Method for controlling air pressure in the area of a landing platform of an aircraft and in the area of the landing platform

Abstract

The application provides a take-off and landing platform of an aircraft and a method for controlling air pressure in an airspace near the take-off and landing platform. The take-off and landing platform comprises a take-off and landing layer and an air pressure regulation layer. The take-off and landing layer comprises a take-off and landing plane for carrying the aircraft. The air pressure regulation layer is located on a side of the take-off and landing plane away from the take-off and landing layer and is used for regulating air pressure at the take-off and landing plane. The air pressure regulation layer can adjust the air pressure environment in the airspace near the take-off and landing platform, reduce the influence of air pressure fluctuation caused by ground effect on the aircraft, and ensure that the aircraft can take off and land smoothly.

Description

Technical Field

[0001] This application relates to the field of aircraft take-off and landing platform technology, and in particular to an aircraft take-off and landing platform and a method for controlling air pressure in the airspace near the take-off and landing platform. Background Technology

[0002] With the comprehensive development of the low-altitude economy, vertical takeoff and landing (VTOL) aircraft, as one of the core technology paths, are receiving high attention.

[0003] The core mechanism for an aircraft to achieve vertical takeoff and landing lies in the use of a multi-rotor system. Its working principle is based on the high-speed rotation of multiple rotors, which causes rapid and non-uniform dynamic changes in the air below the fuselage. This process can cause ground effect when operating close to the ground. Ground effect can interfere with the stability of the airflow below the aircraft and threaten the smoothness and safety of the aircraft's takeoff and landing process. Summary of the Invention

[0004] This application provides a take-off and landing platform for an aircraft and a method for controlling air pressure in the airspace near the take-off and landing platform.

[0005] A first aspect of this application provides a take-off and landing platform for an aircraft, the take-off and landing platform comprising:

[0006] The takeoff and landing level includes a takeoff and landing plane for carrying aircraft.

[0007] The air pressure regulation layer is located on the side opposite to the takeoff and landing plane of the takeoff and landing layer, and is used to regulate the air pressure at the takeoff and landing plane.

[0008] In one embodiment, the pressure control layer includes a pressure control module and a pressure control actuator; the pressure control actuator is used to provide the air pressure required during the take-off and landing of the aircraft; the pressure control module is used to control the pressure control actuator according to the air pressure information at the take-off and landing plane.

[0009] In one embodiment, the air pressure regulating actuator includes multiple fans arranged in a dispersed manner, and the air pressure regulating module is used to regulate the operating status of the fans.

[0010] In one embodiment, the take-off and landing platform further includes multiple sensors evenly distributed on the take-off and landing layer. The sensors are used to collect airflow information and transmit the airflow information to the air pressure regulation layer.

[0011] In one embodiment, the sensor includes a wind speed sensor and a barometric pressure sensor, which are disposed on the takeoff and landing plane, within the takeoff and landing layer, and on the side of the takeoff and landing layer facing the barometric pressure control layer.

[0012] In one embodiment, the take-off and landing layer is provided with a plurality of dispersed ventilation holes, which are used to transport the airflow generated by the pressure regulation layer to the take-off and landing plane.

[0013] In one embodiment, the cross-section of the vent hole is honeycomb-shaped.

[0014] A second aspect of this application provides a method for controlling air pressure in the airspace near a takeoff and landing platform, for controlling the air pressure at the takeoff and landing plane of the platform, the method comprising:

[0015] Collect airflow information at the takeoff and landing plane during aircraft takeoff and landing;

[0016] Based on the flight dynamics model of the aircraft and the airflow information, the air pressure range that satisfies the flight stability of the aircraft is obtained, and the optimal air pressure value within the air pressure range is derived.

[0017] The air pressure at the take-off and landing plane is adjusted to the optimal value according to the air pressure.

[0018] In one embodiment, the control method further includes: obtaining an ideal aerodynamic model of the take-off and landing platform at the take-off and landing plane in an unchanging state, and performing error identification based on the ideal aerodynamic model to obtain a real-time aerodynamic model at the take-off and landing plane, and calculating a control scheme by which the pressure regulation layer adjusts the air pressure at the take-off and landing plane to the optimal air pressure value based on the difference between the real-time aerodynamic model and the ideal aerodynamic model.

[0019] In one embodiment, before identifying errors based on the ideal aerodynamic model, the control method further includes: correcting the ideal aerodynamic model of the take-off and landing platform at the take-off and landing plane in an unchanging state based on external disturbances.

[0020] When an aircraft takes off or lands on an takeoff and landing platform, the aircraft approaches the landing level. The rapid airflow caused by the aircraft's rotor interacts with the landing plane, creating a ground effect. This ground effect generates turbulence near the landing plane, interfering with the stability of the airflow below the aircraft. This makes it difficult for the aircraft to maintain its intended ascent or descent trajectory, reducing the smoothness and safety of the takeoff and landing process. The air pressure regulation layer of the takeoff and landing platform provided in this application embodiment can regulate the air pressure environment at the takeoff and landing platform, reducing the impact of air pressure fluctuations caused by the ground effect on the aircraft and ensuring smooth takeoff and landing.

[0021] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit this application. Attached Figure Description

[0022] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[0023] Figure 1 A three-dimensional structural diagram of a take-off and landing platform provided in an embodiment of this application;

[0024] Figure 2 This is a schematic diagram of the structure of a vent provided in an embodiment of this application;

[0025] Figure 3 This is a schematic diagram of the sensor distribution provided in one embodiment of this application;

[0026] Figure 4 This is a schematic diagram of the structure of a pressure regulating layer provided in an embodiment of this application. Detailed Implementation

[0027] The technical solutions in the embodiments (or "implementations") of this application will be clearly and completely described herein with reference to the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements.

[0028] If the embodiments of this application contain terms relating to directional indications or positional relationships (such as up, down, left, right, front, back, inside, outside, top, bottom, center, vertical, horizontal, longitudinal, transverse, length, width, counterclockwise, clockwise, axial, radial, circumferential, etc.), such terms are only used to explain the relative positional relationships and movements between components in a specific posture (as shown in the attached figures); if the specific posture changes, the directional indications or positional relationships will also change accordingly. Furthermore, the terms "first" and "second" used in the embodiments of this application are only for descriptive convenience and should not be construed as indicating or implying relative importance.

[0029] The take-off and landing platform of the aircraft and the air pressure control method of the take-off and landing platform according to embodiments of this application will be described in detail below with reference to the accompanying drawings. Unless otherwise specified, the features of the following embodiments and implementation methods can complement or combine with each other.

[0030] like Figures 1 to 4 As shown in the figure, this application embodiment provides a take-off and landing platform 100 for an aircraft, the take-off and landing platform 100 including a take-off and landing layer 10 and a pressure regulation layer 20. The take-off and landing layer 10 includes a take-off and landing plane 101, which is used to support the aircraft. The pressure regulation layer 20 is located on the side opposite to the take-off and landing plane 101 of the take-off and landing layer 10, and is used to regulate the air pressure at the take-off and landing plane 101.

[0031] The takeoff and landing layer 10 is the part of the takeoff and landing platform 100 that directly supports the aircraft. The takeoff and landing plane 101 of the takeoff and landing layer 10 is the parking and takeoff / landing area for the aircraft. During the high-speed rotation of the aircraft's multiple rotors, the air beneath the aircraft fuselage undergoes rapid and irregular movement. When the aircraft takes off or lands on the takeoff and landing platform 100, the aircraft approaches the takeoff and landing layer 10. The rapid airflow caused by the aircraft's rotors interacts with the takeoff and landing plane 101, creating a ground effect. This ground effect generates turbulence near the takeoff and landing plane 101, interfering with the stability of the airflow beneath the aircraft. This makes it difficult for the aircraft to maintain its intended ascent or descent trajectory, reducing the smoothness and safety of the takeoff and landing process. The pressure regulation layer 20 can regulate the air pressure environment at the takeoff and landing plane 101, reducing the impact of air pressure fluctuations caused by the ground effect on the aircraft and ensuring smooth takeoff and landing.

[0032] In one embodiment, such as Figure 1 and Figure 2 As shown, the takeoff and landing layer 10 is provided with multiple dispersed ventilation holes 102, which are used to transport the airflow generated by the pressure regulation layer 20 to the takeoff and landing plane 101. By regulating the airflow through the pressure regulation layer 20, the airflow reaches the takeoff and landing plane 101 through the ventilation holes 102, which can alleviate the turbulence generated between the aircraft and the takeoff and landing plane 101 and help reduce the aircraft's turbulence.

[0033] In one embodiment, the cross-section of the vent 102 is honeycomb-shaped. The honeycomb-shaped vent 102 allows for high structural strength while maintaining the lightweight structure of the landing layer 10, ensuring that the vent 102 retains its structural integrity under airflow pressure or external impact. Furthermore, the honeycomb-shaped vent 102 can uniformly guide and disperse airflow, ensuring that the airflow evenly covers the landing plane 101, thus improving the precision and effectiveness of airflow control.

[0034] In one embodiment, the drag coefficient of the landing layer 10 is between 0.1 and 0.2. For example, the drag coefficient of the landing layer 10 can be 0.12, 0.15, 0.18, etc. A lower drag coefficient of the landing layer 10 can reduce airflow losses when passing through the landing layer 10, which is more conducive to achieving precise airflow control and also helps to reduce the energy consumption of the landing platform.

[0035] In one embodiment, the material of the landing layer 10 can be carbon fiber, stainless steel, or other similar materials. When the material of the landing layer 10 is, for example, carbon fiber, the landing layer 10 can achieve both high strength and lightweight design.

[0036] In one embodiment, such as Figure 1 and Figure 3As shown, the takeoff and landing platform 100 also includes multiple sensors 30, which are evenly distributed on the takeoff and landing layer 10. The sensors 30 collect airflow information and transmit it to the pressure control layer 20. The sensors 30 can continuously monitor the airflow environment at the takeoff and landing plane 101, allowing the pressure control layer 20 to dynamically adjust the pressure environment at the takeoff and landing plane 101 based on the airflow information, which helps improve the stability of aircraft takeoff and landing.

[0037] In one embodiment, the sensor 30 includes a wind speed sensor and a barometric pressure sensor, which are disposed on the takeoff and landing plane 101, within the takeoff and landing layer 10, and on the side of the takeoff and landing layer 10 facing the barometric pressure control layer 20. The wind speed sensor detects wind speed, and the barometric pressure sensor detects barometric pressure. The wind speed sensor and barometric pressure sensor are distributed throughout the takeoff and landing layer 10, allowing the barometric pressure control layer 20 to obtain comprehensive airflow information, which helps improve the accuracy of barometric pressure control at the takeoff and landing plane 101.

[0038] In one embodiment, such as Figure 1 and Figure 4 As shown, the air pressure regulation layer 20 includes an air pressure regulation module 21 and an air pressure regulation actuator 22. The air pressure regulation actuator 22 is used to provide the air pressure required during the takeoff and landing of the aircraft. The air pressure regulation module 21 is used to control the air pressure regulation actuator 22 based on the air pressure information at the takeoff and landing plane. The air pressure regulation actuator 22 can generate and adjust the airflow, increasing or decreasing the air pressure at the takeoff and landing plane 101 according to actual needs, creating a stable takeoff and landing air pressure environment for the aircraft. The air pressure regulation module 21 can perform data analysis and processing on the collected air pressure information, calculate the most suitable air pressure regulation strategy, and achieve dynamic adjustment of the air pressure at the takeoff and landing plane 101 through precise control of the air pressure regulation actuator 22.

[0039] In one embodiment, the air pressure regulation actuator 22 includes multiple dispersed fans 221, and the air pressure regulation module 21 is used to regulate the operating status of the fans 221. The dispersed arrangement of the fans 221 can ensure that the air pressure at the takeoff and landing plane 101 is uniformly regulated, avoiding excessively high or low local air pressure, and providing a stable takeoff and landing environment for the aircraft. At the same time, the air pressure regulation module 21 can adjust the speed and deflection angle of one or more fans as needed to achieve fine-tuning of the air pressure in specific areas of the takeoff and landing plane 101, which helps to cope with complex and changing environmental conditions.

[0040] In one embodiment, when the take-off and landing platform 100 carries a quadcopter, it can be equipped with 4 to 8 fans 221; when the take-off and landing platform 100 carries a hexacopter, it can be equipped with 6 to 12 fans 221.

[0041] This application embodiment also provides a method for air pressure control in the airspace near a take-off and landing platform. The air pressure control method is used to control the air pressure at the take-off and landing plane 101 of the aforementioned take-off and landing platform 100. The air pressure control method includes:

[0042] Step 410: Collect airflow information at the takeoff and landing plane 101 during aircraft takeoff and landing.

[0043] Step 420: Based on the flight dynamics model of the aircraft and the airflow information, obtain the air pressure range that satisfies the flight stability of the aircraft, and derive the optimal air pressure value within the air pressure range.

[0044] Step 430: Adjust the air pressure at the take-off and landing plane 101 to the optimal air pressure value.

[0045] In one embodiment, prior to step 430, the control method further includes the steps of: obtaining an ideal aerodynamic model of the take-off and landing platform 100 at the take-off and landing plane in an undeformed state, and performing error identification based on the ideal aerodynamic model to obtain a real-time aerodynamic model at the take-off and landing plane, and calculating a control scheme by which the pressure control layer adjusts the air pressure at the take-off and landing plane 101 to the optimal air pressure value based on the difference between the real-time aerodynamic model and the ideal aerodynamic model.

[0046] Furthermore, the control method also includes the step of: correcting the ideal aerodynamic model of the take-off and landing platform 100 at the take-off and landing plane 101 in an undeformed state based on external disturbances.

[0047] Specifically, in step 410, the sensor 30 can collect data in real time.

[0048] Wind speed and air pressure information x(t) at the descending plane 101.

[0049] In step 420, sensor 30 transmits wind speed and air pressure information x(t) to air pressure control module 21, and the flight dynamics model of the aircraft is as follows: Where X(t) represents the real-time state of the aircraft, F(·) represents the dynamic equation of the aircraft, and the air pressure control module 21 calculates the air pressure range x that satisfies the flight stability of the aircraft based on the flight dynamic model of the aircraft. Ω The optimal air pressure value x was calculated based on the convex optimization algorithm. d (t).

[0050] Obtain the ideal aerodynamic model of the take-off and landing platform 100 at the take-off and landing plane in a non-deformed state. Because the takeoff and landing platform is subject to external uncertainties such as aircraft compression, the ideal aerodynamic model of the takeoff and landing platform 100 at the takeoff and landing plane in a non-deformed state is modified as follows:

[0051] For the uncertainties related to the system state x(t), a neural network is used for estimation. The specific estimation process is Δf(x(t)) + Δg(x(t))u(t) = W T φ(x(t))+∈, where W is the optimal neural network weight value, and ∈ is a Euclidean norm bounded vector. Thus, an extended observer based on the neural network can be constructed to estimate the real-time aerodynamic model of the takeoff and landing platform. The estimation method is as follows: in For real-time estimation of x(t); To estimate the error for the real-time model; It is an estimate of the expected weight values ​​W of the neural network; This is an estimate of the external disturbance w(t), where k1 is a positive definite diagonal matrix. To ensure the accuracy of the model identification, it is necessary to ensure... It is convergent and bounded, therefore the design Real-time update rate Where γ1>0 and γ2≥0; Real-time update rate k2 is a positive definite diagonal matrix.

[0052] The goal of pressure control is to make x(t) approximate x as closely as possible. d (t), therefore the real-time control error of air pressure is δ x (t)=x(t)-x d (t), for the loss function Calculations show that u satisfies * =argmin(Δ c The optimal air pressure control scheme u * , where u(t) includes the fan's deflection angle and rotation speed.

[0053] In step 430, the deflection angle and speed of the fan 221 of the pneumatic pressure regulating actuator 22 are controlled according to the deflection angle and speed information of the fan blades contained in u(t).

[0054] It should be noted that the technical solutions or features described in the above embodiments can be combined or supplemented with each other without conflict. The scope of protection of this application is not limited to the precise structures described in the above embodiments and shown in the accompanying drawings; all modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the scope of protection of this application.

Claims

1. A take-off and landing platform for an aircraft, characterized in that, The take-off and landing platform (100) includes: The take-off and landing layer (10) includes a take-off and landing plane (101) for carrying aircraft; the take-off and landing layer (10) is provided with a plurality of dispersed ventilation holes (102), which are used to dynamically guide the turbulence generated by the take-off and landing activities of the aircraft above the take-off and landing plane (101) according to the pressure difference generated by the pressure control layer (20), thereby reducing the ground effect; The air pressure control layer (20) is located on the side of the take-off and landing plane (101) away from the take-off and landing layer (10). It is used to control the air pressure at the take-off and landing plane (101) to reduce the air pressure fluctuation caused by the ground effect during the take-off and landing of the aircraft. The air pressure control layer (20) includes an air pressure control module (21) and an air pressure control actuator (22). The air pressure control module (21) is used to obtain the air pressure range that meets the flight stability of the aircraft based on the flight dynamics model of the aircraft and the collected airflow information at the take-off and landing plane (101), and to obtain the optimal air pressure value within the air pressure range. The air pressure control actuator (22) is used to adjust the air pressure at the take-off and landing plane (101) to the optimal air pressure value under the control of the air pressure control module (21).

2. The take-off and landing platform according to claim 1, characterized in that, The air pressure regulating actuator (22) includes multiple fans (221) arranged in a dispersed manner, and the air pressure regulating module (21) is used to regulate the operating status of the fans (221).

3. The take-off and landing platform according to claim 1, characterized in that, The take-off and landing platform (100) also includes multiple sensors (30), which are evenly arranged on the take-off and landing layer (10). The sensors (30) are used to collect airflow information and transmit the airflow information to the air pressure control layer (20).

4. The take-off and landing platform according to claim 3, characterized in that, The sensor (30) includes a wind speed sensor and a barometric pressure sensor, which are disposed in the take-off and landing plane (101), the take-off and landing layer (10), and the side of the take-off and landing layer (10) facing the barometric pressure control layer (20).

5. The take-off and landing platform according to claim 4, characterized in that, The cross-section of the vent (102) is honeycomb-shaped.

6. A method for controlling air pressure in the airspace near a take-off and landing platform, used to control the air pressure at the take-off and landing plane (101) of the take-off and landing platform as described in any one of claims 1 to 5, characterized in that, The air pressure control method includes: Collect airflow information at the takeoff and landing plane (101) during aircraft takeoff and landing; Based on the flight dynamics model of the aircraft and the airflow information, the air pressure range that satisfies the flight stability of the aircraft is obtained, and the optimal air pressure value within the air pressure range is derived. The air pressure at the take-off and landing plane (101) is adjusted to the optimal air pressure value.

7. The air pressure control method according to claim 6, characterized in that, The control method further includes: obtaining an ideal aerodynamic model of the take-off and landing platform (100) at the take-off and landing plane (101) in an undeformed state, and performing error identification based on the ideal aerodynamic model to obtain a real-time aerodynamic model at the take-off and landing plane (101), and calculating a control scheme for the pressure control layer to adjust the air pressure at the take-off and landing plane (101) to the optimal air pressure value based on the difference between the real-time aerodynamic model and the ideal aerodynamic model.

8. The air pressure control method according to claim 7, characterized in that, Before the error identification based on the ideal aerodynamic model, the control method further includes: correcting the ideal aerodynamic model of the take-off and landing platform (100) at the take-off and landing plane (101) in an undeformed state based on external disturbances.

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