Unmanned aerial vehicle mechanical control and jet flow drag reduction trailing edge flap pneumatic structure

Abstract

The invention relates to a trailing edge flap pneumatic structure for mechanical control and jet flow resistance reduction of an unmanned aerial vehicle. The trailing edge flap pneumatic structure comprises a deflection angle detection device, a jet flow spraying rod, a jet flow air supply pipe, a controller and a flight control plate. The two deflection angle detection devices are arranged at the two trailing edge flaps and used for detecting the deflection angles of the two trailing edge flaps; the two jet flow spray rods are transversely connected to the upper portions of the two wings and located in front of the two trailing edge flaps, and a plurality of backward jet flow holes are formed in the jet flow spray rods. An inlet of the jet flow air supply pipe is sequentially provided with a jet flow control electromagnetic valve and a jet flow meter and connected with a high-pressure air source, and the jet flow meter is used for detecting the air flow in the jet flow air supply pipe; an outlet of the jet flow air supply pipe is divided into two branches which are connected with the two jet flow spray rods; the controller is connected with the jet flow control electromagnetic valve; the flight control board is connected with the two deflection angle detection devices, the controller and the jet flow meter, and negative feedback control over the air flow of the jet flow air supply pipe based on the trailing edge flap deflection angle is formed.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of unmanned aerial vehicle design, and particularly relates to a mechanical control and jet flow drag reduction trailing edge flap aerodynamic structure of an unmanned aerial vehicle. BACKGROUND

[0002] Compared with manned aircraft, unmanned aerial vehicles have the advantages of light weight, convenient movement, high mobility, long endurance, low cost and the like.

[0003] When the unmanned aerial vehicle is in high-mobility / long-endurance flight, currently, an aerodynamic control surface is usually used to provide a control torque required for flight control, and a large aerodynamic drag is generated due to deflection of the aerodynamic control surface. To this end, a tail is added to reduce the aerodynamic drag. This technical solution increases the weight of the aircraft and reduces the stability and reliability of the unmanned aerial vehicle.

[0004] The present application is proposed in view of the existence of the above technical defects. SUMMARY

[0005] The purpose of the present application is to provide a mechanical control and jet flow drag reduction trailing edge flap aerodynamic structure of an unmanned aerial vehicle to overcome or alleviate at least one aspect of the technical defects known to exist.

[0006] The technical solution of the present application is as follows:

[0007] A mechanical control and jet flow drag reduction trailing edge flap aerodynamic structure of an unmanned aerial vehicle comprises a deflection angle detection device, a jet flow spray rod, a jet flow supply pipe, a controller and a flight control board.

[0008] The deflection angle detection device has two, which are arranged at two trailing edge flaps to detect the deflection angles of the two trailing edge flaps.

[0009] The jet flow spray rod has two, which are transversely connected above the two wings and in front of the two trailing edge flaps, and has a plurality of backward jet flow holes thereon.

[0010] The jet flow supply pipe has a jet flow control electromagnetic valve and a jet flow flowmeter arranged in sequence at the inlet, and is connected to a high-pressure gas source. The jet flow flowmeter is used to detect the gas flow in the jet flow supply pipe.

[0011] The outlet of the jet flow supply pipe is divided into two branches, which are connected to the two jet flow spray rods, and the two branches are provided with jet flow pressure reducing valves.

[0012] The controller is connected to the jet flow control electromagnetic valve.

[0013] The flight control board is connected to the two deflection angle detection devices, and is connected to the controller and the jet flow flowmeter, thereby forming a negative feedback control based on the deflection angles of the trailing edge flaps and the gas flow of the jet flow supply pipe.

[0014] According to at least one of the embodiments of the present application, in the above-mentioned aerodynamic structure of the UAV mechanical control plus jet flow drag reduction trailing edge flap, the flight control board detects the deflection angles of the two trailing edge flaps through the two deflection angle detection devices, obtains the deflection angle of the trailing edge flap by averaging, and then obtains the jet flow matching the deflection angle of the trailing edge flap, so as to adjust the opening degree of the jet flow control electromagnetic valve through the controller, and make the gas flow in the jet flow supply pipe tend to the matching jet flow through the jet flow meter.

[0015] According to at least one of the embodiments of the present application, in the above-mentioned aerodynamic structure of the UAV mechanical control plus jet flow drag reduction trailing edge flap, the jet flow supply pipe inlet is connected to the jet port of the engine or the bleed air port opened on the high-pressure component of the engine.

[0016] According to at least one of the embodiments of the present application, in the above-mentioned aerodynamic structure of the UAV mechanical control plus jet flow drag reduction trailing edge flap, it further comprises a deflection driving gas pipe, a temperature sensing bag, and a lever.

[0017] The deflection control electromagnetic valve and the deflection flow meter are sequentially arranged on the deflection driving gas pipe, the inlet is connected to the high-temperature gas source, and the outlet is connected to the gas inlet end of the temperature sensing bag, and the deflection flow meter is used to detect the gas flow in the deflection driving gas pipe.

[0018] The output end of the temperature sensing bag is connected to one end of the lever, the other end of the lever is divided into two branch rods, the two branch rods are connected to vertical long strip gears, and the two vertical long strip gears are engaged with the circular gears arranged on the two trailing edge flap shafts.

[0019] The two deflection angle detection devices are elastic meters connected between the two branch rods and the wings.

[0020] The controller is connected to the deflection control electromagnetic valve.

[0021] The flight control board is connected to the deflection flow meter, so as to detect the gas flow in the deflection driving gas pipe through the deflection flow meter, and adjust the opening degree of the deflection control electromagnetic valve through the controller.

[0022] According to at least one of the embodiments of the present application, in the above-mentioned aerodynamic structure of the UAV mechanical control plus jet flow drag reduction trailing edge flap, the gas flow in the deflection driving gas pipe is input into the temperature sensing bag, the internal energy is converted into mechanical energy, the temperature sensing bag is heated and expanded, and then drives the lever to move, drives the two vertical long strip gears to move, and drives the two circular gears to rotate, so as to deflect the two trailing edge flaps, and the two deflection angle detection devices are deformed accordingly, the size of the elastic force generated by the deformation has a corresponding relationship with the deflection angle of the trailing edge flap, and the flight control board detects the deflection angles of the two trailing edge flaps through the two deflection angle detection devices.

[0023] According to at least one embodiment of this application, in the above-described aerodynamic structure of trailing edge flaps for mechanical control and jet drag reduction of unmanned aerial vehicles, the deflection drive air inlet is connected to the jet nozzle of the engine, or to the bleed air inlet opened on the high-pressure component of the engine.

[0024] According to at least one embodiment of this application, in the above-described aerodynamic structure of trailing edge flaps for mechanical control and jet drag reduction of unmanned aerial vehicles, the air inlet of the engine adopts the shape of a tapered tube.

[0025] According to at least one embodiment of this application, in the above-mentioned aerodynamic structure of trailing edge flap for mechanical control and jet drag reduction of unmanned aerial vehicles, the jet nozzle, jet air supply pipe, and deflection drive air supply pipe are made of high-strength, high-temperature resistant aluminum alloy.

[0026] According to at least one embodiment of this application, in the above-described aerodynamic structure of the trailing edge flap with mechanical control and jet drag reduction for the UAV, the flight control board, controller, deflection control solenoid valve, and two deflection angle detection devices constitute negative feedback control of the trailing edge flap deflection angle, specifically:

[0027] The flight control board adjusts the opening of the deflection control solenoid valve through the controller based on the deflection angle of the trailing edge flap, thereby adjusting the airflow in the deflection drive air pipe so that the deflection angle of the trailing edge flap tends to the set value.

[0028] According to at least one embodiment of this application, in the above-described aerodynamic structure of the trailing edge flap with mechanical control and jet drag reduction for the UAV, the flight control board, controller, deflection control solenoid valve, and deflection flow meter constitute negative feedback control of the deflection angle of the trailing edge flap, specifically:

[0029] The flight control board calculates the required deflection drive airflow in the deflection drive air supply pipe based on the control value of the trailing edge flap deflection angle. It then adjusts the opening of the deflection control solenoid valve through the controller and detects the airflow in the deflection drive air supply pipe through the deflection flow meter, so that the airflow in the deflection drive air supply pipe tends to the required deflection drive airflow. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the aerodynamic structure of the trailing edge flap for mechanical control and jet drag reduction of the UAV provided in the embodiments of this application;

[0031] in:

[0032] 1-Deflection angle detection device; 2-Jet nozzle; 3-Jet air supply pipe; 4-Controller; 5-Flight control board; 6-Leading edge flap; 7-Wing; 8-Engine; 9-Jet control solenoid valve; 10-Jet flow meter; 11-Jet pressure reducing valve; 12-Deflection drive air supply pipe; 13-Temperature sensor; 14-Lever; 15-Deflection control solenoid valve; 16-Deflection flow meter; 17-Vertical bar gear; 18-Circular gear.

[0033] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0034] 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, and other related parts can be referred to the general design.

[0035] 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 word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0036] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable 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. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0037] By utilizing jet technology and installing jet generators on drones, the interaction between the jet stream and the surrounding air can enhance flight control. Corresponding to the deflection angle of the drone's trailing edge flaps, and using jet assistance with appropriate flow rates, a mechanical control combined with jet drag reduction aerodynamic structure can be constructed. This significantly reduces aerodynamic drag during drone flight. Compared to techniques that reduce drag by adding tail fins, this approach offers significant advantages in controlling drone weight and ensuring stability and reliability.

[0038] Based on the above, this application provides an aerodynamic structure for a trailing edge flap of an unmanned aerial vehicle (UAV) with mechanical control and jet drag reduction, such as... Figure 1 As shown, it includes a deflection angle detection device 1, a jet nozzle 2, a jet air supply pipe 3, a controller 4, and a flight control board 5.

[0039] There are two deflection angle detection devices 1, which are set at the two trailing edge flaps 6 to detect the deflection angle of the two trailing edge flaps 6.

[0040] There are two jet nozzles 2, which are laterally connected above the two wings 7 and located in front of the two trailing edge flaps 6, and have multiple rearward jet holes.

[0041] The jet supply pipe 3 is equipped with a jet control solenoid valve 9 and a jet flow meter 10 in sequence at the inlet, and is connected to a high-pressure air source. Specifically, it can be connected to the jet nozzle of the engine 8 or to the air intake port opened on the high-pressure component of the engine 8. The jet flow meter is used to detect the air flow in the jet supply pipe 3.

[0042] The outlet of the jet air supply pipe 3 is divided into two branches, which are connected to two jet nozzles 2, and jet pressure reducing valves 11 are installed on the two branches.

[0043] Controller 4 is connected to jet control solenoid valve 9.

[0044] The flight control board 5 connects to two deflection angle detection devices 1, as well as to the controller 4 and the jet flow meter 10, forming a negative feedback control of the airflow volume of the jet supply pipe 3 based on the trailing edge flap deflection angle, as detailed below:

[0045] The flight control board 5 detects the deflection angles of the two trailing edge flaps 6 through two deflection angle detection devices 1, takes the average to obtain the trailing edge flap deflection angle, and then obtains the jet flow rate that matches the trailing edge flap deflection angle. The controller 4 adjusts the opening of the jet control solenoid valve 9, and the jet flow rate in the jet supply pipe 3 is detected by the jet flow meter 10, so that the air flow rate in the jet supply pipe 3 tends to match the jet flow rate.

[0046] The above-described embodiment discloses a mechanical control and jet drag reduction trailing edge flap aerodynamic structure for UAVs. The design is based on the trailing edge flap deflection angle and performs negative feedback control on the airflow of the jet supply pipe 3. This allows the jet supply pipe 3 to supply the two jet nozzles 2 with a jet flow rate that matches the trailing edge flap deflection angle. The jet is then ejected rearward through the rearward jet hole, reducing the aerodynamic drag of the UAV. This multi-functional drag reduction is achieved by utilizing the UAV's own conditions. The overall structure is simple, occupies a small volume, and is easy to maintain.

[0047] Jet pressure reducing valves 11 are installed on the two branches of the jet air supply pipe 3 outlet to reduce the pressure and temperature of the transported airflow, thereby protecting the pipeline and its body structure.

[0048] In the aerodynamic structure of the trailing edge flap of the UAV with mechanical control and jet drag reduction disclosed in the above embodiments, the two deflection angle detection devices 1 are force gauges, and further include a deflection drive air supply pipe 12, a temperature sensing bulb 13, and a lever 14.

[0049] A deflection control solenoid valve 15 and a deflection flow meter 16 are sequentially installed on the deflection drive air supply pipe 12. The inlet is connected to a high-temperature air source, which can be connected to the jet port of the engine 8 or to the air intake port opened on the high-pressure component of the engine 8. The outlet is connected to the air inlet of the temperature sensing bulb 13. The deflection flow meter 16 is used to detect the air flow in the deflection drive air supply pipe 12.

[0050] The output end of the temperature sensor 13 is connected to one end of the lever 14, and the other end of the lever 14 is divided into support rods. Vertical long gears 17 are connected to the two support rods, and the two vertical long gears 17 mesh with circular gears 18 set on the rotating shafts of the two trailing edge flaps 6.

[0051] Two deflection angle detection devices 1 are connected between the two support rods and the wing 7.

[0052] Controller 4 is connected to deflection control solenoid valve 15.

[0053] The flight control board 5 is connected to the deflection flow meter 16 so that the air flow in the deflection drive air supply pipe 12 can be detected by the deflection flow meter 16, and the opening degree of the deflection control solenoid valve 15 can be adjusted by the controller 4.

[0054] The airflow in the deflection drive air pipe 12 is input into the temperature sensing bulb 13, which can convert internal energy into mechanical energy, causing the temperature sensing bulb 13 to expand due to heat. This, in turn, drives the lever 14 to move, causing the two vertical bar gears 17 to move, which in turn drives the two circular gears 18 to rotate. This causes the two trailing edge flaps 6 to deflect and the two deflection angle detection devices 1 to deform accordingly. The magnitude of the elastic force generated by this deformation is related to the deflection angle of the trailing edge flaps 6. Thus, the flight control board 5 can detect the deflection angle of the two trailing edge flaps 6 through the two deflection angle detection devices 1.

[0055] The flight control board 5, controller 4, deflection control solenoid valve 15, and two deflection angle detection devices 1 can form a negative feedback control for the deflection angle of the trailing edge flaps. The specific process is as follows:

[0056] The flight control board 5 adjusts the opening of the deflection control solenoid valve 15 through the controller 4 according to the deflection angle of the trailing edge flap, thereby adjusting the air flow in the deflection drive air pipe 12 so that the deflection angle of the trailing edge flap tends to the set value.

[0057] Under the condition that there is a one-to-one correspondence between the air flow rate in the deflection drive air pipe 12 and the deflection angle of the trailing edge flap, negative feedback control of the deflection angle of the trailing edge flap can also be formed by the flight control board 5, controller 4, deflection control solenoid valve 15, and deflection flow meter 16. The specific process is as follows:

[0058] The flight control board 5 calculates the required deflection drive airflow in the deflection drive air supply pipe 12 based on the control value of the trailing edge flap deflection angle. The controller 4 adjusts the opening of the deflection control solenoid valve 15 and detects the airflow in the deflection drive air supply pipe 12 through the deflection flow meter 16, so that the airflow in the deflection drive air supply pipe 12 tends to the required deflection drive airflow.

[0059] The air intake of engine 8 adopts a tapered tube shape to facilitate the introduction and pressurization of gas.

[0060] The jet nozzle 2, jet air supply pipe 3, and deflection drive air supply pipe 12 are made of high-strength, high-temperature resistant aluminum alloy.

[0061] 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 protection scope 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 protection scope of this application.

Claims

1. A UAV mechanical control plus jet drag reduction trailing edge flap aerodynamic structure, characterized in that, The deflection angle detecting device (1), the jet spray rod (2), the jet supply pipe (3), the controller (4), and the flight control board (5) are included. The deflection angle detecting device (1) is provided at the two trailing edge flaps (6) to detect the deflection angles of the two trailing edge flaps (6). The jet spray rod (2) is transversely connected above the two wings (7) and in front of the two trailing edge flaps (6) and has a plurality of rearward jet holes. The jet supply pipe (3) is connected to a high-pressure air source and has a jet control electromagnetic valve (9) and a jet flow meter (10) arranged in sequence at the inlet of the jet supply pipe (3). The outlet of the jet supply pipe (3) is divided into two branches and connected to the two jet spray rods (2) and has a jet pressure reducing valve (11) arranged on each branch. The controller (4) is connected to the jet control electromagnetic valve (9). The flight control board (5) is connected to the two deflection angle detecting devices (1), the controller (4), and the jet flow meter (10) to form a negative feedback control based on the deflection angle of the trailing edge flap and the air flow of the jet supply pipe (3).

2. The UAV mechanical control plus fluidic drag reduction trailing edge flap aerodynamic structure according to claim 1, wherein, The flight control board (5) detects the deflection angles of the two trailing edge flaps (6) through the two deflection angle detecting devices (1), averages the deflection angles to obtain the deflection angle of the trailing edge flap, and then obtains the jet flow matching the deflection angle of the trailing edge flap.

3. The UAV mechanical control plus fluidic drag reduction trailing edge flap aerodynamic structure according to claim 2, wherein, The jet supply pipe (3) is connected to the jet port of the engine (8) or the air inlet port provided on the high-pressure component of the engine (8).

4. The UAV mechanical control plus fluidic drag reduction trailing edge flap aerodynamic structure according to claim 3, wherein, The deflection driving air supply pipe (12), the temperature sensing bag (13), and the lever (14) are further included. The deflection control electromagnetic valve (15) and the deflection flow meter (16) are arranged in sequence on the deflection driving air supply pipe (12), the inlet of which is connected to a high-temperature air source and the outlet of which is connected to the air inlet end of the temperature sensing bag (13), and the deflection flow meter (16) is used to detect the air flow in the deflection driving air supply pipe (12). The output end of the temperature sensing bag (13) is connected to one end of the lever (14), the other end of the lever (14) is divided into two branches, vertical long strip gears (17) are connected to the two branches, and the two vertical long strip gears (17) are engaged with the circular gears (18) provided on the rotating shafts of the two trailing edge flaps (6). The two deflection angle detecting devices (1) are elastic gauges and are connected between the two branches and the wings (7). The controller (4) is connected to the deflection control electromagnetic valve (15). The flight control board (5) is connected to the deflection flow meter (16) to detect the air flow in the deflection driving air supply pipe (12) through the deflection flow meter (16) and adjust the opening degree of the deflection control electromagnetic valve (15) through the controller (4).

5. The UAV mechanical control plus fluidic drag reduction trailing edge flap aerodynamic structure according to claim 4, wherein, The deflection driving air pipe (12) is connected with the jet port of the engine (8) or the air inlet of the high pressure part of the engine (8).

6. The UAV mechanical control plus fluidic drag reduction trailing edge flap aerodynamic structure according to claim 5, wherein, The air inlet of the engine (8) is in the shape of a taper pipe.

7. The UAV mechanical control plus fluidic drag reduction trailing edge flap aerodynamic structure according to claim 6, wherein, The jet pipe (2), the jet air supply pipe (3) and the deflection driving air pipe (12) are made of aluminum alloy with high strength and high temperature resistance.

8. The UAV mechanical control plus fluidic drag reduction trailing edge flap aerodynamic structure according to claim 7, wherein, The flight control board (5), the controller (4), the deflection control electromagnetic valve (15) and the two deflection angle detecting devices (1) constitute a negative feedback control of the deflection angle of the trailing edge flap, specifically as follows:

9. The UAV mechanical control plus fluidic drag reduction trailing edge flap aerodynamic structure according to claim 8, wherein, The flight control board (5) adjusts the opening of the deflection control electromagnetic valve (15) through the controller (4) according to the deflection angle of the trailing edge flap, so as to adjust the air flow in the deflection driving air pipe (12), and make the deflection angle of the trailing edge flap tend to the set value. The flight control board (5), the controller (4), the deflection control electromagnetic valve (15) and the deflection flow meter (16) constitute a negative feedback control of the deflection angle of the trailing edge flap, specifically as follows:

10. The UAV mechanical control plus fluidic drag reduction trailing edge flap aerodynamic structure according to claim 8, wherein, The flight control board (5) calculates the required deflection driving air flow in the deflection driving air pipe (12) according to the control value of the deflection angle of the trailing edge flap, adjusts the opening of the deflection control electromagnetic valve (15) through the controller (4), and detects the air flow in the deflection driving air pipe (12) through the deflection flow meter (16), so as to make the air flow in the deflection driving air pipe (12) tend to the required deflection driving air flow. ​

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