A method and device for detecting aerodynamic characteristics of a fixed-wing target drone

Abstract

The present application relates to a kind of fixed-wing target aerodynamic characteristic detection method and device, comprising: support part, the support part is used to fixedly connect the whole machine to be measured;Base is fixed in test site, and is connected with support part by a plurality of movable pieces arranged horizontally, the movable piece can at least feedback bearing capacity information.The detection device provided by the present application can obtain a plurality of parameters related to aerodynamic characteristics during the whole machine test process by the force feedback of a plurality of movable pieces, and at the same time, the movable nature of movable piece itself can ensure that the force in the air field during the whole machine test can automatically move, so as to visualize the test result.

Description

TECHNICAL FIELD

[0001] The present application relates to unmanned aerial vehicle testing equipment, in particular to a fixed-wing target drone aerodynamic characteristic detection method and device. BACKGROUND

[0002] In order to simulate the attack target more realistically, the target drone usually needs to have some specific maneuvering performance, so as to make various different flight trajectories and attitudes.

[0003] At present, in the prior art, for the aerodynamic performance test of the fixed-wing target drone, the traditional method is still used, that is, the wings and rudders are placed in the wind tunnel for force test, so as to obtain the related data such as lift and deflection force, or the whole machine is placed in the wind tunnel for test, so as to directly test the force condition of the whole machine in the airflow. The whole machine or the wing needs to be supported by a support, and this test method has certain limitations. First, the test result can only obtain a data of the force degree in the airflow, and the dynamic changes of the whole machine in the airflow, such as deflection and pitch activity, cannot be seen. In addition, in the test process, a plurality of force sensors need to be arranged on the support to detect the force conditions of the whole machine at multiple angles, so that the structure arrangement is relatively complex. SUMMARY

[0004] This section aims to summarize some aspects of the embodiments of the present application and briefly introduce some preferred embodiments. Some simplifications or omissions may be made in this section and the abstract and title of the specification to avoid obscuring the purpose of this section, abstract and title, and such simplifications or omissions cannot be used to limit the scope of the present application.

[0005] To solve the technical problems reflected in the background art, the present application provides the following technical solutions:

[0006] A fixed-wing target drone aerodynamic characteristic detection method, at least involving the following steps:

[0007] Arranging a plurality of force points on the target drone body, and testing the force information of the plurality of force points respectively;

[0008] Integrating the plurality of force information, and determining the state of the whole machine in combination with the positions of the force points.

[0009] As a preferred technical solution of the fixed-wing target drone aerodynamic characteristic detection method, the plurality of force points are distributed at different horizontal positions, and the force information includes longitudinal force information.

[0010] A fixed-wing target drone aerodynamic characteristic detection device is used to cooperate with the implementation of the above method, and comprises:

[0011] A support part is used to fixedly connect the whole machine to be tested.

[0012] The base is fixed to a test site and connected to the support part through a plurality of horizontally arranged movable members, which can at least feedback bearing force information.

[0013] As a preferred technical scheme of the fixed-wing target aircraft aerodynamic characteristic detection device, the movable member is provided with an extrusion cavity, the volume of which changes correspondingly during the movement of the movable member, and the extrusion cavity is connected to the pressure measuring chamber, and the pressure measuring chamber is provided with a pressure measuring element.

[0014] As a preferred technical scheme of the fixed-wing target aircraft aerodynamic characteristic detection device, the movable member includes a telescopic cylinder, and the two ends of the telescopic cylinder are movably connected to the support part and the base, respectively.

[0015] As a preferred technical scheme of the fixed-wing target aircraft aerodynamic characteristic detection device, the support part is provided with a plurality of horizontally distributed connection points, and each connection point is connected to a plurality of movable members.

[0016] As a preferred technical scheme of the fixed-wing target aircraft aerodynamic characteristic detection device, the pressure measuring chamber is at least four, and the pressure measuring chambers are connected in an on-off mode, and at least two of the pressure measuring chambers are provided with pressure measuring elements.

[0017] As a preferred technical scheme of the fixed-wing target aircraft aerodynamic characteristic detection device, the telescopic cylinder can at least maintain active movement and passive movement.

[0018] As a preferred technical scheme of the fixed-wing target aircraft aerodynamic characteristic detection device, the telescopic cylinder includes a cylinder and a plug rod in a sleeving mode, and the telescopic cylinder is provided with a magnetism and a magnetizing element.

[0019] The magnetism is arranged on the cylinder, and the magnetizing element is arranged on the plug rod; or

[0020] The magnetism is arranged on the plug rod, and the magnetizing element is arranged on the cylinder.

[0021] As a preferred technical scheme of the fixed-wing target aircraft aerodynamic characteristic detection device, the plug rod and the cylinder are elastically connected.

[0022] The fixed-wing target aircraft aerodynamic characteristic detection method and device provided by the application have the following beneficial effects:

[0023] 1 The detection method can simultaneously obtain a plurality of data such as lift and pitching characteristics by testing the forces of a plurality of different positions of the whole machine, and the dynamic change process of the whole machine can be obtained by the force changes of the plurality of different positions.

[0024] 2. The detection device of the present invention, by combining the method in this scheme, can obtain multiple parameters related to aerodynamic characteristics during the whole machine test process through the force feedback of multiple moving parts. At the same time, through the movable nature of the moving parts themselves, it can ensure that the whole machine can automatically move under the force in the air field during the test, thereby visualizing the test results. Attached Figure Description

[0025] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Wherein:

[0026] Figure 1 This is a schematic diagram of the detection method described in an embodiment of the present invention.

[0027] Figure 2 This is an overall diagram of the detection device described in an embodiment of the present invention.

[0028] Figure 3 For about Figure 2 Another perspective view of the structure shown.

[0029] Figure 4 for Figure 2 Top view of the structure shown.

[0030] Figure 5 for Figure 2 The diagram shows the effect of the device during actual testing.

[0031] Figure 6 for Figure 5 A frontal view of the structure shown.

[0032] Figure 7 for Figure 5 Side view of the structure shown.

[0033] Figure 8 This is a cross-sectional view of the telescopic cylinder described in an embodiment of the present invention.

[0034] Figure 9 This is a cross-sectional view of the internal structure of the base described in an embodiment of the present invention.

[0035] Figure 10 for Figure 9 The diagram shows the interaction between multiple pressure testing chambers.

[0036] Figure label:

[0037] 100. Base; 101. Base plate; 102. Pressure measuring chamber; 103. Connecting port; 200. Top plate; 300. Telescopic cylinder; 301. Cylinder barrel; 302. Plug rod; 303. Extrusion chamber; 400. Return spring; 500. Coil; 501. Permanent magnet. Detailed Implementation

[0038] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0039] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and those skilled in the art can make similar extensions without departing from the spirit of the invention. Therefore, the invention is not limited to the specific embodiments disclosed below.

[0040] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single or selective embodiment that is mutually exclusive with other embodiments.

[0041] Secondly, the present invention is described in detail with reference to the schematic diagrams. When detailing the embodiments of the present invention, for ease of explanation, the cross-sectional views illustrating the device structure may be partially enlarged, not according to the usual scale. Furthermore, the schematic diagrams are merely examples and should not limit the scope of protection of the present invention. In addition, actual fabrication should include three-dimensional spatial dimensions of length, width, and depth.

[0042] In traditional methods, when a target drone or model drone (hereinafter referred to as the whole machine) is placed in a wind field (usually provided by a wind tunnel), the whole machine is anchored in the wind field by support components. Force detection elements need to be configured on the support components at multiple angles, which makes the structure more complex. Furthermore, it can only perform static tests and cannot cooperate with the active movement of the whole machine, making the testing process unvisualizable.

[0043] Based on this, the first embodiment of the present invention provides a method for detecting the aerodynamic characteristics of a fixed-wing target drone, which is used to test the aerodynamic characteristics of a fixed-wing target drone. Compared with traditional detection methods, the process of this method is as follows:

[0044] During the test, at least three stress points are set on the entire machine, distributed horizontally at different locations. With the assistance of the equipment, each stress point can be individually tested vertically, and the testing is limited to a certain range of motion. Figure 1 As shown, the three stress points are referred to as D1, D2 and D3. D1 and D2 are symmetrically distributed on both sides of the machine, and D3 is located in the middle of the machine.

[0045] Based on the above, during the test, by adjusting the entire wing, when D1 and D2 are subjected to forces in different directions in the longitudinal direction, the overall in-flight roll level can be detected. The magnitude of the force difference between the two points can reflect the deflection angle during actual flight. Similarly, based on this principle, when the entire control wings are adjusted, the pitch performance of the entire aircraft can be determined by detecting the force difference between D1, D2, and D3. Therefore, by simultaneously detecting the sum of the forces on D1, D2, and D3, the overall lift level of the aircraft can be tested.

[0046] Furthermore, during the testing process, by utilizing the movable features of the three points—for example, by causing relative movement between D1 and D2 due to the forces acting on the entire machine, thus creating a height difference—the deflection of the entire machine during simulated steering can be visually displayed, achieving a visualization of the steering performance test results. Therefore, by observing the height difference between D1, D2, and D3, the pitch of the entire machine can be determined. When the wind speed changes, observing the rise and fall of the three points can reveal the lift obtained by the entire machine at different speeds, and this result can be visualized.

[0047] The test process listed above is only an explanation of the basic principles. In actual testing, by more precisely and continuously comparing the state differences and force differences between the three points, more test results can be obtained. For example, based on the rate of change of the force at each test point, the response speed of the whole machine's attitude change can be obtained, thus determining the overall maneuverability of the machine. Furthermore, by acquiring the force difference data between D1 and D2 and D3, the overall tilting situation of the machine can also be obtained.

[0048] Compared to existing methods, this method can obtain data on various maneuverability during the simulated flight of the whole aircraft by continuously conducting multiple flexible tests between multiple force points. Therefore, when configuring the corresponding test equipment, there is no need for too many force testing components, which simplifies the equipment. At the same time, by using the movable effect of multiple force points, some results in the test process can be visualized, so as to observe the state adjustment of the whole aircraft during the actual flight through simulated flight experiments.

[0049] Reference Figures 2-10 This is a second embodiment of the present invention, which provides a fixed-wing target drone aerodynamic characteristic detection device to assist in the implementation of the detection method described in the above embodiments, such as... Figures 2-4As shown, the device includes a base for fixing in the wind farm, which consists of a base 100 and a base plate 101 fixed together. It also includes a support for fixing the entire unit. The support is a top plate 200, which is connected to the base plate 101 via multiple telescopic cylinders 300. The two ends of each telescopic cylinder 300 are universally connected to the top plate 200 and the base plate 101, respectively. There are six telescopic cylinders 300. The tops of every two adjacent telescopic cylinders 300 are close together and connected to the same point on the top plate 200. This point can be understood as the stress point in Embodiment 1. There are three such points, distributed as follows: Figure 3 As shown, furthermore, the bottoms of each pair of adjacent telescopic cylinders 300 are also close to each other and are connected to the same point on the bottom plate 101. There are three such points in total, and they are distributed in a ring array to ensure the stability of the entire device.

[0050] The above-described distribution design of the telescopic cylinders 300 gives the entire structure triangular stability, thereby ensuring the stability of the top plate 200. The telescopic cylinders 300 can be elastically stretched or elastically compressed. When not subjected to external force, their length is fixed under normal conditions. That is, when not subjected to tension or excessive compression, their length remains unchanged, so that the top plate 200 is normally in a horizontal state.

[0051] Furthermore, as shown in Figure 9, the base 100 internally contains at least four pressure measuring chambers 102. Each pair of adjacent pressure measuring chambers 102 is interconnected via a connecting port 103. Each connecting port 103 is equipped with an electrically controllable gate valve assembly (its structure is omitted in the figure). This allows each connecting port 103 to be opened and closed independently, thereby achieving communication and isolation between adjacent pressure measuring chambers 102. Regarding the telescopic cylinder 300, as... Figure 8 As shown, it consists of a matching cylinder 301 and a piston rod 302, with a compression chamber 303 formed between them. The compression chamber 303 is connected to one of the pressure measuring chambers 102. A return spring 400 is also connected between the piston rod 302 and the inner bottom wall of the cylinder 301, so that the telescopic cylinder 300 as a whole maintains a fixed length in normal conditions.

[0052] like Figures 5 to 7 As shown, when the entire device is used in conjunction with the main unit for testing, several support rods are pre-installed at the bottom of the main unit used for testing. The bottom of the support rods is fixedly connected to the top plate 200, thereby keeping the main unit fixed on the top plate 200. The movement of the top plate 200 can represent the movement of the main unit during the testing process; specifically, as shown... Figure 4 As shown, the top of the top plate 200 has a positioning arrow. When the entire unit is fixed, the direction of the unit's head is consistent with the direction of this arrow, and the arrow direction is consistent with the windward direction in the wind field. Figure 4As shown, the six telescopic cylinders 300 are hereby abbreviated as S1, S2, S3, S4, S5, and S6, as follows: Figure 10 As shown, the four pressure measuring chambers 102 are referred to as C1, C2, C3 and C4 respectively. Specifically, the compression chambers 303 in S1 and S2 are connected to the air path of C1, the compression chamber 303 in S3 is connected to the air path of C4, the compression chamber 303 in S4 is connected to the air path of C3, and the compression chambers 303 in S5 and S6 are connected to the air path of C2 (the structure of the air pipeline is omitted in the figure). At least C1 and C3 are also equipped with pressure sensors (the specific structure of which is omitted in the figure), which are referred to as Y1 and Y2 respectively.

[0053] Based on the above, during testing, in accordance with the principle of Example 1, different stress states are formed by the various attitude adjustments made by the whole machine in the wind field:

[0054] For example, when testing the overall steering performance of the machine, maintain communication between C1 and C4, and between C2 and C3; isolate C1 and C2, and isolate C3 and C4. For instance, when the machine is... Figure 6 When the viewpoint shows a tendency to tilt to the right, the stretching of S1, S2, and S3 is greater than that of S6, S5, and S4 on the other side. This results in the pressure in C1 and C4 being less than the pressure in C2 and C3. At this time, the pressure value measured by Y1 is less than the pressure value measured by Y2. Therefore, based on the difference between the two values ​​and the rate of change, the steering tilt angle of the whole machine and the corresponding speed when the steering posture is made can be roughly determined, thereby obtaining the maneuverability characteristics in terms of steering.

[0055] When C1 and C2 are interconnected, C4 and C3 are interconnected, C1 and C4 are isolated, and C2 and C3 are isolated, for example, when the whole machine is currently... Figure 7 When the viewpoint deflects to the right, the air pressure values ​​in C4 and C3 are less than the air pressure values ​​in C1 and C2, making the air pressure value measured by Y2 less than the air pressure value measured by Y1. Therefore, the pitch characteristics of the entire aircraft can be detected using the same method as above.

[0056] When C1 is kept isolated and C2, C3 and C4 are interconnected, the oblique deflection characteristics of the whole machine can be obtained based on the detection results between Y1 and Y2 using the same principle.

[0057] When all four pressure measuring chambers 102 are interconnected, the lift level of the entire machine can be determined by acquiring the detection values ​​of Y1 or Y2. At this time, the airflow between the multiple pressure measuring chambers 102 can flow to each other, so that when the entire machine is subjected to deflection force in the air field, it can directly squeeze the telescopic cylinder 300 located on the deflection side, and at the same time stretch the telescopic cylinder 300 on the other side, so that the entire machine can directly perform deflection activities, thereby visually displaying the testing process.

[0058] As can be seen from the above process, the detection device of the present invention does not have a more complex structure compared with the prior art, and only needs to be set with at least two pressure sensors, so as to complete the performance test process of multiple motion angles of the whole machine foundation in conjunction with four pressure measuring chambers 102. At the same time, it can also visualize the activity process of the whole machine in the wind field, which satisfies the static test requirements and can also be dynamically displayed.

[0059] Furthermore, such as Figure 8 As shown, the cylinder 301 of the telescopic cylinder 300 is also equipped with a coil 500 coaxial with itself, and the end of the piston rod 302 is also equipped with a ring-shaped permanent magnet 501. By applying an electrical signal to the coil 500, it is energized, thereby driving the piston rod 302 to move automatically on the cylinder 301. This configuration allows the telescopic cylinder 300 to move actively, so that the movement of the top plate 200 can be automatically controlled during the detection process, thereby driving the whole machine to actively adjust its attitude in the wind field. Thus, with human intervention, the whole machine can be adjusted to the deflection angle that simulates actual flight. This function can be used to observe whether the smoke line of the whole machine is smooth under different attitudes during flow field display tests, thus taking into account the analysis process of flow characteristics under complex conditions such as large angle of attack.

[0060] The testing device provided by this invention is not only suitable for testing fixed-wing target drones, but can also be appropriately used for testing other types of aircraft, such as lift testing of ordinary drones. Therefore, the application scenarios of this testing device are not limited to the testing processes listed in the embodiments, which makes this device have a wider range of applications.

[0061] It should be understood that numerous specific implementation decisions can be made during the development of any practical implementation, such as in any engineering or design project. Such development efforts may be complex and time-consuming, but for those skilled in the art who benefit from this disclosure, the development effort will be a routine work of design, manufacturing, and production without requiring much experimentation.

[0062] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A device for detecting the aerodynamic characteristics of a fixed-wing target drone, characterized in that: include: Support part, the support part is used to fix and connect the whole machine under test; The base is fixed to the test site and connected to the support through multiple horizontally arranged movable parts; There are multiple pressure testing chambers, which are connected in an on / off state, and at least two of the pressure testing chambers are equipped with pressure testing elements. The movable component has a compression chamber, the volume of which changes according to the movement of the movable component. Multiple compression chambers are configured to correspond to multiple pressure measuring chambers respectively, and any corresponding compression chamber and pressure measuring chamber are kept in communication.

2. The aerodynamic characteristic detection device for a fixed-wing target drone according to claim 1, characterized in that: The movable component includes a telescopic cylinder, with both ends being movably connected to the support portion and the base, respectively.

3. The aerodynamic characteristic detection device for a fixed-wing target drone according to claim 2, characterized in that: The support has at least a plurality of horizontally distributed connection points, and each of the connection points is connected to a plurality of movable parts.

4. The aerodynamic characteristic detection device for a fixed-wing target drone according to claim 3, characterized in that: There are at least four pressure testing chambers.

5. The aerodynamic characteristic detection device for a fixed-wing target drone according to claim 4, characterized in that: The telescopic cylinder can maintain at least both active and passive movement.

6. The aerodynamic characteristic detection device for a fixed-wing target drone according to claim 5, characterized in that: It also includes an excitation element, and the telescopic cylinder includes a cylinder barrel and a piston rod that are fitted together, and: The cylinder is equipped with a permanent magnet, and the excitation element is mounted on the piston rod; or The piston rod is equipped with a permanent magnet, and the excitation element is mounted on the cylinder.

7. The aerodynamic characteristic detection device for a fixed-wing target drone according to claim 6, characterized in that: The piston rod and the cylinder are kept in an elastic connection.

Images