Dual-mode cockpit temperature control method based on photoelectric encoder with button switch

Abstract

The invention provides a dual-mode aircraft cockpit temperature control method based on a photoelectric encoder with a button switch, and belongs to the technical field of aircraft electromechanical control system cockpit temperature control. The method comprises the steps that an electromechanical control system drives the photoelectric encoder to be powered on, a current photoelectric encoder rotation gear signal is calculated, a current temperature adjusting mode 1 or a current temperature adjusting mode 2 is determined, and the photoelectric encoder is powered on; a cockpit temperature target value set by a pilot is calculated, and meanwhile the electromechanical control system uploads the current temperature adjusting mode and the target temperature to cockpit display equipment. A dual-mode temperature control design is carried out based on a photoelectric encoder with a button switch, the target temperature value of the cockpit can be set as far as possible, the temperature control precision of the cockpit can be improved, and the comfortable temperature experience of the cockpit of different aircrafts can be met as far as possible; dual-redundancy optical encoder signals and button switch state acquisition are adopted, the cabin temperature is judged through corresponding logic, and the temperature adjusting function is reserved to the maximum extent under the abnormal condition.

Description

Technical Field

[0001] This invention belongs to the field of cabin temperature control technology in aircraft electromechanical control systems, specifically relating to a method for controlling aircraft cabin temperature based on a dual-mode system with push-button switch and photoelectric encoder. Background Technology

[0002] As aircraft are used in more and more scenarios and combat missions in modern society, the requirements for the sensory comfort characteristics of the cockpit temperature are becoming increasingly stringent. This poses a severe challenge to the accurate and timely operation of the onboard electromechanical control system for cockpit temperature control, leading to the development of highly reliable and high-performance cockpit temperature control technologies. Summary of the Invention

[0003] The purpose of this invention is to provide a cabin temperature control technology solution with higher reliability and performance.

[0004] To achieve the above objectives, the present invention provides the following technical solution: a method for controlling aircraft cabin temperature based on a dual-mode aircraft cabin with a push-button switch and photoelectric encoder, the method comprising: The electromechanical control system drives the photoelectric encoder to power on. The current rotation gear signal of the photoelectric encoder is calculated by real-time dual-redundancy acquisition of two phase pulse signals output from the pilot's rotary photoelectric encoder. The current temperature adjustment mode (mode 1 or mode 2) is determined by real-time acquisition of discrete signals from the button status. The pilot's target cabin temperature value is calculated based on the temperature adjustment mode 1 or mode 2 settings and the corresponding temperature table. At the same time, the electromechanical control system uploads the current temperature adjustment mode and target temperature to the cockpit display device. When entering temperature adjustment mode 2, the electromechanical control system drives the button light to illuminate.

[0005] The aircraft cabin temperature control method based on a dual-mode photoelectric encoder with a push-button switch provided by the present invention also has the following technical features: the two pulse signals output by the photoelectric encoder have a phase difference of 90 degrees, and the combined level states of phase A and phase B have four types in clockwise order: 00, 10, 11, 01, and the reverse is counterclockwise order. Each change in level combination is one level.

[0006] The aircraft cabin temperature control method based on a dual-mode photoelectric encoder with a push-button switch provided by this invention also has the following technical features: the electromechanical control system defaults to the initial level combination state of phase A and phase B output by the photoelectric encoder as level 0. By acquiring the level change states of the two pulse signals in real time with dual redundancy, clockwise rotation increases the level by +1 level and counterclockwise rotation increases the level by -1 level. When the level is rotated clockwise to the maximum level value, clockwise rotation continues without increasing the level value, while counterclockwise rotation continues to increase the level value. Similarly, when the level is rotated counterclockwise to the minimum level value, counterclockwise rotation continues without increasing the level value, while clockwise rotation continues to increase the level value. Finally, the photoelectric encoder level value 1 and level value 2 are calculated in real time.

[0007] The aircraft cabin temperature control method based on a dual-mode push-button switch and photoelectric encoder provided by this invention also has the following technical features: temperature adjustment mode 1 and mode 2 each have independent gear positions and temperature correspondences, with the default gear position 0 corresponding to 25°C.

[0008] The aircraft cockpit temperature control method based on a dual-mode photoelectric encoder with a button switch provided by this invention also has the following technical features: when the electromechanical control system collects two discrete signals of button status (both indicating button release), the temperature is controlled according to the temperature value of either the cockpit temperature sensor 1 or 2; when either of the two discrete signals of button status is button press, the temperature is controlled according to the temperature value of either the cockpit air supply temperature sensor 1 or 2. When the discrete signals of button status switch, the calculated values ​​of photoelectric encoder gear 1 and gear 2 are both set to 0. The gear values ​​of gear 1 and gear 2 are re-accumulated according to the pilot's rotation of the photoelectric encoder.

[0009] The aircraft cabin temperature control method based on a dual-mode push-button switch and photoelectric encoder provided by this invention also has the following technical feature: under normal circumstances, the light is off when the push-button switch is flipped up and on when it is pressed, which helps to remind the pilot to confirm the current temperature control mode of the electromechanical control system. When either cockpit in-cabin sensor 1 or cockpit in-cabin sensor 2 is normal, and either cockpit air supply sensor 1 or cockpit air supply sensor 2 is normal, the electromechanical control system switches to normal mode according to the push-button switch: When both cabin in-cabin sensor 1 and cabin in-cabin sensor 2 are faulty, but either cabin air supply sensor 1 or cabin air supply sensor 2 is normal, the electromechanical control system will actively enter temperature regulation mode 2 and turn on the lights. When both cabin air supply sensor 1 and cabin air supply sensor 2 malfunction, the electromechanical control system automatically enters temperature regulation mode 1 and the lights go out.

[0010] The aircraft cabin temperature control method based on a dual-mode push-button switch and photoelectric encoder provided by this invention also has the following technical feature: the temperature adjustment mode is uploaded in real time according to the previous step. When entering temperature control mode 1: If cabin sensor 1 is normal, upload the target temperature corresponding to photoelectric encoder gear 1; if cabin sensor 1 is faulty and cabin sensor 2 is normal, upload the target temperature corresponding to photoelectric encoder gear 2; if both cabin sensors 1 and 2 are faulty, upload the target temperature of 25℃ and control the temperature at 25℃. When entering temperature control mode 2: If cabin air supply sensor 1 is normal, upload the target temperature corresponding to the photoelectric encoder gear value 1; if cabin air supply sensor 1 is faulty and cabin air supply sensor 2 is normal, upload the target temperature corresponding to the photoelectric encoder gear value 2.

[0011] Beneficial effects: The dual-mode aircraft cabin temperature control method based on a push-button switch and photoelectric encoder provided in this application is designed with a push-button switch and photoelectric encoder for dual-mode temperature control. It can set the target cabin temperature value as much as possible, improve the cabin temperature control accuracy, and meet the cabin temperature comfort experience of different pilots as much as possible. It adopts a dual-mode temperature control system, which uses a single-mode dual-redundant cabin temperature sensor to collect data, and uses dual-redundant photoelectric encoder signals and push-button switch status data to collect data. The cabin temperature is determined through corresponding logic judgment, and the temperature adjustment function is retained to the maximum extent in abnormal situations. Attached Figure Description

[0012] To more clearly illustrate the technical solutions of the embodiments of this disclosure, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0013] Figure 1 This is a schematic block diagram of the electromechanical control system for acquiring and driving cabin temperature control provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of the two pulse signals of the photoelectric encoder of the present invention. Detailed Implementation

[0014] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. However, it should be noted that these embodiments are not intended to limit the present invention. Equivalent changes or substitutions in function, method, or structure made by those skilled in the art based on these embodiments are all within the protection scope of the present invention.

[0015] In the description of the embodiments of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the invention.

[0016] Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0017] The terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art will understand the specific meaning of these terms in this invention based on the specific circumstances.

[0018] like Figure 1-2 As shown, this embodiment of the invention provides a method for controlling aircraft cabin temperature based on a dual-mode aircraft cabin with a push-button switch and photoelectric encoder. The method includes: The electromechanical control system drives the photoelectric encoder to power on. The current rotation gear signal of the photoelectric encoder is calculated by real-time dual-redundancy acquisition of two phase pulse signals output from the pilot's rotary photoelectric encoder. The current temperature adjustment mode (mode 1 or mode 2) is determined by real-time acquisition of discrete signals from the button status. The pilot's target cabin temperature value is calculated based on the temperature adjustment mode 1 or mode 2 settings and the corresponding temperature table. At the same time, the electromechanical control system uploads the current temperature adjustment mode and target temperature to the cockpit display device. When entering temperature adjustment mode 2, the electromechanical control system drives the button light to illuminate.

[0019] In some embodiments, the two pulse signals output by the photoelectric encoder have a phase difference of 90 degrees. The combined level states of phase A and phase B have four options in clockwise order: 00, 10, 11, 01 (0 is low level, 1 is high level), and the opposite is counterclockwise order. Each change in level combination is one level.

[0020] In some embodiments, the electromechanical control system defaults to setting the initial level combination of phase A and phase B output by the photoelectric encoder to level 0. By acquiring the level changes of the two pulse signals in real time with dual redundancy, the level increases by +1 for each clockwise rotation and decreases by -1 for each counterclockwise rotation. When the clockwise rotation reaches the maximum level value, clockwise rotation stops increasing the level value, while counterclockwise rotation continues to increase the level value. Similarly, when the counterclockwise rotation reaches the minimum level value, counterclockwise rotation stops increasing the level value, while clockwise rotation continues to increase the level value. Finally, the photoelectric encoder level value 1 and level value 2 are calculated in real time.

[0021] In some embodiments, temperature adjustment mode 1 and mode 2 each have independent gear levels and temperature correspondences. The number of gear levels can be freely set to improve temperature accuracy as much as possible. The gear level and temperature correspondence can be adjusted according to the actual situation of the aircraft cabin. The default gear level 0 corresponds to 25°C.

[0022] In some embodiments, the electromechanical control system acquires two discrete signals of button status when both are "button released", and uses the temperature value of either the cabin temperature sensor 1 or 2 as the target temperature for temperature control; or either of the two discrete signals of button status when either is "button pressed", and uses the temperature value of either the cabin air supply temperature sensor 1 or 2 as the target temperature for temperature control. When the discrete signals of button status switch, the calculated values ​​of gear 1 and gear 2 of the photoelectric encoder are both set to 0, and the gear values ​​of gear 1 and gear 2 are re-accumulated according to the pilot's rotation of the photoelectric encoder.

[0023] In some embodiments, under normal circumstances, the button switch turns off when it is released and turns on when it is pressed, which helps to remind the pilot to confirm the current temperature control mode of the electromechanical control system. When either cockpit in-cabin sensor 1 or cockpit in-cabin sensor 2 is normal, and either cockpit air supply sensor 1 or cockpit air supply sensor 2 is normal, the electromechanical control system switches to normal mode according to the push-button switch: When both cabin in-cabin sensor 1 and cabin in-cabin sensor 2 are faulty, but either cabin air supply sensor 1 or cabin air supply sensor 2 is normal, the electromechanical control system will actively enter temperature regulation mode 2 and turn on the lights. When both cabin air supply sensor 1 and cabin air supply sensor 2 malfunction, the electromechanical control system automatically enters temperature regulation mode 1 and the lights go out.

[0024] In some embodiments, the temperature adjustment mode is uploaded in real time according to the previous step. When entering temperature control mode 1: If cabin sensor 1 is normal, upload the target temperature corresponding to photoelectric encoder gear 1; if cabin sensor 1 is faulty and cabin sensor 2 is normal, upload the target temperature corresponding to photoelectric encoder gear 2; if both cabin sensors 1 and 2 are faulty, upload the target temperature of 25℃ and control the temperature at 25℃. When entering temperature control mode 2: If cabin air supply sensor 1 is normal, upload the target temperature corresponding to the photoelectric encoder gear value 1; if cabin air supply sensor 1 is faulty and cabin air supply sensor 2 is normal, upload the target temperature corresponding to the photoelectric encoder gear value 2.

[0025] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention. The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the protection scope of the present invention.

Claims

1. A method for controlling aircraft cabin temperature based on a dual-mode photoelectric encoder with push-button switch, characterized in that, The method includes: The electromechanical control system drives the photoelectric encoder to power on. The current rotation gear signal of the photoelectric encoder is calculated by real-time dual-redundancy acquisition of two phase pulse signals output from the pilot's rotary photoelectric encoder. The current temperature adjustment mode (mode 1 or mode 2) is determined by real-time acquisition of discrete signals from the button status. The pilot's target cabin temperature value is calculated based on the temperature adjustment mode 1 or mode 2 settings and the corresponding temperature table. At the same time, the electromechanical control system uploads the current temperature adjustment mode and target temperature to the cockpit display device. When entering temperature adjustment mode 2, the electromechanical control system drives the button light to illuminate.

2. The aircraft cabin temperature control method based on a dual-mode photoelectric encoder with push-button switch as described in claim 1, characterized in that: The two pulse signals output by the photoelectric encoder have a phase difference of 90 degrees. The combined level states of phase A and phase B have four options in clockwise order: 00, 10, 11, 01, and counterclockwise order. Each change in the level combination corresponds to one level.

3. The aircraft cabin temperature control method based on a dual-mode photoelectric encoder with a push-button switch as described in claim 2, characterized in that: The electromechanical control system defaults to setting the initial level combination of phase A and phase B output from the photoelectric encoder to level 0. By acquiring the level changes of the two pulse signals in real time with dual redundancy, the level increases by +1 for each clockwise rotation and decreases by -1 for each counterclockwise rotation. When the level reaches the maximum value when rotating clockwise, clockwise rotation stops increasing the level value, while counterclockwise rotation continues to increase the level value. Similarly, when the level reaches the minimum value when rotating counterclockwise, counterclockwise rotation stops increasing the level value, while clockwise rotation continues to increase the level value. Finally, the photoelectric encoder level 1 and level 2 are calculated in real time.

4. The aircraft cabin temperature control method based on a dual-mode photoelectric encoder with push-button switch as described in claim 1, characterized in that: Temperature adjustment mode 1 and mode 2 each have independent settings and temperature correspondences, with the default setting 0 corresponding to 25℃.

5. The aircraft cabin temperature control method based on a dual-mode photoelectric encoder with push-button switch as described in claim 1, characterized in that: The electromechanical control system acquires two discrete signals of button status when both buttons are "button up", and uses the temperature value of either the cabin temperature sensor 1 or 2 as the target temperature for temperature control. When either button is "button down", the system uses the temperature value of either the cabin air supply temperature sensor 1 or 2 as the target temperature for temperature control. When the discrete signals of button status switch, the calculated values ​​of gear 1 and gear 2 of the photoelectric encoder are both set to 0. The gear values ​​of gear 1 and gear 2 are re-accumulated based on the pilot's rotation of the photoelectric encoder.

6. The aircraft cabin temperature control method based on a dual-mode photoelectric encoder with push-button switch according to claim 1, characterized in that: Under normal circumstances, the light is off when the push-button switch is popped up and on when it is pressed, which helps to remind the pilot to confirm the current temperature control mode of the electromechanical control system. When either cockpit in-cabin sensor 1 or cockpit in-cabin sensor 2 is normal, and either cockpit air supply sensor 1 or cockpit air supply sensor 2 is normal, the electromechanical control system switches to normal mode according to the push-button switch: When both cabin in-cabin sensor 1 and cabin in-cabin sensor 2 are faulty, but either cabin air supply sensor 1 or cabin air supply sensor 2 is normal, the electromechanical control system will actively enter temperature regulation mode 2 and turn on the lights. When both cabin air supply sensor 1 and cabin air supply sensor 2 malfunction, the electromechanical control system automatically enters temperature regulation mode 1 and the lights go out.

7. The aircraft cabin temperature control method based on a dual-mode photoelectric encoder with push-button switch as described in claim 1, characterized in that: Temperature adjustment mode is uploaded in real time according to the previous message. When entering temperature control mode 1: If cabin sensor 1 is normal, upload the target temperature corresponding to photoelectric encoder gear 1; if cabin sensor 1 is faulty and cabin sensor 2 is normal, upload the target temperature corresponding to photoelectric encoder gear 2; if both cabin sensors 1 and 2 are faulty, upload the target temperature of 25℃ and control the temperature at 25℃. When entering temperature control mode 2: If cabin air supply sensor 1 is normal, upload the target temperature corresponding to the photoelectric encoder gear value 1; if cabin air supply sensor 1 is faulty and cabin air supply sensor 2 is normal, upload the target temperature corresponding to the photoelectric encoder gear value 2.

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