A method for determining a UAV release aerodynamic compatibility separation boundary

Abstract

The application belongs to the technical field of unmanned aerial vehicle (UAV) release design, and particularly relates to a method for determining a release aerodynamic compatibility separation boundary of an UAV, which is designed to determine a release window size for safe separation of the UAV in the air, and to calculate and determine a range of carrier state parameters for safe release of the UAV on the basis of clear judgment criteria for release aerodynamic compatibility of the UAV, so as to determine the release aerodynamic compatibility separation boundary of the UAV, reduce subjective influence of designers, avoid overdesign and underdesign, and lay a foundation for safe release of the UAV from a cabin in the air.

Description

Technical Field

[0001] This application belongs to the field of UAV deployment design technology, specifically relating to a method for determining the aerodynamic compatibility separation boundary of UAV deployment. Background Technology

[0002] When a drone is deployed from the fuselage of a carrier aircraft, if the aerodynamic compatibility parameters of the drone deployment are not designed properly, the deployed drone may be strongly affected by the wake of the carrier aircraft, affecting the stability of the drone control, or even causing the drone to lose control and collide with the carrier aircraft, damaging the fuselage structure.

[0003] The aerodynamic compatibility parameters for drone deployment refer to the characteristic parameters related to the coexistence and mutual tolerance of the carrier aircraft and the drone during drone deployment. These parameters are important factors affecting the safe deployment of drones from the carrier aircraft's cabin and directly determine the safety of drone deployment in the air. They mainly include the size of the deployment window and the carrier aircraft's status parameters.

[0004] The aerodynamic compatibility separation boundary for drone deployment refers to the range of aerodynamic compatibility parameters that ensure the safe deployment of drones. Currently, this is mostly determined through experience, which is highly subjective and can lead to over- or under-design.

[0005] This application is made in view of the aforementioned technical deficiencies.

[0006] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0007] The purpose of this application is to provide a method for determining the aerodynamic compatibility separation boundary of UAV deployment, so as to overcome or mitigate at least one of the known technical defects.

[0008] The technical solution of this application is:

[0009] A method for determining the aerodynamic compatibility separation boundary for UAV deployment includes:

[0010] Step 1: Based on the dimensions of the carrier aircraft and the drone, determine the size of the delivery window for safe separation during aerial deployment of the drone.

[0011] Set the initial deployment window size, including the heading dimension X, vertical dimension Y, and lateral dimension Z. Enlarge or reduce the size, calculate and analyze the impact of the carrier aircraft's wake on the aerodynamic characteristics of the UAV, and take the heading dimension X, vertical dimension Y, and lateral dimension Z corresponding to the time when the impact on the aerodynamic characteristics of the UAV is small as the deployment window size for safe separation of the UAV during aerial deployment.

[0012] Step 2: Determine the aerodynamic compatibility criteria for drone deployment:

[0013] The drone will not collide with any part of the carrier aircraft during deployment;

[0014] When the drone is deployed, its attitude changes are within a reasonable range and it is autonomously controllable.

[0015] Step 3: Based on the aerodynamic compatibility criteria for UAV deployment, determine the range of carrier aircraft state parameters for safe UAV deployment:

[0016] Assume that the state parameters of the UAV deployment remain unchanged, including velocity V′, pitch angle θ, and yaw angle ψ;

[0017] By changing the state parameters of the carrier aircraft, including speed V, angle of attack α, and sideslip angle β, the trajectory of the UAV deployment and its roll angle are calculated.

[0018] Check the trajectory of the drone deployment and its roll angle. If the drone deployment trajectory does not collide with the carrier aircraft and the attitude change is within a reasonable range, then mark the drone as safe to deploy; otherwise, mark the drone as unsafe to deploy.

[0019] Determine the range of angle of attack α and sideslip angle β that the UAV can safely deploy at different carrier speeds V.

[0020] According to at least one embodiment of this application, in the above-mentioned method for determining the aerodynamic compatibility separation boundary of UAV deployment, step one has a relatively small impact on the aerodynamic characteristics of the UAV, specifically, it has a relatively small impact on the changes in lift, drag, and pitch moment of the UAV.

[0021] According to at least one embodiment of this application, in the above-described method for determining the aerodynamic compatibility separation boundary of UAV deployment, step one has a relatively small impact on changes in UAV lift, drag, and pitch moment, specifically:

[0022] The impact on the lift of the UAV is no more than 3%, the impact on drag is no more than 5%, and the impact on pitch moment is no more than 5%.

[0023] According to at least one embodiment of this application, in the above-mentioned method for determining the aerodynamic compatibility separation boundary of UAV deployment, in step one, the deployment window size for safe separation of UAV deployment in the air is determined, specifically, the directional dimension X is 2.5 times the length of the UAV fuselage, the vertical dimension Z is 1 times the diameter of the carrier fuselage, and the lateral dimension Y is 1 times the diameter of the carrier fuselage.

[0024] According to at least one embodiment of this application, in the above-mentioned method for determining the aerodynamic compatibility separation boundary of UAV deployment, in step two, the attitude change of the UAV during deployment is within a reasonable range and can be autonomously controlled. Specifically, the roll angle change of the UAV during deployment does not exceed ±80°.

[0025] According to at least one embodiment of this application, in the above-described method for determining the aerodynamic compatibility separation boundary of UAV deployment, step three, determining the range of the angle of attack α and sideslip angle β for safe deployment of the UAV at different carrier speeds V, specifically involves:

[0026] Plot the combination of angle of attack α and sideslip angle β for different carrier speeds V. Connect the angle of attack α and sideslip angle β at the boundary between when the UAV can and cannot safely deploy. Connect the angle of attack α and sideslip angle β within the curve envelope to serve as the angle of attack α and sideslip angle β that the UAV can safely deploy.

[0027] This application has at least the following beneficial technical effects:

[0028] This paper provides a method for determining the aerodynamic compatibility separation boundary of UAV deployment. Based on determining the deployment window size for safe separation of UAV deployment in the air and clarifying the aerodynamic compatibility judgment criteria for UAV deployment, the method calculates and determines the range of carrier state parameters for safe UAV deployment. This method can reduce the influence of designers' subjectivity and avoid over-design and under-design, thus laying the foundation for the safe deployment of UAVs from inside the cabin in the air. Attached Figure Description

[0029] Figure 1 This is a flowchart of the method for determining the aerodynamic compatibility separation boundary of UAV deployment provided in the embodiments of this application;

[0030] Figure 2 This is a schematic diagram illustrating the range of angle of attack α and sideslip angle β that the UAV can safely deploy at different carrier speeds V, as provided in the embodiments of this application. Detailed Implementation

[0031] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0032] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0033] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0034] The following is in conjunction with the appendix Figures 1 to 2 This application will be described in further detail.

[0035] A method for determining the aerodynamic compatibility separation boundary for UAV deployment, such as Figure 1 As shown.

[0036] Step 1: Based on the dimensions of the carrier aircraft and the drone, determine the size of the delivery window for safe separation during aerial deployment of the drone.

[0037] The initial deployment window dimensions are set, including the directional dimension X, vertical dimension Y, and lateral dimension Z. The directional dimension X, vertical dimension Y, and lateral dimension Z are enlarged or reduced, and the impact of the carrier aircraft's wake on the aerodynamic characteristics of the UAV is calculated and analyzed. The directional dimension X, vertical dimension Y, and lateral dimension Z corresponding to the condition where the impact on the UAV's aerodynamic characteristics is small are selected. Specifically, the impact of the carrier aircraft's wake on the UAV's aerodynamic characteristics is small, meaning that the impact on the UAV's lift change is no more than 3%, the impact on drag change is no more than 5%, and the impact on pitch moment change is no more than 5%.

[0038] The heading dimension X of the launch window is usually 2.5 times the length of the UAV fuselage, the vertical dimension Z is usually 1 times the diameter of the carrier fuselage, and the lateral dimension Y has little impact on the aerodynamic characteristics of the UAV and is usually 1 times the diameter of the carrier fuselage.

[0039] In one specific embodiment, the diameter of the carrier aircraft is 4m, the length of the UAV fuselage is 5m, the heading dimension X of the launch window is 12.5m, the vertical dimension Z is 4m, and the lateral dimension Y is 4m.

[0040] Step 2: Determine the aerodynamic compatibility criteria for drone deployment.

[0041] The aerodynamic compatibility criteria for drone deployment can specifically include the following two points:

[0042] The drone will not collide with any part of the carrier aircraft during deployment;

[0043] When the drone is deployed, the attitude change is within a reasonable range and can be autonomously controlled. Specifically, it can be designed so that the roll angle change does not exceed ±80° when the drone is deployed.

[0044] Step 3: Based on the aerodynamic compatibility judgment criteria for UAV deployment, determine the range of carrier aircraft state parameters for safe UAV deployment.

[0045] Assume that the state parameters of the UAV deployment remain unchanged, including velocity V′, pitch angle θ, and yaw angle ψ;

[0046] By changing the state parameters of the carrier aircraft, including speed V, angle of attack α, and sideslip angle β, the trajectory of the UAV deployment and its roll angle are calculated.

[0047] Check the drone's deployment trajectory and roll angle. If the drone's deployment trajectory does not collide with the carrier aircraft, and the roll angle change does not exceed ±80°, then the drone is marked as safely deployed.

[0048] Otherwise, it will be marked as a drone that cannot be safely deployed;

[0049] To determine the range of pitch angles α and yaw angles β that the UAV can safely deploy at different carrier speeds V, please refer to the following:

[0050] Plot the combinations of angle of attack α and sideslip angle β for the carrier aircraft at different carrier speeds V. Use squares to mark the angles of attack α and sideslip angle β that the UAV can safely deploy, and circles to mark the angles of attack α and sideslip angle β that the UAV cannot safely deploy. Connect the angles of attack α and sideslip angle β at the boundary between safe and unsafe deployment. Then connect the angles of attack α and sideslip angle β within the curve envelope to represent the angles of attack α and sideslip angle β that the UAV can safely deploy. Figure 2 As shown.

[0051] The method for determining the aerodynamic compatibility separation boundary of UAV deployment disclosed in the above embodiments, based on determining the deployment window size for safe separation of UAV deployment in the air and clarifying the aerodynamic compatibility judgment criteria for UAV deployment, calculates and determines the range of carrier state parameters for safe deployment of UAV, thereby determining the aerodynamic compatibility separation boundary for UAV deployment. This method can reduce the influence of designers' subjectivity, avoid over-design and under-design, and lay the foundation for the safe deployment of UAVs from inside the cabin in the air.

[0052] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0053] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A method for determining the aerodynamic compatibility separation boundary for UAV deployment, characterized in that, include: Step 1: Based on the dimensions of the carrier aircraft and the drone, determine the size of the delivery window for safe separation during aerial deployment of the drone. Set the initial deployment window size, including the heading dimension X, vertical dimension Y, and lateral dimension Z. Enlarge or reduce the size, calculate and analyze the impact of the carrier aircraft's wake on the aerodynamic characteristics of the UAV, and take the heading dimension X, vertical dimension Y, and lateral dimension Z corresponding to the time when the impact on the aerodynamic characteristics of the UAV is small as the deployment window size for safe separation of the UAV during aerial deployment. Step 2: Determine the aerodynamic compatibility criteria for drone deployment: The drone will not collide with any part of the carrier aircraft during deployment; When the drone is deployed, its attitude changes are within a reasonable range and it is autonomous and controllable; Step 3: Based on the aerodynamic compatibility criteria for UAV deployment, determine the range of carrier aircraft state parameters for safe UAV deployment: Assuming the state parameters of the drone deployment remain constant, including speed Pitch angle Yaw angle ; Change the carrier's state parameters, including speed. Angle of attack Sideslip angle Calculate the trajectory of the drone deployment and its roll angle; Check the trajectory of the drone deployment and its roll angle. If the drone deployment trajectory does not collide with the carrier aircraft and the attitude change is within a reasonable range, then mark the drone as safe to deploy; otherwise, mark the drone as unsafe to deploy. Determine the speed of different carriers Below, the angle of attack at which the drone can be safely deployed. Sideslip angle Scope; In step one, the impact on the aerodynamic characteristics of the UAV is relatively small, specifically the impact on changes in lift, drag, and pitch moment. In step one, the impact on changes in lift, drag, and pitch moment of the UAV is relatively small, specifically: The impact on the lift of the UAV is no more than 3%, the impact on drag is no more than 5%, and the impact on pitch moment is no more than 5%.

2. The method for determining the aerodynamic compatibility separation boundary of UAV deployment according to claim 1, characterized in that, In step one, the dimensions of the launch window for safe separation of the UAV during aerial deployment are determined. Specifically, the heading dimension X is 2.5 times the length of the UAV fuselage, the vertical dimension Z is 1 times the diameter of the carrier fuselage, and the lateral dimension Y is 1 times the diameter of the carrier fuselage.

3. The method for determining the aerodynamic compatibility separation boundary of UAV deployment according to claim 1, characterized in that, In step two, when the drone is deployed, the attitude change is within a reasonable range and can be autonomously controlled. Specifically, when the drone is deployed, the roll angle change does not exceed ±80°.

4. The method for determining the aerodynamic compatibility separation boundary of UAV deployment according to claim 1, characterized in that, In step three, the different carrier speeds are determined. Below, the angle of attack at which the drone can be safely deployed. Sideslip angle The scope is as follows: Draw different carrier speeds Below, the angle of attack of the carrier aircraft Sideslip angle Combining and connecting drones at the angle of attack at the boundary where they can and cannot be safely deployed. Sideslip angle To connect the angles of attack within the envelope of the curve. Sideslip angle Angle of attack that enables the safe deployment of drones Sideslip angle .

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