment , relative to the guidance deviation detected by satellite and radar guidance equipment 、 There is a large deviation. In this case, it can be considered that the guidance deviation detected by the photoelectric guidance equipment If there is a large error, increase the fusion weight of satellite and radar guidance equipment to detect the guidance deviation 、 , and reduce the fusion weight of the optoelectronic guidance equipment to detect the guidance deviation ;

[0057] like Less than 、 , indicating the guidance deviation detected by the Zhunda guidance equipment , relative to the guidance deviation detected by satellite and optoelectronic guidance equipment 、 There is a large deviation. At this time, it can be considered that the guidance deviation detected by the radar guidance equipment If there is a large error, increase the fusion weight of satellite and optoelectronic guidance equipment to detect the guidance deviation 、 , and reduce the fusion weight of radar guidance equipment detection guidance deviation ;

[0058] like Less than 、 , indicating the guidance deviation detected by the satellite equipment , relative to the guidance deviation detected by satellite and optoelectronic guidance equipment 、 There is a large deviation. In this case, it can be considered that the guidance deviation detected by the satellite equipment If there is a large error, increase the fusion weight of radar and optoelectronic guidance equipment to detect and guide the deviation. 、 , and reduce the fusion weight of satellite guidance equipment detection guidance deviation .

[0059] In the method for guiding an aircraft to land on a ship deck disclosed in the above embodiment, the guidance deviation detected by satellite, radar, and photoelectric guidance equipment is designed. 、 、 The relative size between them is used to dynamically adjust the fusion weight of satellite, radar and optoelectronic guidance equipment to detect and guide deviations. 、 、 , fuse the guidance deviations detected by satellites, radars, and optoelectronic guidance equipment, and use the fused guidance deviations to automatically control the aircraft to land on the ship deck, realizing non-similar three-redundant configuration of guidance deviations, which can make full use of the anti-interference ability and measurement accuracy of satellites, radars, and optoelectronic guidance equipment in different distance ranges to ensure the calculation of fused guidance deviations The accuracy of the system can be improved to achieve accurate guidance of the aircraft landing on the ship deck, and to improve the problems of uneven data switching.

[0060] Can design the fusion weight of satellite, radar, and optoelectronic guidance equipment to detect guidance deviations 、 、 , the initial value is 1, the minimum value is 0, and the maximum value is 2.

[0061] Fusion weights of satellite, radar, and optoelectronic guidance equipment for detecting and guiding deviations 、 、 The step size of each increase can be designed to be 0.05, and the step size of each decrease can be designed to be 0.1, so as to quickly reduce the large error to the fusion guidance deviation The influence of fusion guidance deviation is guaranteed to be calculated The accuracy of the system is guaranteed to achieve accurate guidance of the aircraft landing on the ship deck and ensure the smoothness of the data.

[0062] Based on the above embodiment disclosed in the aircraft guided landing method on the ship deck, the present application further discloses an aircraft guided landing system on the ship deck, including a ship-borne guidance computer, a data link transmission system, an onboard control computer, such as Figure 3 shown.

[0063] The shipboard guidance computer uses satellites, radars, and optoelectronic guidance equipment to detect guidance deviations, fuses the guidance deviations detected by satellites, radars, and optoelectronic guidance equipment, and transmits the fused guidance deviations 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 fused guidance deviations.

[0064] The shipboard guidance computer integrates the guidance deviations detected by satellites, radars, and optoelectronic guidance equipment. The specific reference is as follows:

[0065] ;

[0066] in,

[0067] To guide the deviation for integration;

[0068] 、 、 Guidance deviations detected by satellite, radar, and optoelectronic guidance equipment include altitude deviation and lateral deviation between the aircraft and the ideal glide path;

[0069] 、 、 Fusion weights for detecting guidance deviations for satellites, radars, and optoelectronic guidance equipment.

[0070] Fusion weights of satellite, radar, and optoelectronic guidance equipment for detecting and guiding deviations 、 、 , based on guidance deviations detected by satellites, radars, and optoelectronic guidance equipment 、 、 The relative size of the space between the two nodes is dynamically adjusted as follows:

[0071] 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 ;

[0072] like Less than 、 , indicating the guidance deviation detected by the photoelectric guidance equipment , relative to the guidance deviation detected by satellite and radar guidance equipment 、 There is a large deviation. In this case, it can be considered that the guidance deviation detected by the photoelectric guidance equipment If there is a large error, increase the fusion weight of satellite and radar guidance equipment to detect the guidance deviation 、 , and reduce the fusion weight of the optoelectronic guidance equipment to detect the guidance deviation ;

[0073] like Less than 、 , indicating the guidance deviation detected by the radar guidance equipment , relative to the guidance deviation detected by satellite and optoelectronic guidance equipment 、 There is a large deviation. At this time, it can be considered that the guidance deviation detected by the radar guidance equipment If there is a large error, increase the fusion weight of satellite and optoelectronic guidance equipment to detect the guidance deviation 、 , and reduce the fusion weight of radar guidance equipment detection guidance deviation ;

[0074] like Less than 、 , indicating the guidance deviation detected by the satellite equipment , relative to the guidance deviation detected by satellite and optoelectronic guidance equipment 、 There is a large deviation. In this case, it can be considered that the guidance deviation detected by the satellite equipment If there is a large error, increase the fusion weight of radar and optoelectronic guidance equipment to detect and guide the deviation. 、 , and reduce the fusion weight of satellite guidance equipment detection guidance deviation .

[0075] Can design the fusion weight of satellite, radar, and optoelectronic guidance equipment to detect guidance deviations 、 、 , the initial value is 1, the minimum value is 0, and the maximum value is 2.

[0076] Fusion weights of satellite, radar, and optoelectronic guidance equipment for detecting and guiding deviations 、 、 The step size of each increase can be designed to be 0.05, and the step size of each decrease can be designed to be 0.1, so as to quickly reduce the large deviation to the fusion guidance deviation The influence of fusion guidance deviation is guaranteed to be calculated The accuracy of the system is guaranteed to achieve accurate guidance of the aircraft landing on the ship deck and ensure the smoothness of the data.

[0077] 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 transmits data in a first frequency band, and the second frequency band transmission data link transmits data in a second frequency band. The first frequency band can be specifically a U band, and the second frequency band can be specifically an L band.

[0078] When the data link transmission system in the first frequency band is valid, the data link transmission system automatically selects the first frequency band transmission data link to transmit data between the shipboard guidance computer and the airborne control computer. When the data link transmission system in the first frequency band is invalid and the data link transmission system in the second frequency band is valid, the data link transmission system automatically selects the second frequency band transmission data link to transmit data between the shipboard guidance computer and the airborne control computer, thereby realizing non-similar redundant hot backup of the data link transmission system and effectively ensuring the reliability of data transmission between the shipboard guidance computer and the airborne control computer.

[0079] 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.

[0080] The data link transmission system can use a spectrum analyzer to detect the validity of the first frequency band transmission data link and the second frequency band transmission data link. If the intensity or signal-to-noise ratio of the data transmission of the first frequency band transmission data link and the second frequency band transmission data link detected by the spectrum analyzer cannot meet the requirements, then the first frequency band transmission data link and the second frequency band transmission data link are judged to be invalid; otherwise, the first frequency band transmission data link and the second frequency band transmission data link are judged to be valid.

[0081] There are three onboard control computers, all of which transmit data with the ship's guidance computer through a data link transmission system. The three onboard control computers share data and resources. The three onboard control computers can work together to achieve a triple-redundancy design of the onboard control computers, avoiding the failure of a single onboard control computer causing failure of the entire system, and improving the overall safety of the system.

[0082] The aircraft guided landing system on the ship deck disclosed in the above embodiment is designed to implement the aircraft guided landing method on the ship deck disclosed in the above embodiment. The description is relatively simple. For specific related matters, please refer to the relevant instructions in the part of the aircraft guided landing method on the ship deck. Its technical effects can also refer to the technical effects of the relevant parts of the aircraft guided landing method on the ship deck, which will not be repeated here.

[0083] In addition, those skilled in the art should also be able to realize that the functions of the aircraft guided landing 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 the two. This application only generally describes it according to its 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.

[0084] 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 guiding an aircraft to land on a ship deck, characterized in that: This 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 automatically controlling the aircraft to land on the ship deck using the fused guidance deviations; The guidance deviations detected by satellites, radars, and optoelectronic guidance equipment are integrated, specifically: in, r 融合 To guide the deviation for integration; r1, r2, and r3 are the guidance deviations detected by satellite, radar, and optoelectronic guidance equipment; k1, k2, and k3 are the fusion weights of the guidance deviations detected by satellites, radars, and optoelectronic guidance equipment. They are dynamically adjusted according to the relative sizes of the guidance deviations r1, r2, and r3 detected by satellites, radars, and optoelectronic guidance equipment. Specifically, they are: Calculate the difference △r between the guidance deviation r1 detected by the satellite guidance equipment and the guidance deviation r2 detected by the radar guidance equipment 12 , calculate the difference △r between the guidance deviation r1 detected by the satellite guidance equipment and the guidance deviation r3 detected by the photoelectric guidance equipment 13 , calculate the difference △r between the guidance deviation r2 detected by the radar guidance equipment and the guidance deviation r3 detected by the photoelectric guidance equipment 23 ; If △r 12 Less than △r 13 ,△r 23 , then increase the fusion weights k1 and k2 of the satellite and radar guidance equipment to detect the guidance deviation, and reduce the fusion weight k3 of the optoelectronic guidance equipment to detect the guidance deviation; If △r 13 Less than △r 12 ,△r 23 , then increase the fusion weights k1 and k3 of the satellite and optoelectronic guidance equipment to detect the guidance deviation, and reduce the fusion weight k2 of the radar guidance equipment to detect the guidance deviation; If △r 23 Less than △r 12 ,△r 13 , then increase the fusion weights k2 and k3 of the radar and optoelectronic guidance equipment to detect the guidance deviation, and reduce the fusion weight k1 of the satellite guidance equipment to detect the guidance deviation; The fusion weights k1, k2, and k3 of the satellite, radar, and optoelectronic guidance equipment detection and guidance deviations are increased by 0.05 each time and decreased by 0.1 each time.

2. The method for guiding an aircraft to land on a ship deck according to claim 1, wherein: The fusion weights k1, k2, and k3 of the satellite, radar, and optoelectronic guidance equipment detection and guidance deviations have an initial value of 1, a minimum value of 0, and a maximum value of 2.

3. A system for guiding an aircraft to land on a ship deck, characterized in that: Including shipboard guidance computer, data link transmission system, and airborne control computer; The shipboard guidance computer uses satellites, radars, and optoelectronic guidance equipment to detect guidance deviations, fuses the guidance deviations detected by satellites, radars, and optoelectronic guidance equipment, and transmits the fused guidance deviations to the onboard control computer via a data link transmission system. The onboard control computer automatically controls the aircraft to land on the ship's deck based on the fused guidance deviations. The shipboard guidance computer integrates the guidance deviations detected by satellites, radars, and optoelectronic guidance equipment, specifically: in, r 融合 To guide the deviation for integration; r1, r2, and r3 are the guidance deviations detected by satellites, radars, and optoelectronic guidance equipment, including the altitude deviation and lateral deviation of the aircraft from the ideal glide path. k1, k2, and k3 are the fusion weights of the guidance deviations detected by satellites, radars, and optoelectronic guidance equipment. They are dynamically adjusted according to the relative sizes of the guidance deviations r1, r2, and r3 detected by satellites, radars, and optoelectronic guidance equipment. Specifically, they are: Calculate the difference △r between the guidance deviation r1 detected by the satellite guidance equipment and the guidance deviation r2 detected by the radar guidance equipment 12 ; Calculate the difference △r between the guidance deviation r1 detected by the satellite guidance equipment and the guidance deviation r3 detected by the photoelectric guidance equipment 13 Calculate the difference △r between the guidance deviation r2 detected by the radar guidance equipment and the guidance deviation r3 detected by the photoelectric guidance equipment 23 ; If △r 12 Less than △r 13 ,△r 23 , then increase the fusion weights k1 and k2 of the satellite and radar guidance equipment to detect the guidance deviation, and reduce the fusion weight k3 of the optoelectronic guidance equipment to detect the guidance deviation; If △r 13 Less than △r 12 ,△r 23 , then increase the fusion weights k1 and k3 of the satellite and optoelectronic guidance equipment to detect the guidance deviation, and reduce the fusion weight k2 of the radar guidance equipment to detect the guidance deviation; If △r 23 Less than △r 12 ,△r 13 , then increase the fusion weights k2 and k3 of the radar and optoelectronic guidance equipment to detect the guidance deviation, and reduce the fusion weight k1 of the satellite guidance equipment to detect the guidance deviation; The fusion weights k1, k2, and k3 of the satellite, radar, and optoelectronic guidance equipment detection and guidance deviations are increased by 0.05 each time and decreased by 0.1 each time.

4. The aircraft guided landing system on a ship deck according to claim 3, characterized in that: The fusion weights k1, k2, and k3 of the satellite, radar, and optoelectronic guidance equipment detection and guidance deviations have an initial value of 1, a minimum value of 0, and a maximum value of 2.

5. The aircraft guided landing system on a ship deck according to claim 4, 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 transmits data in the first frequency band, and the second frequency band transmission data link transmits data in the second frequency band; When the data link transmission system in the first frequency band is valid, the data link transmission system automatically selects the first frequency band data link transmission to transmit data between the shipboard guidance computer and the airborne control computer; when the data link transmission system in the first frequency band is invalid and the data link transmission system in the second frequency band is valid, the data link transmission system automatically selects the second frequency band data link transmission to transmit data 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.

6. The aircraft guided landing system on a ship deck according to claim 5, characterized in that: There are three onboard control computers, all of which transmit data with the ship's guidance computer through a data link transmission system. The three onboard control computers share data and resources, and the three onboard control computers can work together.

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