An aircraft control system
By using GPS or IMU to sense wind direction through the aircraft control system, combined with the control module and WAL button, the aircraft position is automatically corrected to solve the aircraft deviation problem, thereby improving the stability and alignment accuracy of the aircraft.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- AUTOFLIGHT (KUNSHAN) CO LTD
- Filing Date
- 2024-12-30
- Publication Date
- 2026-06-30
AI Technical Summary
Aircraft are easily affected by airflow and deviate during flight, requiring a control system that automatically corrects the position to align with the direction of the airflow.
The aircraft control system employs a flight control module and a control module. It uses sensors such as GPS or IMU to detect wind direction, and the control module automatically corrects the aircraft's position to align with the direction of the incoming flow. Manual control is achieved by combining the WAL button.
This technology enables the aircraft to automatically align itself with the direction of the incoming flow after deflection, improving flight stability and accuracy.
Smart Images
Figure CN122308337A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aircraft, and more specifically, to an aircraft control system. Background Technology
[0002] Aircraft are susceptible to deviation from their intended flight path due to airflow. Therefore, a control system is needed to automatically correct the aircraft's position after deviation, bringing the nose back in the direction of the oncoming airflow. Summary of the Invention
[0003] The purpose of this invention is to provide an aircraft control system that can automatically correct the position of the aircraft after it has deviated, thereby aligning the nose of the aircraft with the direction of the oncoming flow.
[0004] To achieve this objective, the present invention adopts the following technical solution:
[0005] This invention provides an aircraft control system for controlling an aircraft to automatically align with the incoming wind direction. The flight modes include vertical takeoff and landing mode, cruise mode, and switching mode. The control system includes a flight control module and a control module. The control module includes a user-operable control device that can send different commands to the flight control module to control the aircraft to automatically align with the incoming wind direction.
[0006] Preferably, the control system includes a sensing device that can sense the direction of the incoming wind. When the command is sent to the flight control module, the flight control module uses the sensing device to control the aircraft to automatically align with the direction of the incoming wind.
[0007] Preferably, the sensing device is GPS. The aircraft's navigation system estimates the aircraft's position based on the GPS. When a crosswind blows the aircraft off course, command 'a' is sent to the control module to control the aircraft to shift in the opposite direction of the blow, thereby correcting its position.
[0008] Preferably, the sensing device is an IMU. The aircraft's navigation system estimates the aircraft's position based on the IMU. When a crosswind blows the aircraft off course, command b is sent to the control module to control the aircraft to deviate in the opposite direction of the blow, thereby correcting its position.
[0009] Preferably, the aircraft continuously updates its position using the GPS, and determines the crosswind direction by comparing the target position with the current hovering position.
[0010] Preferably, the aircraft continuously updates its position using the IMU, and the aircraft determines the crosswind direction by comparing the difference between the target position and the current hovering position.
[0011] Preferably, the control device includes a WAL button. When the button is pressed, a command is sent to the flight control module, and the nose of the aircraft will automatically align with the incoming wind direction.
[0012] Preferably, the button is a virtual button integrated on the touchscreen. Attached Figure Description
[0013] Figure 1 This is a schematic diagram showing that the aircraft does not deviate from its course;
[0014] Figure 2 This is a diagram illustrating the aircraft rolling to the left.
[0015] Figure 3 This is a diagram illustrating an aircraft rolling to the right.
[0016] Figure 4 This is a schematic diagram of the aircraft's control system;
[0017] Figure 5 This is a schematic diagram of an aircraft using GPS as its sensing device;
[0018] Figure 6 This is a schematic diagram of an aircraft's sensing device being an IMU;
[0019] Figure 7 This is a schematic diagram of the aircraft control module;
[0020] Figure 8 This is a schematic diagram of the aircraft's control system. Detailed Implementation
[0021] The following embodiments further illustrate the technical solutions of this application. It should be understood that the specific embodiments described herein are merely for explaining this application. Furthermore, it should be noted that, for ease of description, only the parts relevant to this application are shown in the accompanying drawings, not all of them.
[0022] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections or detachable connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; or internal connections between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.
[0023] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.
[0024] like Figure 1 As shown, this application discloses an aircraft control system 200 for controlling an aircraft 100 to automatically align with the incoming wind direction. The flight modes include vertical takeoff and landing mode, cruise mode, and switching mode. The control system 200 includes a flight control module 300 and a control module 400. The control module 400 includes a user-operable control device 410, which can send different commands to the flight control module 300 to control the aircraft 100 to automatically align with the incoming wind direction.
[0025] like Figure 2 As shown, the control system 200 also includes a sensor 500. When there is a wind coming from the right, the aircraft 100 will be blown to the left and form a roll angle β. At this time, after the aircraft 100 senses the direction of the incoming wind according to the sensor 500, the control module 400 controls the nose to shift to the right and align with the direction of the incoming wind.
[0026] like Figure 3 As shown, the control system 200 also includes a sensor 500. When there is a wind coming from the left, the aircraft 100 will be blown to the right and form a roll angle β. At this time, after the aircraft 100 senses the direction of the incoming wind according to the sensor 500, the control module 400 controls the nose to shift to the left and align with the direction of the incoming wind.
[0027] Please refer to the following: Figure 4 In this application, the control system 200 also includes a sensor 500, which can sense the wind direction of the incoming flow. When command a or command b is sent to the flight control module 300, the flight control module 300 uses the sensor 500 to control the aircraft 100 to shift to the windy side, and the control module 400 controls the nose to shift so as to align with the wind direction of the incoming flow.
[0028] Please refer to the following: Figure 5 For example, in Figure 5In this context, sensor 500 can be GPS, also known as the Global Positioning System, a high-precision radio navigation and positioning system developed and launched by the United States based on artificial Earth satellites. GPS provides accurate geographical location, vehicle speed, and precise time information anywhere in the world and in near-Earth space. Since its inception, GPS has attracted numerous users due to its high precision, all-weather operation, global coverage, and convenience. The navigation system of aircraft 100 estimates the aircraft's position based on GPS. When a crosswind blows aircraft 100 to one side, command 'a' is sent to control module 400. Control module 400 then controls aircraft 100 to deviate in the opposite direction of the initial wind deviation, thus determining the direction of the incoming wind.
[0029] Now continue to refer to Figure 5 In this application, the aircraft 100 can also continuously update its position via GPS. The aircraft 100 determines the direction of the incoming wind by comparing the difference between the target position and the current hovering position.
[0030] Please refer to the following: Figure 6 For example, in Figure 6 In this context, the sensing device 500 can be an IMU, also known as an inertial measurement unit, which measures the three-axis attitude angles (or angular rates) and acceleration of an object. Typically, an IMU contains three single-axis accelerometers and three single-axis gyroscopes. The accelerometers detect the acceleration signals of the object along the three independent axes of the carrier coordinate system, while the gyroscopes detect the angular velocity signals of the carrier relative to the navigation coordinate system. By measuring the angular velocity and acceleration of the object in three-dimensional space, the object's attitude can be calculated. This has significant application value in navigation. The navigation system of the aircraft 100 estimates the aircraft's position based on the IMU. When a crosswind blows the aircraft 100 to one side, command b is sent to the control module 400. The control module 400 controls the aircraft 100 to deflect in the opposite direction of the initial blown direction, thus determining the direction of the incoming wind.
[0031] like Figure 7 and Figure 8 As shown, the control device 410 of this application includes a WAL button 420. The button 420 can be an actual physical button or a virtual button 420 integrated on the touch screen.
[0032] When button 420 is pressed, command a or command b is sent to the control module 400 of aircraft 100. GPS or IMU senses the wind direction of the incoming flow and then controls aircraft 100 to shift in the opposite direction of the initial blown direction. At this time, the nose of the aircraft will be aligned with the direction of the incoming flow.
[0033] The above embodiments are merely illustrative of the principles and effects of this application. Any person skilled in the art can modify or alter the above embodiments without departing from the purpose of this application. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the purpose disclosed in this application should still be covered by the claims of this application.
Claims
1. An aircraft control system for controlling an aircraft to automatically align with the oncoming wind direction, wherein the flight modes include vertical takeoff and landing mode, cruise mode, and switching mode, characterized in that, The control system includes: Flight control module and control module; The control module includes a user-operable control device that can send different commands to the flight control module to control the aircraft to automatically align with the incoming wind direction.
2. The aircraft control system according to claim 1, characterized in that, The control system includes a sensing device that can detect the direction of the incoming wind. When the command is sent to the flight control module, the flight control module uses the sensing device to control the aircraft to automatically align with the direction of the incoming wind.
3. The aircraft control system according to claim 2, characterized in that, The sensing device is GPS. The aircraft's navigation system estimates the aircraft's position based on the GPS. When a crosswind blows the aircraft off course, command 'a' is sent to the control module to control the aircraft to shift in the opposite direction of the blow, thereby correcting its position.
4. The aircraft control system according to claim 2, characterized in that, The sensing device is an IMU. The aircraft's navigation system estimates the aircraft's position based on the IMU. When a crosswind blows the aircraft off course, command b is sent to the control module to control the aircraft to deviate in the opposite direction of the blow, thereby correcting its position.
5. The aircraft control system according to claim 3, characterized in that, The aircraft continuously updates its position using the GPS, and determines the crosswind direction by comparing the target position with the current hovering position.
6. The aircraft control system according to claim 4, characterized in that, The aircraft continuously updates its position using the IMU, and determines the crosswind direction by comparing the target position with the current hovering position.
7. The aircraft control system according to claim 1, characterized in that, The control device includes a WAL button. When the button is pressed, a command is sent to the flight control module, and the nose of the aircraft will automatically align with the incoming wind direction.
8. The aircraft control system according to claim 7, characterized in that, The button is a virtual button integrated into the touchscreen.