Aircraft LED signal light lighting detection circuit and method

Abstract

The present invention discloses an aircraft LED signal light illumination detection circuit and method, comprising an aircraft LED signal light having a first side LED and a second side LED; a first PWM controller for controlling the on / off frequency and timing of the first side LED; and a second PWM controller for controlling the on / off frequency and timing of the second side LED. The invention has the beneficial effect of greatly reducing the probability of missed fault detection to ensure subsequent flight safety.

Description

Technical Field

[0001] The present invention relates to an aircraft LED signal light lighting detection circuit and method, which are mainly used to improve the efficiency of signal light lighting fault judgment, and at the same time improve the troubleshooting efficiency of other functional faults related to lighting faults, taking into account the requirements of aircraft electromagnetic compatibility, and can be applied to various aircraft models. Background Art

[0002] The signal lights in the cockpit of an aircraft provide the flight crew with corresponding flight information and operation prompts. In view of the characteristics of low power consumption, the signal lights of the current mainstream models are LEDs. In order to ensure that the signal lights can work normally during the flight and avoid danger caused by misjudgment by the crew, the crew will turn on all the signal lights before the flight to check whether their lighting functions are intact. However, due to the functional requirements of various systems, the number of signal lights in the cockpits of current mainstream models is nearly 100, especially the top control panel area where most of the signal lights are concentrated. According to the current national military standard (GJB), US military standard (MIL) documents, and SAE standards, the average brightness of the signal lights should be higher than 1000cd / m2 2 When the human eye is exposed to a large amount of high-brightness stimulation in a short period of time, the physiological system will activate protective measures, which will reduce the human eye's ability to judge the on and off of traffic lights. Therefore, when one of the dozens of traffic lights is not on due to a fault, it is difficult for the human eye to identify it, resulting in a significantly increased probability of missing the fault. Summary of the invention

[0003] The purpose of the present invention is to solve the problem in the prior art that it is difficult for human eyes to identify signal light failures, and to provide a novel aircraft LED signal light illumination detection circuit and method.

[0004] In order to achieve this purpose, the technical solution of the present invention is as follows: an aircraft LED signal light lighting detection circuit, comprising:

[0005] An aircraft LED signal light having a first side LED and a second side LED;

[0006] A first PWM controller, which is used to control the on / off frequency and timing of the LED on the first side; and

[0007] The second PWM controller is used to control the on / off frequency and timing of the LED on the second side.

[0008] As a preferred solution of an aircraft LED signal light lighting detection circuit, the first PWM controller controls the first side LED through a first drive circuit, and the second PWM controller controls the second side LED through the second drive circuit.

[0009] As a preferred solution for an aircraft LED signal light illumination detection circuit, the physical distance between the drive circuit and the LED is less than a certain distance to meet the requirements of electromagnetic compatibility of the aircraft.

[0010] The present invention also provides an aircraft LED signal light illumination detection method, comprising the following steps:

[0011] providing a lighting detection circuit; and,

[0012] The first PWM controller controls the on / off frequency and timing of the first side LED, and the second PWM controller controls the on / off frequency and timing of the second side LED. In a single control cycle, the control signal of the first PWM controller is different or substantially different from the control signal of the second PWM controller to alternately turn on and off the first side LED and the second side LED.

[0013] As a preferred solution of an aircraft LED signal light illumination detection method, if the timing of the first PWM controller is completely consistent with the timing of the second PWM controller, the control signal of the first PWM controller is different from the control signal of the second PWM controller.

[0014] As a preferred solution of an aircraft LED signal light illumination detection method, if the timing of the second PWM controller is based on the timing of the first PWM controller, considering the time taken for the timing signal of the first PWM controller to reach the second PWM controller, the control signal of the first PWM controller is substantially different from the control signal of the second PWM controller. Further, in a single control cycle, the control signal of the first PWM controller is the same as the control signal of the second PWM controller only for a period of time to compensate for the timing control error; preferably, the period of time is less than 1 / 8 of the control cycle. Further, every several control cycles, the first PWM controller will output a timing signal to the second PWM controller to prevent timing confusion.

[0015] As a preferred solution of an aircraft LED signal light lighting detection method, the first PWM controller outputs a light-on signal in the first half cycle and a light-off signal in the second half cycle, while the second PWM controller outputs a light-off signal in the first half cycle and a light-on signal in the second half cycle.

[0016] As a preferred solution of an aircraft LED signal light lighting detection method, the frequencies of the control signal of the first PWM controller and the control signal of the second PWM controller are both lower than the flicker frequency limit that can be recognized by the human eye, so that the human eye can recognize the alternation of the bright and dark areas on both sides of the fault signal light; preferably, the frequency is lower than 10 Hz.

[0017] Compared with the prior art, the beneficial effect of the present invention is at least that: under the condition of meeting the electromagnetic compatibility requirements, the aircraft crew can clearly check the signal lights with faulty lighting functions, greatly reducing the probability of missed fault detection to ensure subsequent flight safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a structural schematic diagram of the present invention.

[0019] Figure 2 It is a schematic diagram of the principle of the present invention. DETAILED DESCRIPTION

[0020] The present invention is further described in detail below by means of specific embodiments connected with the accompanying drawings. It should be noted that the description of these embodiments is used to help understand the present invention, but does not constitute a limitation of 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.

[0021] See also Figure 1 and 2 In one embodiment, a circuit for controlling the lighting function of an aircraft LED signal light comprises:

[0022] Two PWM controllers 1 and 2;

[0023] An LED signal light 3 separating four lighting zones;

[0024] Two drive circuits 4 and 5;

[0025] The above embodiment is only the simplest embodiment, and it can be applied to any complex device as needed, and its effects and functions are as described in the content of the present invention.

[0026] The two PWM controllers are used to control the on and off timing and frequency of the LED light sources on both sides of the signal light, so that the signal light with normal function can be illuminated normally during the lighting function inspection, while the faulty signal light will flash. The signal light is divided into four lighting areas Q1, Q2, Q3, and Q4, which are suitable for single-layer or double-layer signal lights. The two PWM controllers output duty cycle PWM signals for the drive circuits on both sides, that is, PWM controller 1 controls drive circuit 1, and PWM controller 2 controls drive circuit 2. The drive circuits on both sides drive the LED light sources on both sides of the signal light, that is, drive circuit 1 controls the LED light sources of Q1 and Q3, and drive circuit 2 controls the LED light sources of Q2 and Q4. PWM controller 1 sends a high level in the first half cycle and a low level in the second half cycle, while PWM controller 2 does the opposite, sending a low level in the first half cycle and a high level in the second half cycle, so that Q1, Q3 and Q2, Q4 are alternately on and off. The frequency of the PWM control signal sent by PWM controller 1 and PWM controller 2 is 1Hz. A signal light that functions normally will not be recognized by the human eye as alternating on and off of the left and right areas. If the LED in one area of ​​the signal light is abnormal, the signal light will flicker and the fault will be recognized. PWM controller 1 sends a timing signal to PWM controller 2 while controlling the on and off of the LED light sources of Q1 and Q3. When PWM controller 2 receives the timing signal, it controls the on and off of the LED light sources of Q2 and Q4. In a single cycle, PWM controller 1 and PWM controller 2 are in the same high level state for 0.1s before alternating between high and low levels to compensate for the timing control error. PWM controller 1 sends a timing signal every 10s to avoid functional confusion caused by errors in the timing signal after long-term operation. The physical distance between the drive circuit and the signal light is less than 50mm to meet the requirements of aircraft electromagnetic compatibility.

[0027] The above only expresses the implementation mode of the present invention, and its description is relatively specific and detailed, but it cannot be understood as limiting the scope of the invention patent. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. Therefore, the protection scope of the patent of the present invention shall be based on the attached claims.

Claims

1. A method for detecting aircraft LED signal lights, characterized in that: The invention comprises the following steps: providing a lighting detection circuit, wherein the lighting detection circuit comprises an aircraft LED signal light, which has a first side LED and a second side LED; a first PWM controller, which is used to control the on-off frequency and timing of the first side LED; and a second PWM controller, which is used to control the on-off frequency and timing of the second side LED; and the on-off frequency and timing of the first side LED are controlled by the first PWM controller, and the on-off frequency and timing of the second side LED are controlled by the second PWM controller, and in a single control cycle, the control signal of the first PWM controller is different from or substantially different from the control signal of the second PWM controller, so as to alternately turn on and off the first side LED and the second side LED; the control signal of the first PWM controller and the control signal of the second PWM controller are different from or substantially different from the control signal of the second PWM controller, so as to alternately turn on and off the first side LED and the second side LED; The frequencies of the control signals are all lower than the flicker frequency limit that the human eye can recognize, so that the human eye can recognize the alternation of the lighting of the two side areas of the fault signal light; the human eye will not recognize the alternation of the lighting of the left and right side areas of a signal light with normal function. If the LED in one side area of ​​the signal light is abnormal, the signal light will flicker and the fault will be recognized; if the timing of the first PWM controller is exactly the same as the timing of the second PWM controller, the control signal of the first PWM controller is different from the control signal of the second PWM controller; if the timing of the second PWM controller is based on the timing of the first PWM controller, considering the time it takes for the timing signal of the first PWM controller to reach the second PWM controller, the control signal of the first PWM controller is basically different from the control signal of the second PWM controller.

2. The aircraft LED signal light illumination detection method according to claim 1, characterized in that: In a single control cycle, the control signal of the first PWM controller and the control signal of the second PWM controller are identical only for a period of time to compensate for a timing control error.

3. The aircraft LED signal light illumination detection method according to claim 1, characterized in that: The first PWM controller outputs a light-on signal in the first half cycle and a light-off signal in the second half cycle, while the second PWM controller outputs a light-off signal in the first half cycle and a light-on signal in the second half cycle.

4. The aircraft LED signal light illumination detection method according to claim 1, characterized in that: Every several control cycles, the first PWM controller will output a timing signal to the second PWM controller to prevent timing confusion.

5. The aircraft LED signal light illumination detection method according to claim 1, characterized in that: The first PWM controller controls the first-side LED through a first driving circuit, and the second PWM controller controls the second-side LED through a second driving circuit.

6. The aircraft LED signal light illumination detection method according to claim 1, characterized in that: The physical distance between the driving circuit and the LED is less than a certain distance to meet the requirements of electromagnetic compatibility of aircraft.

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