Retractable aircraft landing lamp with retracting and releasing synchronization function and retracting and releasing method
By introducing a communication synchronization mechanism of the master and slave lamps in the landing light of the retractable aircraft, the problems of poor uniformity of the dual lamp release angle and poor retractable and release time in the existing technology are solved, and the synchronous retractable and release of the dual lamps are realized, which improves the ability to complete combat tasks.
Patent Information
- Application Number
- CN202311718220.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-12-14
- Publication Date
- 2025-06-17
AI Technical Summary
The existing landing lights of the existing aircraft are poor in the angle consistency after the double lights are released, and the time difference in the retracting and retracting is large, which cannot be synchronized, which affects the completion of combat missions.
Design a landing light for retracting and retracting aircraft with retracting and retracting synchronization function, and ensure that the retracting and retracting positions of the dual lights are consistent through communication synchronization between the master and slave lights. The main lamp sends the retracting and retracting position information to the slave lamp, and the slave lamp adjusts the retracting and retracting position of its lamp head according to the received information to achieve synchronous retracting and retracting.
The angle consistency and time synchronization of dual-light collection and release are achieved, improving the efficiency of aircraft landing lights and the ability to complete combat tasks.
Smart Images
Figure CN120160109A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to a retractable aircraft landing light, and in particular, to a retractable aircraft landing light with a retraction and extension synchronization function and a retraction and extension method. Background Art
[0002] Retractable aircraft landing lights belong to the aircraft lighting system. Generally, an aircraft is equipped with 2 retractable aircraft landing lights. The retractable landing lights not only need to provide the environmental lighting required for the aircraft to take off, land and taxi at night, but also need to be controlled by the pilot to realize the function of releasing and retracting the lamp head with an adjustable irradiation angle.
[0003] At present, all existing retractable landing lights are independently controlled by single lamps. During actual use, there will be a problem that the angles of the two lamps are not consistent after they are released, resulting in the front and back dispersion of the ground light spots. Moreover, the time difference between the two lamps reaching the fully retracted or extended position is relatively large, and synchronization cannot be achieved, which will affect the completion of combat missions. Summary of the Invention
[0004] The purpose of the present invention is to solve the problem of poor angle consistency of the two lamps of the aircraft landing light in the prior art, and to provide a new type of retractable aircraft landing light and retraction and extension method with a communication synchronization function for the retraction and extension of the two lamps.
[0005] In order to achieve the above purpose, a technical solution provided by the present invention is as follows:
[0006] Compared with the prior art, the beneficial effects of the present invention are at least as follows: 1. Simple structure, small volume and light weight; 2. The two retractable aircraft landing lights supporting a single aircraft are divided into a main lamp and a slave lamp. The retractable aircraft landing light serving as the slave lamp adjusts the retraction and extension position of its landing light head according to the retraction and extension position information sent by the retractable aircraft landing light serving as the main lamp, and the retraction and extension consistency is good, and the main lamp and the slave lamp can be interchanged. Brief Description of the Drawings
[0007] Figure 1 It is a schematic external view of the present invention.
[0008] Figure 2 It is a schematic structural view of the actuating device in the present invention.
[0009] Figure 3 It is a functional structure diagram of the landing light control software of the present invention.
[0010] Figure 4 It is a working flow chart of the landing light control software of the present invention. Detailed Description of the Invention
[0011] The present invention will be further described in detail below in conjunction with the accompanying drawings through specific embodiments. It should be noted here that the description of these embodiments is used to help understand the present invention, but does not limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.
[0012] Please refer to Figure 1 , which shows a retractable aircraft landing light with a retraction and extension synchronization function. The retractable aircraft landing light is used to provide ambient lighting required for the aircraft to take off, land, and / or taxi at night.
[0013] The retractable aircraft landing light includes: a landing light housing 4, a landing light head 7, an actuating device 5 for retracting and extending the landing light head, etc.
[0014] The interior of the landing light housing houses a lamp head drive printed circuit board 3 and an actuating control printed circuit board 2. An electrical connector 6 is fixed to the peripheral wall of the landing light housing 4. The electrical connector 6 has a power interface and a communication interface. The communication interface can be selected as an RS422 bus interface. The electrical connector 6 is electrically connected to the lamp head drive printed circuit board 3 and the actuating control printed circuit board 2 respectively. The lamp head drive printed circuit board 3 receives the aircraft power supply and the lamp head drive signal from the outside through the electrical connector 6. The actuating control printed circuit board 2 receives the aircraft power supply and the actuating control signal from the outside through the electrical connector 6. When the retractable aircraft landing light is used as the main light, the actuating control printed circuit board 2 also sends its retraction and extension position information to the outside through the electrical connector 6. When the retractable aircraft landing light is used as the slave light, the actuating control printed circuit board 2 also receives the retraction and extension position information (the retraction and extension position information of the main light) from the outside through the electrical connector 6.
[0015] In one embodiment, the lamp head drive printed circuit board 3 is parallel to the actuating control printed circuit board 2, with the lamp head drive printed circuit board 3 below and the actuating control printed circuit board 2 above.
[0016] The landing light head 7 is accommodated inside the landing light housing 4 in the retracted state. The landing light head 7 leaves the landing light housing 4 in the extended state. The landing light head 7 has a lamp head housing and a lamp head light source printed circuit board inside the lamp head housing. The lamp head light source printed circuit board is electrically connected to the lamp head drive printed circuit board 3. The lamp head light source printed circuit board is controlled by the lamp head drive printed circuit board 3. The LED light source of the lamp head light source printed circuit board can be configured with a TIR light distribution lens. The aircraft power supply and the lamp head drive signal from the outside can be supplied to the lamp head drive printed circuit board 3 through the electrical connector 6. The lamp head drive printed circuit board 3 controls the operation of the lamp head light source printed circuit board according to the aircraft power supply and the lamp head drive signal.
[0017] In one embodiment, the LED light source on the lamp holder light source printed circuit board has two operating modes: friendly and concealed. The switching of the operating mode of the LED light source on the lamp holder light source printed circuit board is controlled by the lamp holder drive signal.
[0018] The actuating device 5 includes a DC motor 57, a speed reducer 55, a sector gear 54, an angular displacement sensor 52, etc. The DC motor 57 and the angular displacement sensor 52 are both electrically connected to the actuating control printed circuit board 2. The DC motor 57 is controlled by the actuating control printed circuit board 2. The motor shaft of the DC motor 57 is connected to the input shaft of the speed reducer 55. The output shaft of the speed reducer 55 is connected to the sector gear 54. The circumferential end face of the sector gear 54 is fixedly connected to the lamp holder housing of the landing lamp head 7. Thus, the DC motor 57 drives the sector gear 54 to retract and extend the landing lamp head 7 through the speed reducer 55. The input shaft of the angular displacement sensor 52 can be coaxially and fixedly connected to the output shaft of the speed reducer 55 or the sector gear 54. The angular displacement sensor 52 is used to detect the angular displacement state of the output shaft of the speed reducer 55 or the sector gear 54 to determine the retraction / extension position information of the landing lamp head. The purpose of setting the speed reducer 55 is to convert the high-speed and low-torque power output by the DC motor into the low-speed and high-torque power required for retracting and extending the landing lamp head.
[0019] In one embodiment, a gear docking flange is formed on the circumferential end face of the sector gear 54, and a housing docking flange is formed on the lamp holder housing of the landing lamp head 7. The gear docking flange and the housing docking flange are fixedly connected by screws.
[0020] The chip microprocessor of the actuating control printed circuit board 2 is programmed with a control program for retracting and extending the landing lamp head. The external aircraft power supply and actuating control signal are fed to the actuating control printed circuit board 2 through the electrical connector 6. After being processed by the chip microprocessor, it controls the DC motor 57 to drive the retraction and extension of the landing lamp head 7. If the chip microprocessor receives the retraction / extension in-place signal from the angular displacement sensor 52, the DC motor 57 stops rotating. At any position during the retraction and extension process, if the aircraft terminal cuts off the actuating control signal, the DC motor 57 stops rotating and the brake works to lock the last-stage transmission shaft to prevent jitter, that is, the landing lamp head 7 can stay at any angle.
[0021] Currently, an aircraft is generally equipped with two of the retractable aircraft landing lights. One of the retractable aircraft landing lights serves as the main light, while the other retractable aircraft landing light serves as the slave light. The retractable aircraft landing light serving as the slave light receives the retraction and extension position information sent by the retractable aircraft landing light serving as the main light. The retractable aircraft landing light serving as the slave light adjusts the retraction and extension position of its landing light head according to the retraction and extension position information sent by the retractable aircraft landing light serving as the main light. The retractable aircraft landing light serving as the slave light performs speed adjustment based on the retraction and extension position information determined by its angular displacement sensor 52 to ensure that the angle error between the two retractable aircraft landing lights is not greater than 0.6° when they stay at any position during movement. At the same time, by controlling the form and position tolerance and the fit tolerance of the transmission parts in the actuating device 5, and by controlling the rotational speed of the DC motor 57, the requirement that the time difference between the two retractable aircraft landing lights reaching the limit retraction position is not greater than 0.5 s is achieved.
[0022] The above only expresses the embodiments of the present invention, and the description is relatively specific and detailed. However, it should not be construed as a limitation on the scope of the invention patent. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several modifications and improvements can still be made, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention patent shall be subject to the appended claims.
Claims
1. A retractable aircraft landing light with retraction and extension synchronization function, characterized in that, Comprising: A landing light housing, a landing light lamp head, and an actuating device for retracting and extending the landing light lamp head. Inside the landing light housing, there is a lamp head drive printed circuit board for controlling the illumination of the landing light lamp head and an actuating control printed circuit board for controlling the retraction and extension of the actuating device. The landing light housing is fixed with an electrical connector. When the retractable aircraft landing light is used as the main light, the actuating control printed circuit board receives an external actuating control signal through the electrical connector and controls the actuating device to retract and extend the landing light lamp head according to the actuating control signal. Moreover, the actuating control printed circuit board also sends the main light retraction and extension position information, which is the retraction and extension position information of the landing light lamp head, to the outside through the electrical connector. When the retractable aircraft landing light is used as a slave light, the actuating control printed circuit board receives the main light retraction and extension position information from the outside through the electrical connector and controls the actuating device to retract and extend the landing light lamp head according to the main light retraction and extension position information to achieve synchronous retraction and extension of the main and slave lights.
2. The retractable aircraft landing light with retraction and extension synchronization function according to claim 1, characterized in that, The actuating device has a DC motor, a reducer, an angular displacement sensor, a sector gear, and a mechanism housing. The DC motor is controlled by the actuating control printed circuit board. The motor shaft of the DC motor is connected to the input shaft of the reducer. The output shaft of the reducer is connected to the sector gear. The circumferential end face of the sector gear is fixedly connected to the landing light lamp head. The angular displacement sensor is used to detect the angular displacement state of the output shaft of the reducer or the sector gear to determine the retraction and extension position information of the landing light lamp head.
3. The retractable aircraft landing light with retraction and extension synchronization function according to claim 2, characterized in that, A gear docking flange is formed on the circumferential end face of the sector gear, and a housing docking flange is formed on the landing light lamp head. The gear docking flange and the housing docking flange are fixedly connected by screws.
4. The retractable aircraft landing light with retraction and extension synchronization function according to claim 1, characterized in that, The electrical connector has a power interface and a communication interface. Preferably, the communication interface can be selected as an RS422 bus interface.
5. The retractable aircraft landing light with retraction and extension synchronization function according to claim 1, characterized in that, When in the retracted state, the landing light lamp head is accommodated inside the landing light housing, and when in the extended state, it leaves the landing light housing. The landing light lamp head has a lamp head housing and a lamp head light source printed circuit board inside the lamp head housing. The lamp head light source printed circuit board is controlled by the lamp head drive printed circuit board.
6. The retractable aircraft landing light with retraction and extension synchronization function according to claim 5, characterized in that, The LED light source of the lamp head light source printed circuit board is equipped with a TIR light distribution lens.
7. The retractable aircraft landing light with retraction and extension synchronization function according to claim 5, characterized in that, The LED light source of the lamp head light source printed circuit board has two working modes: friendly and concealed.
8. A method for retracting and extending the retractable aircraft landing light with retraction and extension synchronization function according to any one of claims 1 to 7, characterized in that, Including: Determining whether the retractable aircraft landing light is a slave light; If so, the actuating control printed circuit board receives the main light retraction and extension position information from the outside through the electrical connector and controls the actuating device to retract and extend the landing light lamp head according to the main light retraction and extension position information to achieve synchronous retraction and extension of the main and slave lights; If not, the actuating control printed circuit board receives an external actuating control signal through the electrical connector and controls the actuating device to retract and extend the landing light lamp head according to the actuating control signal. Moreover, the actuating control printed circuit board also sends the main light retraction and extension position information, which is the retraction and extension position information of the landing light lamp head, to the outside through the electrical connector.