An airport navigation lighting control system based on flight information

Abstract

The present invention relates to the technical field of airport lighting equipment, and in particular to an airport navigation lighting control system based on flight information, comprising: an illumination unit for outputting navigation lighting using illumination parameters to generate navigation lighting information, an aviation interaction unit for generating and outputting real-time flight information, an information receiving unit for receiving the real-time flight information output by the aviation interaction unit to locate the real-time position of an aircraft in the air, an analysis unit for determining whether the flight status of the aircraft meets the standards and the reasons for not meeting the standards and generating corresponding processing instructions, and a control unit for receiving corresponding processing instructions to determine the illumination parameters of the illumination unit and send corresponding notifications to the aviation interaction unit. The present invention sends corresponding instructions to the aircraft based on the flight environment or real-time flight status of the aircraft and specifically adjusts the illumination parameters of the lights, while ensuring that the aircraft can land smoothly at a designated location, and effectively improves the navigation efficiency of the system of the present invention for aircraft landing.

Description

Technical Field

[0001] The invention relates to the technical field of airport lighting equipment, and in particular to an airport navigation lighting control system based on flight information. Background Art

[0002] The airport navigation lighting control system is a comprehensive system, which mainly includes approach lighting system, runway lighting system and taxiway lighting system. It follows strict standards and aims to provide necessary visual guidance and safety guarantee for aircraft takeoff, landing and taxiing, and ensure that aircraft can operate safely and accurately at night or in low visibility conditions. With the continuous advancement and innovation of aviation technology, in order to improve the safety and efficiency of flight, the airport navigation lighting system will also be continuously upgraded and improved, especially the research on approach lighting system and some runway lighting systems related to landing, so as to effectively complete the smooth landing of aircraft and contribute more to the development of aviation industry.

[0003] Chinese patent publication number: CN102098832A, discloses a distributed airport navigation lighting control system and method. The system of the present invention includes a field activity status sensor, a tower monitoring station, an intersection controller, a coordination controller, a straight segment controller, and a light signal PLC output interface, which are networked through a redundant Ethernet. The above scheme relies on the tower monitoring station to convert the position signal of the field moving object into a field activity status signal, and the status signal is sent to the light controller. The controller encodes the generated control instruction and transmits it to the designated light station through the redundant Ethernet to control the dimmer of each controlled object. It can be seen that the above scheme cannot send corresponding instructions to the aircraft based on the flight environment or real-time flight status of the aircraft and adjust the illumination parameters of the light in a targeted manner, resulting in the inability to guide the aircraft to the designated landing point, thereby failing to effectively ensure the navigation efficiency of the airport navigation lighting control system for the aircraft. Summary of the invention

[0004] To this end, the present invention provides an airport navigation lighting control system based on flight information to overcome the problem in the prior art that the environmental factors cannot be overcome to guide the aircraft to a designated landing point, resulting in low navigation efficiency for the aircraft landing.

[0005] To achieve the above object, the present invention provides an airport navigation lighting control system based on flight information, comprising:

[0006] An irradiation unit, comprising a plurality of irradiation lamp groups arranged on the ground in a corresponding order, each irradiation lamp group is used to output navigation light using corresponding irradiation parameters to generate navigation light information, wherein the irradiation parameters include irradiation brightness, irradiation concentration, flashing frequency and irradiation elevation angle, and the irradiation brightness and irradiation concentration are adjusted by the distance between the lamp beads and the lens in the corresponding irradiation lamp group;

[0007] An aviation interaction unit, which is arranged on the aircraft and connected to the illumination unit, is used to obtain the navigation light information on the ground, and to generate and output real-time flight information, wherein the flight information includes flight speed, flight altitude and flight pitch angle;

[0008] An information receiving unit, which is arranged on the ground and connected to the aviation interaction unit, is used to receive the real-time flight information generated and output by the aviation interaction unit, so as to locate the real-time three-dimensional coordinate position of the aircraft in the air according to the flight information;

[0009] an analysis unit, which is arranged on the ground and connected to the information receiving unit, and is used to determine whether the flight status of the aircraft meets the standard based on the two-dimensional coordinates of the predicted aircraft landing point determined according to the flight information, and to determine the reason for not meeting the standard based on the flight information; the analysis unit is also used to generate corresponding processing instructions according to the determined reason for not meeting the standard;

[0010] a control unit connected to the analysis unit, configured to determine the irradiation parameters of the irradiation unit based on the processing instructions output by the analysis unit, and to send a corresponding notification to the aviation interaction unit;

[0011] A database is connected to the analysis unit and is used to store prediction data of the two-dimensional coordinates of the predicted aircraft landing point determined according to the flight information.

[0012] Furthermore, the analysis unit is also provided with two-dimensional coordinates of a navigation point that matches the corresponding navigation light information. The analysis unit is used to determine whether the flight status of the aircraft meets the standards based on the absolute distance between the acquired predicted aircraft landing point two-dimensional coordinates and the navigation point two-dimensional coordinates, and, when it is determined that the flight status of the aircraft does not meet the standards, determine whether the aircraft recognizes the navigation light information output by the illumination unit based on the time node of acquiring the real-time flight information, or determine the reason why the flight status of the aircraft does not meet the standards based on the landing point connection line between the navigation point two-dimensional coordinates and the predicted aircraft landing point two-dimensional coordinates.

[0013] Furthermore, the analysis unit is also used to determine whether the aircraft recognizes the navigation light information output by the illumination unit based on the interaction time, and to determine the illumination brightness of the illumination unit based on the interaction time difference according to the determination result, or to determine the reason why the aircraft's flight status does not meet the standard based on the landing point connection line between the two-dimensional coordinates of the navigation light landing point and the two-dimensional coordinates of the predicted aircraft landing point; wherein the interaction time is the cumulative time taken for the illumination unit to output the navigation light information to the information receiving unit to receive the real-time flight information.

[0014] Furthermore, the analysis unit is also used to increase the illumination brightness of the illumination unit based on the interaction duration difference, and the increase in the illumination brightness of the illumination unit is proportional to the interaction duration difference; wherein the interaction duration difference is the difference between the interaction duration and the preset interaction duration.

[0015] Furthermore, the analysis unit is also used to adjust the bead transmission distance to correct the illumination brightness based on the brightness difference when the illumination brightness of the illumination unit increases to the brightness critical value, and the correction amplitude of the illumination brightness is proportional to the bead transmission distance; wherein, the brightness difference is the difference between the brightness requirement and the brightness critical value, and the bead transmission distance is the distance between the lamp bead and the lens.

[0016] Furthermore, the analysis unit is also used to determine the reason why the flight status of the aircraft does not meet the standards based on the landing point angle, and send corresponding notifications to the aviation interaction unit based on the determined reasons, including flight direction deviation notifications, light refraction notifications and landing point mismatch notifications.

[0017] Furthermore, the analysis unit is also used to send a light refraction notification when it is determined that the navigation light information is refracted, and to increase the bead penetration distance based on the angle difference, and the increase in the bead penetration distance is proportional to the angle difference; wherein the angle difference is the angle difference between the landing point angle and the preset landing point angle.

[0018] Furthermore, the analysis unit is also used to send a landing point mismatch notification when the aircraft landing point does not match, and to determine the reason why the flight status of the aircraft does not meet the standards based on the landing point vertical coordinate difference, and to correct the flashing frequency of the illumination unit based on the landing point vertical coordinate difference according to the determined reason, or to correct the illumination elevation angle of the illumination unit based on the flight altitude; wherein the landing point vertical coordinate difference is the difference between the vertical coordinate of the two-dimensional coordinate of the navigation aid landing point and the vertical coordinate of the predicted aircraft landing point two-dimensional coordinate.

[0019] Furthermore, the analysis unit is also used to increase the flashing frequency of the illumination unit based on the difference in the vertical coordinate of the landing point when it is determined that the aircraft landing distance is less than the preset landing distance, and the increase in the flashing frequency is proportional to the difference in the vertical coordinate of the landing point; wherein the landing distance is the predicted distance between the aircraft landing point and the terminal, and the preset landing distance is the distance between the navigation aid landing point and the terminal.

[0020] Furthermore, the analysis unit is also used to reduce the illumination elevation angle of the illumination unit based on the flight altitude difference when it is determined that the aircraft landing distance is greater than the preset landing distance, and the reduction degree of the illumination elevation angle is proportional to the flight altitude difference; wherein the flight altitude difference is the difference between the real-time flight altitude and the flight altitude corresponding to the two-dimensional coordinates of the navigation aid landing point.

[0021] Compared with the prior art, the beneficial effect of the present invention lies in that, by setting an aviation interaction unit and an analysis unit, the present invention determines the current position of the aircraft through the flight information of the aircraft output by the aviation interaction unit, and obtains the predicted two-dimensional coordinates of the aircraft landing point. At the same time, it determines whether the flight status of the aircraft meets the standard according to the absolute distance between the predicted two-dimensional coordinates of the aircraft landing point and the two-dimensional coordinates of the navigation aid landing point. The flight status of the aircraft can be determined quickly and accurately, so as to determine whether to send a corresponding notification to the aircraft. At the same time, when it is determined that the flight status of the aircraft does not meet the standard, a corresponding instruction is generated based on the determined reason, and the irradiation parameters of the irradiation unit are determined through the instruction, and the instruction is sent to the aircraft. After receiving the notification and the irradiation parameters, the aircraft can adjust the flight information so that the aircraft can land at the target point, thereby ensuring that the aircraft can land smoothly at the designated location, and effectively improving the navigation efficiency of the system of the present invention for aircraft landing.

[0022] Furthermore, the analysis unit provided in the present invention is also used to determine whether the aircraft recognizes the navigation light information output by the illumination unit based on the interaction duration, so as to more accurately determine the flight status of the aircraft and avoid misjudgment. While improving the accuracy of aircraft flight status determination, it further improves the navigation efficiency of the system of the present invention for aircraft landing.

[0023] Furthermore, the analysis unit provided in the present invention is also used to specifically adjust the illumination brightness of the illumination unit based on the difference in interaction duration, which can avoid the situation where the aviation interaction unit is unable to recognize the navigation light information emitted by the navigation light, thereby effectively ensuring the stability of data interaction between the illumination unit and the aviation interaction unit, while further improving the accuracy of aircraft flight status judgment, and further improving the navigation efficiency of the system of the present invention for aircraft landing.

[0024] Furthermore, the analysis unit provided in the present invention is also used to adjust the bead transmission distance to correct the illumination brightness based on the brightness difference, which can effectively avoid the scattering of light resulting in the light output by the illumination unit failing to meet the brightness requirements, thereby causing the aviation interaction unit to be unable to recognize the navigation lighting information. While further improving the accuracy of aircraft flight status judgment, it also further improves the navigation efficiency of the system of the present invention for aircraft landing.

[0025] Furthermore, the analysis unit provided in the present invention is also used to send a corresponding notification to the aviation interaction unit based on the reason why the flight status of the aircraft does not meet the standards, so that the aircraft can know the subsequent operation direction, and adjust the flight information through the corresponding notification, so as to quickly and accurately adjust the landing site of the aircraft to the corresponding position, thereby further improving the accuracy of the aircraft's flight status judgment and further improving the navigation efficiency of the system of the present invention for aircraft landing.

[0026] Furthermore, the analysis unit provided in the present invention is also used to increase the bead penetration distance based on the angle difference when sending the light refraction notification, which can avoid the misjudgment of the aircraft due to light deflection. While further improving the accuracy of aircraft flight status judgment, it further improves the navigation efficiency of the system of the present invention for aircraft landing.

[0027] Furthermore, the analysis unit provided in the present invention is also used to determine the reason why the flight status of the aircraft does not meet the standards based on the difference in the vertical coordinates of the landing points when determining to send a landing point mismatch notification, so as to more accurately determine the reason why the flight status of the aircraft does not meet the standards, thereby further improving the accuracy of the aircraft flight status determination and further improving the navigation efficiency of the system of the present invention for aircraft landing.

[0028] Furthermore, the analysis unit provided in the present invention is also used to increase the flashing frequency of the illumination unit based on the difference in the vertical coordinate of the landing point, thereby effectively avoiding the situation where the predicted aircraft landing distance is less than the preset landing distance. While further improving the accuracy of the aircraft's flight status judgment, it further improves the navigation efficiency of the system of the present invention for aircraft landing.

[0029] Furthermore, the analysis unit provided in the present invention is also used to reduce the irradiation elevation angle of the irradiation unit based on the flight altitude difference, thereby effectively avoiding the situation where the predicted aircraft landing distance is greater than the preset landing distance. While further improving the accuracy of aircraft flight status judgment, it further improves the navigation efficiency of the system of the present invention for aircraft landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 This is a structural block diagram of the airport navigation lighting control system based on flight information of the present invention;

[0031] Figure 2 The present invention is a flowchart of the airport navigation lighting control system based on flight information;

[0032] Figure 3 A flow chart of the present invention for determining whether the flight status of an aircraft meets the standard and determining whether the aircraft recognizes the navigation light information output by the illumination unit;

[0033] Figure 4 The present invention is a flow chart for analyzing the reasons why the flight status of an aircraft does not meet the standards. DETAILED DESCRIPTION

[0034] In order to make the objects and advantages of the present invention more clearly understood, the present invention is further described below in conjunction with embodiments; it should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0035] The preferred embodiments of the present invention are described below with reference to the accompanying drawings. It should be understood by those skilled in the art that these embodiments are only used to explain the technical principles of the present invention and are not intended to limit the protection scope of the present invention.

[0036] It should be noted that, in the description of the present invention, terms such as "up", "down", "left", "right", "inside" and "outside" indicating directions or positional relationships are based on the directions or positional relationships shown in the drawings. This is merely for the convenience of description and does not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it cannot be understood as a limitation on the present invention.

[0037] In addition, it should be noted that in the description of the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0038] See also Figure 1 As shown, it is a structural block diagram of the airport navigation lighting control system based on flight information of the present invention.

[0039] The system of the embodiment of the present invention includes an irradiation unit, an aviation interaction unit, an information receiving unit, an analysis unit, a control unit and a database, wherein:

[0040] The irradiation unit includes a plurality of irradiation lamp groups arranged on the ground in a corresponding order, each irradiation lamp group is used to output navigation light using corresponding irradiation parameters to generate navigation light information, wherein the irradiation parameters include irradiation brightness, irradiation concentration, flashing frequency and irradiation elevation angle, and the irradiation brightness and irradiation concentration are adjusted by the distance between the lamp beads and the lens in the corresponding irradiation lamp group;

[0041] The aviation interaction unit is arranged on the aircraft and connected to the illumination unit, and is used to receive the navigation light information generated by the illumination unit, and to generate and output real-time flight information, wherein the flight information includes flight speed, flight altitude and flight pitch angle;

[0042] The information receiving unit is arranged on the ground and connected to the aviation interaction unit, and is used to receive the real-time flight information generated and output by the aviation interaction unit, so as to locate the real-time three-dimensional coordinate position of the aircraft in the air according to the flight information;

[0043] The analysis unit is arranged on the ground and connected to the information receiving unit, and is used to determine whether the flight status of the aircraft meets the standard based on the two-dimensional coordinates of the predicted aircraft landing point determined according to the flight information, and to determine the reason for not meeting the standard based on the flight information; the analysis unit is also used to generate corresponding processing instructions according to the determined reason for not meeting the standard;

[0044] The control unit is connected to the analysis unit, and is used to determine the irradiation parameters of the irradiation unit based on the processing instructions output by the analysis unit, and to send a corresponding notification to the aviation interaction unit;

[0045] The database is connected to the analysis unit and is used to store prediction data for determining the two-dimensional coordinates of the predicted aircraft landing point based on the flight information.

[0046] See also Figure 2 As shown, it is a workflow diagram of the airport navigation lighting control system based on flight information of the present invention.

[0047] When the airport navigation lighting control system based on flight information described in the embodiment of the present invention is in operation, the irradiation unit sends the navigation lighting information to the aviation interaction system, the aviation interaction system receives the navigation lighting information, generates and outputs real-time flight information of the real-time aircraft, and transmits the received navigation lighting information and real-time flight information to the information receiving unit. The information receiving unit locates the real-time three-dimensional coordinate position of the aircraft in the air according to the real-time flight information received from the aviation interaction unit, and transmits the navigation lighting information and the real-time three-dimensional coordinate position of the aircraft in the air to the analysis unit. The analysis unit determines the predicted two-dimensional coordinates of the aircraft landing point according to the real-time three-dimensional coordinate position of the aircraft in the air combined with the predicted data in the database, determines the navigation two-dimensional coordinates according to the navigation lighting information, and determines whether the flight status of the aircraft meets the standard according to the determined predicted two-dimensional coordinates of the aircraft landing point and the navigation two-dimensional coordinates. The analysis unit also determines the reason for not meeting the standard based on the flight information, and generates a corresponding processing instruction and transmits it to the control unit. The control unit determines the irradiation parameters of the irradiation unit based on the received processing instruction, and sends a corresponding notification to the aviation interaction unit.

[0048] See also Figure 3 As shown, it is a flow chart of the present invention for determining whether the flight status of an aircraft meets the standard and determining whether the aircraft recognizes the navigation light information output by the illumination unit.

[0049] The analysis unit of the embodiment of the present invention is further provided with a two-dimensional coordinate of a navigation point that matches the corresponding navigation light information, and the analysis unit is used to determine whether the flight state of the aircraft meets the standard based on the absolute distance between the acquired two-dimensional coordinate of the predicted aircraft landing point and the two-dimensional coordinate of the navigation point:

[0050] When the absolute distance is less than or equal to the first preset absolute distance D1, it is determined that the flight status of the aircraft meets the standard, wherein the first preset absolute distance D1 in this embodiment is 8m;

[0051] When the absolute distance is greater than the first preset absolute distance D1 and less than or equal to the second preset absolute distance D2, it is determined that the flight status of the aircraft does not meet the standard, and it is determined whether the aircraft recognizes the navigation light information output by the illumination unit based on the time node of the acquired real-time flight information, wherein the second preset absolute distance D2 in this embodiment is 12m;

[0052] When the absolute distance is greater than the second preset absolute distance D2, it is determined that the flight status of the aircraft does not meet the standard, and the reason why the flight status of the aircraft does not meet the standard is determined based on the landing point connection line between the two-dimensional coordinates of the navigation aid landing point and the two-dimensional coordinates of the predicted aircraft landing point.

[0053] Please continue reading Figure 3 As shown, the analysis unit in the embodiment of the present invention is further used to determine whether the aircraft recognizes the navigation light information output by the illuminating unit based on the interaction time, wherein the interaction time is the cumulative time taken for the illuminating unit to output the navigation light information to the information receiving unit to receive the real-time flight information:

[0054] When the interaction time is greater than or equal to a preset interaction time T, it is determined that the aircraft has not recognized the navigation light information output by the illumination unit, and the illumination brightness of the illumination unit is determined based on the obtained interaction time difference, wherein the preset interaction time T in this embodiment is 1.6s;

[0055] When the interaction time is less than the preset interaction time T, it is determined that the aircraft recognizes the navigation light information output by the illumination unit and the flight status of the aircraft does not meet the standard. The reason why the flight status of the aircraft does not meet the standard is determined based on the landing point connection line between the two-dimensional coordinates of the navigation landing point and the two-dimensional coordinates of the predicted aircraft landing point.

[0056] Please continue reading Figure 3 As shown, the analysis unit in the embodiment of the present invention is further used to increase the illumination brightness of the illumination unit based on the interaction duration difference, wherein the interaction duration difference is the difference between the interaction duration and the preset interaction duration:

[0057] When the interaction time difference is greater than the second preset interaction time difference △T2, the illumination brightness of the illumination unit is increased to 1.9 times of the initial illumination brightness, wherein the second preset interaction time difference △T2 in this embodiment is 0.6s;

[0058] When the interaction time difference is less than or equal to the second preset interaction time difference △T2 and greater than the first preset interaction time difference △T1, the illumination brightness of the illumination unit is increased to 1.38 times of the initial illumination brightness, wherein the first preset interaction time difference △T1 in this embodiment is 0.35s;

[0059] When the total process duration difference is less than or equal to the interaction duration difference ΔT1, the illumination brightness of the illumination unit is increased to 1.12 times of the initial illumination brightness.

[0060] Please continue reading Figure 3 As shown, the analysis unit of the embodiment of the present invention is further used to adjust the bead penetration distance to correct the illumination brightness based on the brightness difference when the illumination brightness of the illumination unit increases to the brightness critical value, wherein the brightness difference is the difference between the brightness requirement and the brightness critical value, and the bead penetration distance is the distance between the lamp bead and the lens:

[0061] When the illumination brightness of the illumination unit increases to a brightness critical value Bc, the bead transmission distance is adjusted based on brightness requirements to correct the illumination brightness, wherein the brightness critical value Bc in this embodiment is 3.6%.

[0062] When the brightness difference is greater than the second preset brightness difference △B2, the bead penetration distance is increased to 1.23 times of the original bead penetration distance to correct the illumination brightness, wherein the second preset brightness difference △B2 of this embodiment is 1.2%;

[0063] When the brightness difference is less than or equal to the second preset brightness difference △B2 and greater than the first preset brightness difference △B1, the bead penetration distance is increased to 1.12 times of the original bead penetration distance to correct the illumination brightness, wherein the first preset brightness difference △B1 in this embodiment is 0.8%;

[0064] When the brightness difference is less than or equal to the first preset brightness difference, the bead penetration distance is increased to 1.05 times of the original bead penetration distance to correct the illumination brightness.

[0065] See also Figure 4 As shown, it is a flow chart of the present invention for analyzing the reasons why the flight status of the aircraft does not meet the standards.

[0066] The analysis unit of the embodiment of the present invention is further used to determine the reason why the flight status of the aircraft does not meet the standard based on the landing point angle, and send a corresponding notification to the aviation interaction unit based on the determined reason, including a flight direction deviation notification, a light refraction notification, and a landing point mismatch notification, wherein the landing point angle is the angle between the landing point connection line of the two-dimensional coordinates of the navigation aid landing point and the two-dimensional coordinates of the predicted aircraft landing point and the vertical navigation light setting direction:

[0067] When the landing angle is greater than the second preset landing angle A2, it is determined that the flight state of the aircraft does not meet the standard, the flight of the aircraft deviates, and a flight direction deviation notification is issued, wherein the second preset landing angle A2 in this embodiment is 2.8°;

[0068] When the landing angle is less than or equal to the second preset landing angle A2 and greater than the first preset landing angle A1, it is determined that the flight state of the aircraft does not meet the standard, the navigation light information output by the irradiation unit is deflected, and a light refraction notification is sent, wherein the first preset landing angle A1 in this embodiment is 1.6°;

[0069] When the landing point angle is less than or equal to the first preset landing point angle A1, it is determined that the flight status of the aircraft does not meet the standard, the predicted aircraft landing point ordinate does not meet the standard, and a landing point mismatch notification is sent.

[0070] Please continue reading Figure 4 As shown, the analysis unit in the embodiment of the present invention is further used to send a light refraction notification when it is determined that the navigation light information is refracted, and to increase the bead penetration distance based on the angle difference, wherein the angle difference is the angle difference between the landing point angle and the first preset landing point angle:

[0071] When the angle difference is greater than the second preset angle difference △A2, the bead penetration distance is increased to 1.38 times of the initial bead penetration distance, wherein the second preset angle difference △A2 of this embodiment is 0.78°;

[0072] When the angle difference is less than or equal to the second preset angle difference △A2 and greater than the first preset angle difference △A1, the bead penetration distance is increased to 1.16 times of the initial bead penetration distance, wherein the second preset angle difference △A2 of this embodiment is 0.32°;

[0073] When the angle difference is less than or equal to the first preset angle difference ΔA1, the bead penetration distance is increased to 1.02 times of the initial bead penetration distance.

[0074] Please continue reading Figure 4 As shown, the analysis unit in the embodiment of the present invention is further used to send a landing point mismatch notification when the aircraft landing point does not match, and determine the reason why the flight status of the aircraft does not meet the standard based on the landing point ordinate difference, wherein the landing point ordinate difference is the difference between the ordinate of the two-dimensional coordinate of the navigation aid landing point and the ordinate of the two-dimensional coordinate of the predicted aircraft landing point:

[0075] When the difference in the vertical coordinate of the landing point is greater than zero, it is determined that the aircraft landing point distance is less than the preset landing point distance, and the flashing frequency of the irradiation unit is corrected based on the difference in the vertical coordinate of the landing point; wherein the landing point distance is the distance between the predicted aircraft landing point and the terminal, and the preset landing point distance is the distance between the navigation aid landing point and the terminal;

[0076] When the difference in the vertical coordinates of the landing points is less than zero, it is determined that the aircraft landing distance is greater than the preset landing distance, and the irradiation elevation angle of the irradiation unit is corrected based on the flight altitude.

[0077] Please continue reading Figure 4 As shown, the analysis unit of the embodiment of the present invention is also used to increase the flashing frequency of the irradiation unit based on the difference in the vertical coordinates of the landing points:

[0078] When the vertical coordinate difference of the landing point is greater than the second preset vertical coordinate difference of the landing point △V2, the flashing frequency of the irradiation unit is increased to 1.52 times of the initial flashing frequency, wherein the second preset vertical coordinate difference of the landing point △V2 in this embodiment is 13.2m;

[0079] When the vertical coordinate difference of the landing point is less than or equal to the second preset vertical coordinate difference of the landing point △V2 and greater than the first preset vertical coordinate difference of the landing point △V1, the flashing frequency of the irradiation unit is increased to 1.32 times of the initial flashing frequency, wherein the first preset vertical coordinate difference of the landing point in this embodiment is △V1=12.6m;

[0080] When the vertical coordinate difference of the landing point is less than or equal to the first preset vertical coordinate difference of the landing point, the flashing frequency of the irradiation unit is increased to 1.08 times of the initial flashing frequency.

[0081] Please continue reading Figure 4 As shown, the analysis unit in the embodiment of the present invention is further used to reduce the irradiation elevation angle of the irradiation unit based on the flight altitude difference, wherein the flight altitude difference is the difference between the real-time flight altitude and the flight altitude corresponding to the two-dimensional coordinates of the navigation aid landing point:

[0082] When the flight height difference is greater than the second preset flight height difference ΔF2, the irradiation elevation angle of the irradiation unit is reduced to 0.8 times of the initial irradiation elevation angle, wherein the second preset flight height ΔF2 in this embodiment is 0.68m;

[0083] When the flight height difference is less than or equal to the second preset flight height difference F2 and greater than the first preset flight height difference ΔF1, the irradiation elevation angle of the irradiation unit is reduced to 0.6 times of the initial irradiation elevation angle, wherein the first preset flight height ΔF1 in this embodiment is 0.55m;

[0084] When the flight height difference is less than or equal to the first preset flight height difference ΔF1, the irradiation elevation angle of the irradiation unit is reduced to 0.35 times of the initial irradiation elevation angle.

[0085] So far, the technical solutions of the present invention have been described in conjunction with the preferred embodiments shown in the accompanying drawings. However, it is easy for those skilled in the art to understand that the protection scope of the present invention is obviously not limited to these specific embodiments. Without departing from the principle of the present invention, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present invention.

[0086] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An airport navigation lighting control system based on flight information, characterized in that: include: An irradiation unit, comprising a plurality of irradiation lamp groups arranged on the ground in a corresponding order, each irradiation lamp group is used to output navigation light using corresponding irradiation parameters to generate navigation light information, wherein the irradiation parameters include irradiation brightness, irradiation concentration, flashing frequency and irradiation elevation angle, and the irradiation brightness and irradiation concentration are adjusted by the distance between the lamp beads and the lens in the corresponding irradiation lamp group; An aviation interaction unit, which is arranged on the aircraft and connected to the illumination unit, is used to obtain the navigation light information on the ground, and to generate and output real-time flight information, wherein the flight information includes flight speed, flight altitude and flight pitch angle; An information receiving unit, which is arranged on the ground and connected to the aviation interaction unit, is used to receive the real-time flight information generated and output by the aviation interaction unit, so as to locate the real-time three-dimensional coordinate position of the aircraft in the air according to the flight information; an analysis unit, which is arranged on the ground and connected to the information receiving unit, and is used to determine whether the flight status of the aircraft meets the standard based on the two-dimensional coordinates of the predicted aircraft landing point determined according to the flight information, and to determine the reason for not meeting the standard based on the flight information; the analysis unit is also used to generate corresponding processing instructions according to the determined reason for not meeting the standard; a control unit connected to the analysis unit, configured to determine the irradiation parameters of the irradiation unit based on the processing instructions output by the analysis unit, and to send a corresponding notification to the aviation interaction unit; A database, connected to the analysis unit, for storing prediction data of two-dimensional coordinates of a predicted aircraft landing point determined according to the flight information; The analysis unit is also provided with a two-dimensional coordinate of a navigation point that matches the corresponding navigation light information. The analysis unit is used to determine whether the flight state of the aircraft meets the standard based on the absolute distance between the acquired two-dimensional coordinate of the predicted aircraft landing point and the two-dimensional coordinate of the navigation point, and, when it is determined that the flight state of the aircraft does not meet the standard, determine whether the aircraft recognizes the navigation light information output by the illumination unit based on the time node of acquiring the real-time flight information, or determine the reason why the flight state of the aircraft does not meet the standard based on the landing point connection line between the two-dimensional coordinate of the navigation point and the two-dimensional coordinate of the predicted aircraft landing point; The analysis unit is also used to determine whether the aircraft recognizes the navigation light information output by the illumination unit based on the interaction duration, and to determine the illumination brightness of the illumination unit based on the interaction duration difference according to the determination result, or to determine the reason why the aircraft's flight status does not meet the standards based on the landing point connection line between the two-dimensional coordinates of the navigation light landing point and the two-dimensional coordinates of the predicted aircraft landing point; wherein the interaction duration is the cumulative duration used from the illumination unit outputting the navigation light information to the information receiving unit receiving the real-time flight information.

2. The airport navigation lighting control system based on flight information according to claim 1, characterized in that: The analysis unit is also used to increase the illumination brightness of the illumination unit based on the interaction duration difference, and the increase in the illumination brightness of the illumination unit is proportional to the interaction duration difference; wherein the interaction duration difference is the difference between the interaction duration and a preset interaction duration.

3. The airport navigation lighting control system based on flight information according to claim 2, characterized in that: The analysis unit is also used to adjust the bead-to-bead distance to correct the illumination brightness based on the brightness difference when the illumination brightness of the illumination unit increases to the brightness critical value, and the correction amplitude of the illumination brightness is proportional to the bead-to-bead distance; wherein the brightness difference is the difference between the brightness requirement and the brightness critical value, and the bead-to-bead distance is the distance between the lamp bead and the lens.

4. The airport navigation lighting control system based on flight information according to claim 3 is characterized in that: The analysis unit is also used to determine the reason why the flight status of the aircraft does not meet the standards based on the landing point angle, and send corresponding notifications to the aviation interaction unit based on the determined reasons, including flight direction deviation notifications, light refraction notifications and landing point mismatch notifications.

5. The airport navigation lighting control system based on flight information according to claim 4, characterized in that: The analysis unit is also used to send a light refraction notification when it is determined that the navigation light information is refracted, and to increase the bead penetration distance based on the angle difference, and the increase in the bead penetration distance is proportional to the angle difference; wherein the angle difference is the angle difference between the landing point angle and the preset landing point angle.

6. The airport navigation lighting control system based on flight information according to claim 5, characterized in that: The analysis unit is also used to send a landing point mismatch notification when the aircraft landing point does not match, and to determine the reason why the flight status of the aircraft does not meet the standards based on the landing point longitudinal coordinate difference, and to correct the flashing frequency of the illumination unit based on the landing point longitudinal coordinate difference according to the determined reason, or to correct the illumination elevation angle of the illumination unit based on the flight altitude; wherein the landing point longitudinal coordinate difference is the difference between the longitudinal coordinate of the two-dimensional coordinate of the navigation aid landing point and the longitudinal coordinate of the predicted aircraft landing point two-dimensional coordinate.

7. The airport navigation lighting control system based on flight information according to claim 6, characterized in that: The analysis unit is also used to increase the flashing frequency of the illumination unit based on the difference in the vertical coordinates of the landing point when it is determined that the aircraft landing distance is less than the preset landing distance, and the increase in the flashing frequency is proportional to the difference in the vertical coordinates of the landing point; wherein the landing distance is the predicted distance between the aircraft landing point and the terminal, and the preset landing distance is the distance between the navigation aid landing point and the terminal.

8. The airport navigation lighting control system based on flight information according to claim 7, characterized in that: The analysis unit is also used to reduce the illumination elevation angle of the illumination unit based on the flight altitude difference when it is determined that the aircraft landing distance is greater than the preset landing distance, and the reduction degree of the illumination elevation angle is proportional to the flight altitude difference; wherein the flight altitude difference is the difference between the real-time flight altitude and the flight altitude corresponding to the two-dimensional coordinates of the navigation aid landing point.

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