Circular liquid crystal aviation instrument based on CAN bus
Patent Information
- Application Number
- CN202522069042.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-26
- Publication Date
- 2026-08-21
- Estimated Expiration
- 2035-09-26
AI Technical Summary
[0005]本实用新型的目的在于提供一种基于CAN总线的圆形液晶航空仪表，以解决上述背景技术中提出的仪表安装繁琐，可靠性低，显示信息单一的问题
本实用新型通过设置的圆形液晶显示模组，便于模拟传统圆形仪表的显示布局，契合飞行员对传统圆形仪表布局的阅读习惯，无需对仪表显示布局进行重新适应，同时其采用圆形结构设计，可匹配传统机械仪表的安装尺寸，能直接替换原有机械仪表，无需大规模改造仪表板，降低航空电子设备升级成本，实现即插即用、升级便捷，且该显示模组无活动部件，属于全固态电子设计，寿命长，可靠性高于传统机械仪表的显示部件，能减少因显示部件故障导致的仪表问题，还能综合显示飞行参数，如姿态、航向、高度、空速等，及导航信息，实现信息集成呈现，让飞行员直观获取多种数据，提升信息读取效率，同时可根据飞行阶段突出重点数据，进一步优化信息展示效果，满足不同飞行场景下的信息获取需求。
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Figure CN224670088U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of avionics technology, specifically to a circular LCD aviation instrument based on a CAN bus. Background Technology
[0002] In the field of avionics technology, traditional aviation instruments are the basic equipment for general aviation or light aircraft to monitor and display flight status. They are mainly divided into two categories: mechanical and electromechanical. Their core function is to present pilots with key parameters during flight, such as attitude, heading, altitude, airspeed and other basic flight data. Some instruments can also assist in displaying simple flight status information. These instruments have long been used in the instrument panel configuration of various general aviation and light aircraft. They are important tools for pilots to obtain flight data and judge flight status during flight, and provide basic data support for traditional aviation flight operations.
[0003] However, it still has some drawbacks. For example, current aviation instruments are bulky and heavy, have easily worn moving parts, relatively low reliability, fixed and simple display information, and difficulties in information exchange between different instruments. Although the flat-panel electronic flight instrument system that has emerged in recent years has solved some of these problems, its installation often requires modification of the entire instrument panel, which is costly and does not conform to the pilot's reading habits of the traditional circular instrument layout.
[0004] To address the aforementioned issues, this application proposes a circular LCD aviation instrument based on a CAN bus. Utility Model Content
[0005] The purpose of this invention is to provide a circular LCD aviation instrument based on a CAN bus, so as to solve the problems of cumbersome instrument installation, low reliability, and limited information display mentioned in the background art.
[0006] To achieve the above objectives, the technical solution adopted by this utility model is as follows: a circular LCD aviation instrument based on a CAN bus, comprising an instrument mounting plate, an instrument body fixedly connected inside the instrument mounting plate, the number of the instrument bodies being multiple sets, a polygonal shell fixedly connected to the front outer surface of the instrument mounting plate, and a circular LCD display module fixedly connected to the front outer surface of the polygonal shell.
[0007] Preferably, the rear end of the circular liquid crystal display module is electrically connected to a main processing control unit, the main processing control unit is fixedly connected to the inner cavity of the instrument body, and the front end of the main processing control unit is fixedly connected to a built-in sensor module.
[0008] Preferably, the front outer surface of the polygonal housing is fixedly connected with screws and a rotary encoder, and the rear end of the rotary encoder is fixedly connected with a main processing control unit.
[0009] Preferably, a cylindrical shell and a nut are fixedly connected to the rear outer surface of the polygonal shell, and the inner wall of the nut is fixedly connected to the outer wall of the screw.
[0010] Preferably, the rear outer surface of the cylindrical shell is fixedly connected to a GPS interface, a CAN bus communication interface, and a pneumatic interface.
[0011] Preferably, the front end of the CAN bus communication interface is fixedly connected to the main processing control unit, and multiple sets of the instrument bodies are interconnected through the CAN bus communication interface.
[0012] Compared with the prior art, the beneficial effects of this utility model are: This invention utilizes a circular LCD display module to simulate the display layout of traditional circular instruments, aligning with pilots' reading habits and eliminating the need for readjustment to the instrument display layout. Its circular structure also matches the installation dimensions of traditional mechanical instruments, allowing direct replacement without large-scale instrument panel modifications, thus reducing upgrade costs for avionics equipment. This achieves plug-and-play functionality and convenient upgrades. Furthermore, the display module has no moving parts, representing an all-solid-state electronic design with a long lifespan and higher reliability than traditional mechanical instrument display components, reducing instrument problems caused by display component failures. It can also comprehensively display flight parameters such as attitude, heading, altitude, airspeed, and navigation information, providing integrated information presentation. This allows pilots to intuitively access multiple data points, improving information retrieval efficiency. Additionally, it can highlight key data based on flight phases, further optimizing the information display to meet the information acquisition needs of different flight scenarios. Attached Figure Description
[0013] Figure 1 This is a schematic diagram of the overall structure of a circular LCD aviation instrument based on a CAN bus according to this utility model; Figure 2 This is a schematic diagram of the front end of a circular LCD aviation instrument based on a CAN bus according to this utility model; Figure 3 This is a schematic diagram of the rear structure of a circular LCD aviation instrument based on a CAN bus according to this utility model; Figure 4 This is an enlarged structural diagram of A in a circular LCD aviation instrument based on a CAN bus according to this utility model.
[0014] In the diagram: 1. Instrument mounting plate; 2. Instrument body; 3. Circular LCD display module; 4. Screw; 5. Rotary encoder; 6. Polygonal housing; 7. Cylindrical housing; 8. Nut; 9. GPS interface; 10. CAN bus communication interface; 11. Air pressure interface. Detailed Implementation
[0015] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.
[0016] Please see Figures 1-4 A circular LCD aviation instrument based on a CAN bus includes an instrument mounting plate 1. Multiple instrument bodies 2 are fixedly connected inside the mounting plate 1. A polygonal outer shell 6 is fixedly connected to the front outer surface of the mounting plate 1, and a circular LCD display module 3 is fixedly connected to the front outer surface of the polygonal outer shell 6. The circular LCD display module 3 facilitates the simulation of the display layout of traditional circular instruments, conforming to the pilot's reading habits of traditional circular instrument layouts, eliminating the need for readjustment to the instrument display layout. Furthermore, its circular structure design allows it to match the installation dimensions of traditional mechanical instruments, enabling direct replacement of the original... With mechanical instruments, there is no need for large-scale instrument panel modifications, reducing the cost of upgrading avionics equipment. It achieves plug-and-play functionality and convenient upgrades. Moreover, the display module has no moving parts and is an all-solid-state electronic design, which has a long lifespan and higher reliability than the display components of traditional mechanical instruments. It can reduce instrument problems caused by display component failures. It can also comprehensively display flight parameters such as attitude, heading, altitude, airspeed, and navigation information, achieving integrated information presentation. This allows pilots to intuitively obtain a variety of data, improving information reading efficiency. At the same time, it can highlight key data according to the flight stage to further optimize the information display effect and meet the information acquisition needs of different flight scenarios.
[0017] In this embodiment, as shown Figures 1-2As shown, the rear end of the circular LCD display module 3 is electrically connected to the main processing control unit. The main processing control unit is fixedly connected to the inner cavity of the instrument body 2. The front end of the main processing control unit is fixedly connected to a built-in sensor module. The front outer surface of the polygonal housing 6 is fixedly connected to a screw 4 and a rotary encoder 5. The rear end of the rotary encoder 5 is fixedly connected to the main processing control unit. The rear outer surface of the polygonal housing 6 is fixedly connected to a cylindrical housing 7 and a nut 8. The inner wall of the nut 8 is fixedly connected to the outer wall of the screw 4. The main processing control unit processes the received data, runs the graphical interface, and generates display information including flight parameters such as attitude, heading, altitude, airspeed, and navigation information. The information will be transmitted to the circular LCD module 3, which is electrically connected to itself and fixed to the outer surface of the front end of the polygonal housing 6. The circular LCD module 3 displays the information in a layout that simulates a traditional circular instrument. The pilot can send commands to the main processing control unit by rotating and pressing the rotary encoder 5 fixed to the outer surface of the front end of the polygonal housing 6 to adjust the input data, operate the display menu, or switch the graphical interface, such as the level indicator, attitude indicator, airspeed indicator, altimeter, etc., and the working mode. The instrument mounting plate 1 provides a fixed support for the instrument body 2. The polygonal housing 6 is stably installed by the cooperation of screws 4 and nuts 8, which together ensure the stable operation of the instrument as a whole.
[0018] In this embodiment, as shown Figures 3-4 As shown, a GPS interface 9, a CAN bus communication interface 10, and a pressure interface 11 are fixedly connected to the rear outer surface of the cylindrical housing 7. A main processing control unit is fixedly connected to the front end of the CAN bus communication interface 10. Multiple instrument bodies 2 are interconnected through the CAN bus communication interface 10. When a circular LCD aviation instrument based on a CAN bus is working, the main processing control unit fixed in the inner cavity of the instrument body 2 first receives data. The data sources are, on the one hand, the raw data collected by the built-in sensor module fixedly connected to its front end, and on the other hand, the external data obtained through the GPS interface 9 and the pressure interface 11 fixedly connected to the rear outer surface of the cylindrical housing 7. At the same time, multiple instrument bodies 2 are interconnected through the CAN bus communication interface 10 on their respective cylindrical housings 7 to realize data exchange between them.
[0019] Working principle When a circular LCD aviation instrument based on a CAN bus is in operation, the main processing control unit, fixed inside the instrument body 2, first receives data. The data sources are, on the one hand, raw data collected by the built-in sensor module fixedly connected to its front end, and on the other hand, external data obtained through the GPS interface 9 and the barometric pressure interface 11 fixedly connected to the rear outer surface of the cylindrical housing 7. Simultaneously, multiple instrument bodies 2 are interconnected through the CAN bus communication interface 10 on their respective cylindrical housings 7, enabling data exchange. Then, the main processing control unit processes the received data, runs the graphical interface, and generates display information including flight parameters such as attitude, heading, altitude, airspeed, and navigation information. The information is then transmitted to the circular LCD module 3, which is electrically connected to itself and fixed to the outer surface of the front end of the polygonal housing 6. The circular LCD module 3 displays the information in a layout that simulates a traditional circular instrument. The pilot can send commands to the main processing control unit by rotating and pressing the rotary encoder 5, which is fixed to the outer surface of the front end of the polygonal housing 6, to adjust the input data, operate the display menu, or switch the graphical interface, such as the level indicator, attitude indicator, airspeed indicator, altimeter, etc., and the working mode. The instrument mounting plate 1 provides a fixed support for the instrument body 2. The polygonal housing 6 is stably installed by the cooperation of screws 4 and nuts 8, which together ensure the stable operation of the instrument as a whole.
[0020] Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.
Claims
1. A circular LCD aviation instrument based on a CAN bus, comprising an instrument mounting plate (1), characterized in that: The instrument mounting plate (1) is internally fixedly connected to an instrument body (2), and there are multiple sets of instrument bodies (2). A polygonal shell (6) is fixedly connected to the front outer surface of the instrument mounting plate (1), and a circular liquid crystal display module (3) is fixedly connected to the front outer surface of the polygonal shell (6).
2. A circular LCD aviation instrument based on a CAN bus according to claim 1, characterized in that: The rear end of the circular liquid crystal display module (3) is electrically connected to the main processing control unit, which is fixedly connected to the inner cavity of the instrument body (2), and the front end of the main processing control unit is fixedly connected to the built-in sensor module.
3. A circular LCD aviation instrument based on a CAN bus according to claim 2, characterized in that: The front outer surface of the polygonal shell (6) is fixedly connected with screws (4) and a rotary encoder (5), and the rear end of the rotary encoder (5) is fixedly connected with a main processing control unit.
4. A circular LCD aviation instrument based on a CAN bus according to claim 3, characterized in that: The rear outer surface of the polygonal shell (6) is fixedly connected to a cylindrical shell (7) and a nut (8), and the inner wall of the nut (8) is fixedly connected to the outer wall of the screw (4).
5. A circular LCD aviation instrument based on a CAN bus according to claim 4, characterized in that: The rear outer surface of the cylindrical shell (7) is fixedly connected to a GPS interface (9), a CAN bus communication interface (10), and a pneumatic interface (11).
6. A circular LCD aviation instrument based on a CAN bus according to claim 5, characterized in that: The main processing control unit is fixedly connected to the front end of the CAN bus communication interface (10), and multiple sets of the instrument bodies (2) are interconnected through the CAN bus communication interface (10).