An unmanned aerial vehicle ground test platform and a ground test method

Abstract

This application belongs to a test platform. Aiming at the problems of single test function and insufficient verification ability existing in the current ground test device for vertical takeoff and landing unmanned aerial vehicles, a ground test platform for unmanned aerial vehicles and a ground test method are provided, which include an incoming flow wind speed regulating intake section, a test section, and an incoming flow wind speed regulating exhaust section that are coaxially connected and communicated in sequence. The incoming flow wind speed regulating intake section is also sequentially provided with a heat exchange section and an environment simulation section. A force measuring bench and a lifting floor are arranged in the test section. The incoming flow wind speed regulating exhaust section is used to provide power for the axial movement of the air flow, so that the air flow forms a flow field in the test section and the air flow is discharged through the exhaust end. The incoming flow wind speed regulating intake section, the test section, and the incoming flow wind speed regulating exhaust section jointly form a pipeline capable of regulating the incoming flow wind speed, realizing the aerodynamic simulation during the flight of the unmanned aerial vehicle, and capable of realizing various aerodynamic test functions such as the hover force measuring test, forward flight force measuring test, and ground effect test of the unmanned aerial vehicle, and simulating various meteorological conditions.

Description

Technical Field

[0001] The present application relates to a test platform, and specifically to an unmanned aerial vehicle ground test platform and a ground test method. Background Art

[0002] With the rapid development of the low-altitude economy, the UAV industry has ushered in unprecedented development opportunities, especially various types of UAVs with vertical take-off and landing capabilities. Based on their excellent low-altitude and low-speed performance, strong maneuverability, and good site adaptability, they are widely used in agriculture, forestry, surveying and mapping, electricity, environmental protection, fire fighting and other industries, and have broad prospects.

[0003] At present, drones with vertical take-off and landing capabilities mainly include the following types: multi-rotor drones, unmanned helicopters, composite wing drones, coaxial twin-rotor drones, tandem twin-rotor drones, tilt-rotor drones, etc. Although these drones have made great technological progress, their performance is poor in severe weather conditions, which is specifically manifested in their insufficient ability to perform tasks around the clock. Therefore, various types of vertical take-off and landing drones need to undergo a large number of ground tests during the research and development process to fully verify whether all aspects of the drone's performance meet the design requirements. However, existing drone ground test equipment generally only considers verifying the drone's aerodynamic performance, without considering the complex environmental assessment issues faced by drones during their service life. The test function is relatively single and the verification capability is insufficient. Summary of the invention

[0004] In order to solve the technical problems that the current vertical take-off and landing UAV ground test equipment has a single test function and insufficient verification capability, the present application provides a UAV ground test platform and a ground test method.

[0005] In order to achieve the above objectives, this application adopts the following technical solutions:

[0006] In a first aspect, the present application proposes a UAV ground test platform, comprising an incoming wind speed regulating air intake, a test section, and an incoming wind speed regulating exhaust section, which are coaxially connected and connected in sequence; the incoming wind speed regulating air intake, the test section, and the incoming wind speed regulating exhaust section jointly form a pipeline capable of regulating the incoming wind speed, the inlet of the incoming wind speed regulating air intake section is an air intake end, and the outlet of the incoming wind speed regulating exhaust section is an exhaust end;

[0007] The incoming wind speed regulating air inlet is also provided with a heat exchange section and an environment simulation section in sequence; the heat exchange section is used to cool or heat the airflow in the incoming wind speed regulating air inlet, and the environment simulation section is used to provide a variety of meteorological environments for the airflow in the incoming wind speed regulating air inlet;

[0008] A force measuring bench and a lifting floor are arranged in the test section. The force measuring bench passes through the lifting floor and is used for parking an unmanned aerial vehicle (UAV) and testing the aerodynamic performance of the UAV. The lifting floor is used for adjusting the height of the UAV from the ground. A variety of meteorological simulation systems are arranged at the top of the force measuring bench in the test section.

[0009] The incoming flow wind speed regulating exhaust section is used to provide power for the axial movement of the air flow, so that the air flow establishes a flow field in the test section and is discharged through the exhaust end.

[0010] Further, the incoming flow wind speed regulating intake section includes an air suction section, a rectifying section, and a contraction section arranged in sequence from the intake end.

[0011] The heat exchange section is located between the air suction section and the rectifying section, and the environment simulation section is located between the rectifying section and the contraction section. The air suction section, the heat exchange section, the rectifying section, the environment simulation section, and the contraction section are coaxially connected and communicate with each other.

[0012] The large end of the air suction section is close to the intake end, and the large end of the contraction section is close to the intake end.

[0013] Further, the incoming flow wind speed regulating exhaust section includes a diffuser section, a power section, and an exhaust section that are coaxially connected and communicate with each other in sequence from the intake end.

[0014] The small end of the diffuser section is close to the intake end, and the small end of the exhaust section is close to the intake end.

[0015] The power section is used to suck the air flow in the air suction section into the test section.

[0016] Further, the profile curve of the contraction section along the axial direction conforms to:

[0017]

[0018] wherein, R 2 is the radius of the outlet of the contraction section, R is the radius of the cross-section at the axial distance x from the inlet of the contraction section, C is the contraction ratio, x is the axial distance from the inlet of the contraction section, and L is the length of the contraction section.

[0019] Further, the diffusion angles of both the diffuser section and the exhaust section are 5°.

[0020] Further, multiple layers of damping nets are installed axially in the rectifying section.

[0021] Further, one or more of a detachable rain blowing system, a snow blowing system, and a spraying system are arranged in the environment simulation section.

[0022] The variety of meteorological simulation systems include one or more of a sunshine system, a rainfall system, and a snowfall system.

[0023] Furthermore, the overall shape of the air intake section is trumpet-shaped, and a first protective net for preventing foreign objects from entering is installed at the entrance of the air intake section;

[0024] A second protective net for preventing foreign objects from entering is installed at the outlet of the exhaust section.

[0025] Furthermore, the exterior of the test section is covered with heat-insulating material;

[0026] A fan system is arranged inside the power section.

[0027] In a second aspect, the present application provides a test method for the above-mentioned unmanned aerial vehicle ground test platform, including:

[0028] Making the gas enter from the intake end of the incoming flow wind speed regulating intake section, adjusting the air flow to the required temperature range through the heat exchange section, and applying corresponding meteorological conditions to the air flow through the environmental simulation section, and then sending the air flow into the test section; at the same time, the incoming flow wind speed regulating exhaust section provides power for the axial movement of the air flow, enabling the air flow to establish a flow field in the test section and discharging the air flow through the exhaust end;

[0029] Adjusting the unmanned aerial vehicle to the target height above the ground through the lifting floor, providing the target meteorology for the test section with the aid of a variety of meteorological simulation systems, and testing the aerodynamic performance of the unmanned aerial vehicle through the force measuring bench.

[0030] Compared with the prior art, the present application has the following beneficial effects:

[0031] The present application provides an unmanned aerial vehicle ground test platform, including an incoming flow wind speed regulating intake section, a test section, and an incoming flow wind speed regulating exhaust section that are coaxially connected and communicated in sequence. The incoming flow wind speed regulating intake section is also sequentially provided with a heat exchange section and an environmental simulation section. A force measuring bench and a lifting floor are arranged in the test section. The incoming flow wind speed regulating exhaust section is used to provide power for the axial movement of the air flow, enabling the air flow to establish a flow field in the test section and discharging the air flow through the exhaust end. The incoming flow wind speed regulating intake section, the test section, and the incoming flow wind speed regulating exhaust section jointly form a pipeline capable of regulating the incoming flow wind speed, realizing the aerodynamic simulation during the flight of the unmanned aerial vehicle. Through the unique design of installing a force measuring bench and a lifting floor inside the test section, various aerodynamic test functions such as the hovering force measuring test, forward flight force measuring test, and ground effect test of the unmanned aerial vehicle are realized, solving the problem that the functions of the existing unmanned aerial vehicle ground test device are relatively single. At the same time, with the aid of the heat exchange section, a low-temperature or high-temperature environment can be provided, and various meteorological environment conditions faced during the forward flight of the unmanned aerial vehicle can be provided through the environmental simulation section. The various meteorological simulation systems arranged in the test section can also provide various meteorological conditions for the unmanned aerial vehicle. Combined with the lifting floor, the problem that the existing unmanned aerial vehicle ground test device has insufficient ability to assess and verify the complex environment faced during the service life of the unmanned aerial vehicle is solved.

[0032] The present application also proposes a method for ground testing of an unmanned aerial vehicle (UAV), which is based on the above-mentioned UAV ground test platform and has all the advantages of the above-mentioned UAV ground test platform. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the accompanying drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present application and should not be regarded as limiting the scope. For those of ordinary skill in the art, without creative efforts, other related drawings can also be obtained based on these drawings.

[0034] Figure 1 It is a schematic diagram of a UAV ground test platform of the present application;

[0035] Figure 2 It is a schematic diagram of the contraction section in the embodiment of the present application.

[0036] Wherein: 1 - suction section, 2 - heat exchange section, 3 - rectification section, 4 - environmental simulation section, 5 - contraction section, 6 - test section, 7 - heat insulation material, 8 - sunlight system, 9 - rainfall system, 10 - snowfall system, 11 - UAV, 12 - diffusion section, 13 - power section, 14 - exhaust section, 15 - first protective net, 16 - heat exchanger, 17 - damping net, 18 - rain blowing system, 19 - snow blowing system, 20 - spraying system, 21 - screw lift, 22 - lift floor, 23 - force sensor, 24 - force measuring bench, 25 - fan, 26 - support web, 27 - fairing, 28 - second protective net. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0037] To make the objectives, technical solutions, and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are some, but not all, of the embodiments of the present application. Generally, the components of the embodiments of the present application described and illustrated in the drawings here can be arranged and designed in various different configurations.

[0038] Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the present application to be protected, but merely represents the selected embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of the present application.

[0039] It should be noted that similar reference numerals and letters indicate similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0040] In the description of the embodiments of the present application, it should be noted that if terms such as "upper", "lower", "horizontal", "inner", etc. are used to indicate the orientation or positional relationship, it is based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the inventive product is usually placed during use. This is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present application. In addition, terms such as "first", "second", etc. are only used for distinguishing descriptions and cannot be understood as indicating or implying relative importance.

[0041] In addition, if the term "horizontal" appears, it does not mean that the component is required to be absolutely horizontal, but it can be slightly inclined. For example, "horizontal" only means that its direction is more horizontal relative to "vertical", and it does not mean that the structure must be completely horizontal, but it can be slightly inclined.

[0042] In the description of the embodiments of the present application, it should also be noted that unless otherwise clearly specified and limited, if terms such as "set", "installed", "connected", "linked" are used, they should be understood in a broad sense. For example, it 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 directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0043] A vertical takeoff and landing unmanned aerial vehicle (VTOL UAV) is a UAV with a unique design concept, combining the advantages of fixed-wing UAVs and multi-rotor UAVs. It can take off and land vertically and cruise quickly horizontally. Therefore, it can take off and land without a runway, thus being suitable for flight missions in various complex environments.

[0044] The ground test device for vertical takeoff and landing unmanned aerial vehicles is an important equipment for testing the performance and functions of VTOL UAVs. The main purpose is to ensure that the UAV can meet the design requirements and safety standards before formal flight. The ground test device can conduct performance tests, function verification, fault troubleshooting, and data collection and analysis.

[0045] At present, the core function of the ground test device is to simulate the flight state and test the aerodynamic parameters of the UAV, such as lift, drag, stability, etc. These tests are crucial for the design and optimization of the UAV. Although aerodynamic performance is fundamental, the UAV also needs to face various complex environments in actual applications, such as high temperature, low temperature, high humidity, dust, salt fog, etc. However, the existing ground test devices have deficiencies in simulating these environments. In addition, the service life of the UAV may be as long as several years or even a decade, during which it will undergo multiple maintenance, upgrades, and modifications. The ground test device has limited ability to evaluate the long-term service performance of the UAV.

[0046] Based on the above situation, this application proposes a UAV ground test platform and a ground test method. The following will describe this application in detail in combination with the embodiments and the drawings.

[0047] As the first embodiment of a UAV ground test platform in this application, it may include an incoming flow wind speed regulating intake section, a test section 6, and an incoming flow wind speed regulating exhaust section that are sequentially coaxially connected and communicated; the incoming flow wind speed regulating intake section, the test section 6, and the incoming flow wind speed regulating exhaust section jointly form a pipeline capable of regulating the incoming flow wind speed. The inlet of the incoming flow wind speed regulating intake section is the intake end, and the outlet of the incoming flow wind speed regulating exhaust section is the exhaust end. In actual application, the gas enters the ground test platform through the intake end of the inlet of the incoming flow wind speed regulating intake section, flows out through the exhaust end of the outlet of the incoming flow wind speed regulating exhaust section, the air flow passes through the test section 6, and the UAV 11 conducts the required tests in the test section 6.

[0048] The incoming flow wind speed regulating intake section is also sequentially provided with a heat exchange section 2 and an environment simulation section 4. The heat exchange section 2 is used to cool or heat the air flow in the incoming flow wind speed regulating intake section, and the environment simulation section 4 is used to provide various meteorological environments for the air flow in the incoming flow wind speed regulating intake section. It should be noted that the specific structural form of the heat exchange section 2 can be adjusted according to actual design needs, and this application does not make restrictions as long as it can regulate the temperature of the air flow in the incoming flow wind speed regulating intake section. The purpose is to adjust the gas in the incoming flow wind speed regulating intake section to a low temperature or high temperature state according to the test requirements, or it can also be adjusted to the temperature range required by the test to meet the corresponding test requirements. The environment simulation section 4 can provide corresponding meteorological environments for the air flow in the incoming flow wind speed regulating intake section. For example, it can simulate real meteorological environments such as rain, frost, freezing, etc., and can realize the switching of various meteorological environments according to test requirements.

[0049] The test section 6 is provided with a force measuring bench 24 and a lifting floor 22. The force measuring bench 24 passes through the lifting floor and is used to park the unmanned aerial vehicle 11 and test the aerodynamic performance of the unmanned aerial vehicle. The lifting floor 22 is used to adjust the height of the unmanned aerial vehicle 11 from the ground. A variety of meteorological simulation systems are provided at the top of the force measuring bench 24 within the test section 6. It should be noted that the force measuring bench 24 is a key device for testing the aerodynamic performance of the unmanned aerial vehicle, which can simulate various force conditions of the unmanned aerial vehicle 11 during flight, and can accurately measure parameters such as the tension, torque, and rotational speed of key components such as the motor and propeller of the unmanned aerial vehicle, so as to evaluate the performance parameters of the unmanned aerial vehicle 11 and optimize the corresponding design scheme. In other embodiments of the present application, the force measuring bench can also support real-time dynamic testing, simulate the dynamic force conditions of the unmanned aerial vehicle 11 during flight, and provide strong support for the dynamic performance evaluation of the unmanned aerial vehicle 11. It should also be noted that the lifting power structure of the lifting floor 22 can also be adjusted according to actual design needs, and any existing lifting method can be adopted as long as it can cooperate with the force measuring bench 24 to adjust the height of the unmanned aerial vehicle 11 from the ground. The present application does not limit the specific structural form. As an example, the force measuring bench 24 can pass through the middle of the lifting floor 22, and a force sensor 23 is installed on the force measuring bench 24 to measure the aerodynamic force of the unmanned aerial vehicle 11 in the hovering or forward flow field. The lifting floor 22 realizes height adjustment through a screw lift 21 to measure the ground effect influence of the unmanned aerial vehicle 11 at different heights from the ground. Through this design, the problem of the relatively single function of the existing unmanned aerial vehicle ground test device is solved.

[0050] The oncoming flow wind speed regulating exhaust part is used to provide power for the axial movement of the air flow, so that the air flow establishes a flow field within the test section 6 and discharges the air flow through the exhaust end. It should be noted that the oncoming flow wind speed regulating exhaust part provides power near the exhaust end, so that the air flow flows out through the oncoming flow wind speed regulating intake part, the test section 6 and the oncoming flow wind speed regulating exhaust part, providing corresponding air flow conditions for the unmanned aerial vehicle ground test located within the test section 6 and establishing a flow field.

[0051] It should be noted that the unmanned aerial vehicle ground test platform of the present application can not only be used for testing the unmanned aerial vehicle 11 with vertical takeoff and landing capabilities, but also can test other unmanned aerial vehicles 11 that need to conduct ground tests, and can be applied according to the test requirements of the unmanned aerial vehicle 11. Through the coordinated cooperation of each component, the present application solves the problems of the single test function and insufficient verification ability of the existing unmanned aerial vehicle ground test device.

[0052] Such as Figure 1As shown in the figure, this is the second embodiment of a ground test platform for an unmanned aerial vehicle in this application, which may include an air intake section 1, a heat exchange section 2, a rectifying section 3, a multi-functional environmental simulation section 4, a contraction section 5, a test section 6, a diffuser section 12, a power section 13, and an exhaust section 14 that are coaxially connected and communicated in sequence. Specifically, a first protective net 15 may be installed at the inlet of the air intake section 1 to prevent foreign objects from being sucked into the ground test platform through the air inlet end of the air intake section 1. A heat exchanger may be installed inside the heat exchange section 2 to cool or heat the inhaled gas for the low-temperature or high-temperature environmental assessment test of the unmanned aerial vehicle 11. A multi-layer damping net 17 may be installed inside the rectifying section 3 to make the incoming flow uniform and improve the quality of the flow field. It should be noted that the number of layers of the damping net 17 can be determined according to the requirement of the flow uniformity effect. The damping net 17 can eliminate vortices and turbulence in the airflow in the rectifying section 3, making the airflow smoother. By arranging the multi-layer damping net 17, the airflow can be refined layer by layer, reducing the influence of eddy currents and turbulence, thereby improving the uniformity of the flow field. At least one of a rain blowing system 18, a snow blowing system 19, or a spraying system 20 may be installed inside the multi-functional environmental simulation section 4 according to the test requirements, corresponding to the horizontal rain blowing, horizontal snow blowing, or icing environmental assessment test during the forward flight of the unmanned aerial vehicle 11. When the heat exchanger 16 is in the refrigeration mode, the snow blowing system 19 can achieve the forward flight snow blowing test assessment of the unmanned aerial vehicle 11. When the heat exchanger 16 is in the refrigeration mode, the spraying system 20 can achieve the icing test assessment of the unmanned aerial vehicle 11. The rain blowing system 18 can achieve the forward flight rain blowing test assessment of the unmanned aerial vehicle 11. It should be noted that in other embodiments of this application, the test system can also be increased accordingly to provide a richer environmental simulation. The contraction section 5 is a replaceable section, and its function is to accelerate the airflow to obtain a flow field environment with a desired wind speed. In actual applications, the specific structural shape of the contraction section 5 can be adjusted accordingly. In some embodiments of this application, the following preferred structural design is adopted:

[0053] As Figure 2 shown, it is a schematic diagram of the contraction section 5. The cross-section of the contraction section 5 is circular, and the profile curve of the contraction section 5 along the axial direction is determined by the following formula:

[0054]

[0055] wherein, R 2 is the outlet radius of the contraction section 5, R is the cross-sectional radius at the axial distance x from the inlet of the contraction section 5, C is the contraction ratio, x is the axial distance from the inlet of the contraction section 5, and L is the length of the contraction section 5. In actual applications, the units of R 2 , R, x, and L as important parameters should be consistent. For example, the unit can be set to mm. C = (R 1 / 2 ) 2 , R 1 is the inlet radius of the contraction section. During actual calculation, the unit should be the same as that of R2 Unify.

[0056] The axial profile curve conforms to the above formula, and the curvature transition of the wall surface in the contraction section is relatively gentle. When the air flow accelerates in the contraction section, wall separation is not likely to occur, which can make the air flow velocity in the test section uniform and stable, and improve the flow field quality.

[0057] In this embodiment, the suction section 1, the heat exchange section 2, the rectification section 3, the multi-functional environmental simulation section 4 and the contraction section 5 together serve as the incoming flow velocity regulating intake part, and the diffuser section 12, the power section 13 and the exhaust section 14 together serve as the incoming flow velocity regulating exhaust part, combining into a pipeline with the ability to regulate the test incoming flow velocity, realizing the aerodynamic simulation during the flight of the unmanned aerial vehicle 11. Through the above structural design, the incoming flow velocity in the test section 6 can be determined by the following formula:

[0058]

[0059] Where, v 1 is the inlet air velocity of the contraction section 5, and v 2 is the incoming flow velocity of the test section 6. In actual calculation, the units of v 1 and v 2 need to be unified. For example, they can be unified to use m / s.

[0060] The test section 6 is the main place for the test of the unmanned aerial vehicle 11. The outside of the test section 6 can be sprayed with heat-insulating materials to reduce heat exchange and maintain the temperature inside the test section 6. Test equipment such as a force measuring bench 24, a lifting floor 22, a rainfall system 9, a snowfall system 10 and a sunshine system 8 are installed inside the test section 6, which are used to conduct the hovering, forward flight force measuring tests and ground effect tests of the unmanned aerial vehicle 11, as well as environmental assessment tests such as rainfall, snowfall and sunshine. Through this combination method, the problem that the existing ground test device for unmanned aerial vehicles lacks the ability to assess and verify the complex environment faced during the service life of unmanned aerial vehicles is solved.

[0061] In other embodiments of the present application, the rainfall system 9, the snowfall system 10 and the sunshine system 8, as the meteorological simulation system, can also be increased or decreased according to the test requirements. For example, adding a meteorological simulation system can provide more meteorological conditions for the test of the unmanned aerial vehicle 11.

[0062] The function of the diffuser section 12 is to decelerate and pressurize the air flow. A fan system can be installed inside the power section 13, and its function is to suck air from the suction section into the test section to establish a flow field. A second protective net 28 can be installed at the outlet of the exhaust section 14 to prevent foreign objects from entering the ground test platform through the exhaust end of the exhaust section 14. In practical applications, the fan system can include components such as a fan 25, a fairing 27, and a support web 26. The fan 25, as the core power component of the fan system, generates an air flow by rotating and drives the gas to flow from the suction section 1 into the test section 6. It is the key to establishing the flow field and can ensure that the gas enters the test section 6 at a certain speed and flow rate. The fairing 27 is installed at the outlet of the fan 25, and its main function is to straighten the air flow generated by the fan 25, reduce eddies and turbulence, make the air flow more stable and uniform, and contribute to improving the accuracy and reliability of the test. The support web 26 does not directly participate in the generation and straightening of the air flow, but plays an important supporting and fixing role in the fan system. The support web 26 firmly installs the fan 25 and other components inside the power section 13 to ensure the stability and safety of the entire system.

[0063] In some embodiments of the present application, the unmanned aerial vehicle ground test platform can be further optimized. The shape of the suction section 1 is a flared shape, and a first protective net 15 is installed at the inlet of the suction section 1. The material of the first protective net 15 is stainless steel, which can prevent foreign objects from being sucked in during the operation of the ground test platform. The material of the first protective net 15 can also be adjusted accordingly according to the gas conditions. Four layers of damping nets 17 are installed inside the rectifying section 3, and the material of the damping nets 17 can be stainless steel accordingly. The contraction section 5 can be integrally of a replaceable structure. Under the condition that the working conditions of the fan system are certain, by replacing the contraction section 5 with different contraction ratios, different incoming flow wind speed simulations can be achieved. The test section 6 can adopt a reinforced concrete structure, and an adiabatic material 7 is sprayed on the outside. The adiabatic material 7 is polyurethane foam to reduce the heat exchange between the test section and the external environment through the wall. The exhaust section 14 adopts an expanding pipe, and the diffusion angles of the diffuser section 12 and the exhaust section 14 are both 5°. A second protective net 28 is also installed at the outlet of the exhaust section 14, and the material of the second protective net 28 can correspondingly use stainless steel to prevent foreign objects from entering the ground test platform through the exhaust end of the exhaust section 14.

[0064] It should be noted that if the diffusion angle is too large, the air flow is prone to separation and the energy loss increases. If the diffusion angle is too small, a larger length is required to reach the same diffuser section outlet diameter, which will increase the length dimension and construction cost of the equipment. In this embodiment, the diffusion angle is set to 5°, which can ensure that the air flow is not easily separated when passing through the diffuser section, and the energy loss of the air flow passing through the diffuser section 12 is the smallest, while reasonably controlling the length of the diffuser section 12 so that it is not too long.

[0065] This application combines the intake section 1, the rectifying section 3, the contraction section 5, the test section 6, the diffuser section 12, the power section 13 and the exhaust section 14 to form a pipeline with the ability to adjust the test incoming flow velocity, realizing the aerodynamic simulation during the flight of the unmanned aerial vehicle 11. Through the unique design of installing a force measuring bench 24 and a lifting floor 22 at the inner bottom of the test section 6, various aerodynamic test functions such as the hovering force measuring test, the forward flight force measuring test and the ground effect test of the unmanned aerial vehicle 11 are realized, solving the problem that the functions of the existing unmanned aerial vehicle ground test device are relatively single. In addition, this application cools or heats the inhaled gas through the heat exchanger 16 designed inside the heat exchange section 2 to realize the low-temperature or high-temperature environment assessment test function of the unmanned aerial vehicle 11. Through the rain blowing system 18, the snow blowing system 19 or the spraying system 20 designed inside the multi-functional environment simulation section 4, the horizontal rain blowing, horizontal snow blowing or icing environment assessment test function during the forward flight of the unmanned aerial vehicle 11 is realized. Through the rainfall system 9, the snowfall system 10 and the sunshine system 8 designed at the inner top of the test section 6, the assessment test function of the unmanned aerial vehicle 11 under natural rainfall, snowfall or sunshine and other environments is realized. Through the combination of these unique designs, the problem that the existing unmanned aerial vehicle ground test device has insufficient ability to assess and verify the complex environments faced during the service life of the unmanned aerial vehicle 11 is solved.

[0066] Based on the above unmanned aerial vehicle ground test platform, this application also correspondingly proposes a method for testing an unmanned aerial vehicle on the ground, which may include:

[0067] Let the gas enter from the intake end of the incoming flow velocity regulating air intake section, adjust the air flow to the required temperature range through the heat exchange section 2, and after applying corresponding meteorological conditions to the air flow through the environment simulation section 4, send the air flow into the test section 6; at the same time, the incoming flow velocity regulating exhaust section provides power for the axial movement of the air flow, enables the air flow to establish a flow field in the test section 6, and discharges the air flow through the exhaust end.

[0068] Adjust the unmanned aerial vehicle 11 to the target height above the ground through the lifting floor 22, and provide the target meteorology for the test section 6 with the help of a variety of meteorological simulation systems, and test the aerodynamic performance of the unmanned aerial vehicle through the force measuring bench 24.

[0069] It should be noted that the method for testing an unmanned aerial vehicle on the ground in this application is realized based on the aforementioned unmanned aerial vehicle ground test platform. In practical applications, the embodiments of the aforementioned unmanned aerial vehicle ground test platform can be adopted, which will not be elaborated here.

[0070] The above are only the preferred embodiments of this application and are not used to limit this application. For those skilled in the art, this application can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of this application shall be included within the protection scope of this application.

Claims

1. A UAV ground test platform, characterized in that: The invention comprises an incoming wind speed regulating air intake section, a test section (6) and an incoming wind speed regulating exhaust section which are coaxially connected and communicated in sequence; the incoming wind speed regulating air intake section, the test section (6) and the incoming wind speed regulating exhaust section together form a pipeline capable of regulating the incoming wind speed; the inlet of the incoming wind speed regulating air intake section is an air intake end, and the outlet of the incoming wind speed regulating exhaust section is an exhaust end; The inlet section for adjusting the incoming wind speed comprises an air intake section (1), a rectifying section (3) and a contraction section (5) which are arranged in sequence from the air intake end, and the inlet section for adjusting the incoming wind speed is also arranged in sequence with a heat exchange section (2) and an environmental simulation section (4); the heat exchange section is located between the air intake section (1) and the rectifying section (3), the environmental simulation section (4) is located between the rectifying section (3) and the contraction section (5), and the air intake section (1), the heat exchange section (2), the rectifying section (3), the environmental simulation section (4) and the contraction section (5) are coaxially connected and communicated; the large end of the air intake section (1) is close to the air intake end, and the large end of the contraction section (5) is close to the air intake end; the heat exchange section (2) is used to cool or heat the airflow in the inlet section for adjusting the incoming wind speed, and the environmental simulation section (4) is used to provide a variety of meteorological environments for the airflow in the inlet section for adjusting the incoming wind speed; The profile curve of the contraction section (5) along the axial direction conforms to: in, is the outlet radius of the contraction section (5), is the axial distance from the inlet of the contraction section (5) x The cross-sectional radius at , C is the contraction ratio, x is the axial distance from the inlet of the contraction section (5), L is the length of the contraction section (5); The incoming wind speed regulating exhaust section comprises a diffuser section (12), a power section (13) and an exhaust section (14) which are coaxially connected and communicated in sequence from the air inlet end; the small end of the diffuser section (12) is close to the air inlet end, and the small end of the exhaust section (14) is close to the air inlet end; the power section (13) is used to inhale the air flow in the air inlet section (1) into the test section (6); the diffusion angles of the diffuser section (12) and the exhaust section (14) are both 5°; The test section (6) is provided with a force measuring platform (24) and a lifting floor (22); the force measuring platform (24) passes through the lifting floor and is used to park the UAV (11) and test the aerodynamic performance of the UAV; the lifting floor (22) is used to adjust the height of the UAV (11) above the ground; and a plurality of meteorological simulation systems are provided at the top of the force measuring platform (24) in the test section (6); The incoming air velocity regulating exhaust part is used to provide power for the axial movement of the airflow, so that the airflow establishes a flow field in the test section (6) and discharges the airflow through the exhaust end.

2. The UAV ground test platform according to claim 1, characterized in that: A plurality of layers of damping nets (17) are installed axially in the rectifying section (3).

3. The UAV ground test platform according to claim 2, characterized in that: The environment simulation section (4) is provided with one or more of a detachable rain blowing system (18), a snow blowing system (19), and a spray system (20); The various meteorological simulation systems include one or more of a sunshine system (8), a rainfall system (9), and a snowfall system (10).

4. The UAV ground test platform according to claim 3, characterized in that: The air intake section (1) is shaped like a trumpet as a whole, and a first protective net (15) is installed at the entrance of the air intake section (1) to prevent foreign matter from entering; A second protective net (28) is installed at the outlet of the exhaust section (14) to prevent foreign matter from entering.

5. The UAV ground test platform according to claim 4, characterized in that: The test section (6) is externally coated with a heat insulating material (7); A fan system is arranged inside the power section (13).

6. A test method for the UAV ground test platform according to any one of claims 1 to 5, characterized in that: include: The gas enters from the air inlet end of the air velocity regulating air inlet section, the air flow is adjusted to a required temperature range through the heat exchange section (2), and after the corresponding meteorological conditions are applied to the air flow through the environmental simulation section (4), the air flow is sent to the test section (6); at the same time, the air velocity regulating exhaust section provides power for the axial movement of the air flow, so that the air flow establishes a flow field in the test section (6), and the air flow is discharged through the exhaust end; The unmanned aerial vehicle (11) is adjusted to a target height above the ground by means of a lifting floor (22), and target weather is provided in the test section (6) by means of a variety of weather simulation systems, and the aerodynamic performance of the unmanned aerial vehicle is tested by means of a force measuring bench (24).

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