A Distributed Sensor-Based Aerodynamic Data Evaluation Device

Abstract

An aerodynamic data evaluation device based on distributed sensors includes an aircraft body with wings, multiple pressure measuring holes, multiple pressure sensors, a data transmission device, and a data processing unit. The multiple pressure measuring holes are distributed across the surface of the wings for collecting air pressure data. The multiple pressure sensors are all located inside the aircraft body and correspond one-to-one with the multiple pressure measuring holes. The pressure sensors and pressure measuring holes are connected via connecting pipes to measure air pressure data and convert it into electrical signals. The data transmission device is electrically connected to the pressure sensors for reading and transmitting air pressure data. The data processing unit is connected to the data transmission device and configured to calculate the flight parameters of the aircraft body based on the air pressure data, thereby achieving aerodynamic performance evaluation. This device achieves global flow field prediction by distributing multiple pressure measuring holes on the wings. By calculating the aircraft's flight parameters and evaluating aerodynamic performance through the data processing unit, errors in complex flow field environments are reduced.

Description

Technical Field

[0001] This utility model relates to the field of aerodynamic data measurement technology for aircraft, specifically an aerodynamic data evaluation device based on distributed sensors, and an evaluation device based on distributed embedded surface pressure sensors, which is suitable for real-time acquisition and verification of aerodynamic data of fixed-wing aircraft. Background Technology

[0002] To obtain various flight parameters of an aircraft, the aircraft is equipped with a sensor system to measure and collect data. Currently, aerodynamic data measurement of aircraft mainly relies on probe-type systems (such as pitot tubes) and embedded sensing systems (FADS).

[0003] Probe-type systems require exposed sensors to measure flight parameters, but external sensors can compromise the aircraft's stealth capabilities and interfere with the flow field distribution on the aircraft's surface, leading to data distortion.

[0004] Although the FADS system embeds sensors inside the aircraft and measures the air pressure on the aircraft surface by setting pressure measurement holes to calculate various flight parameters, its pressure measurement holes are concentrated in the nose area, making it impossible to measure the global flow field around the aircraft, and the error is significant in complex flow environments. Utility Model Content

[0005] (a) Technical problems to be solved

[0006] This invention provides a pneumatic data evaluation device based on distributed sensors, which solves the following technical problems:

[0007] Layout limitations: Overcome the measurement blind spots of the concentrated layout at the nose and realize global flow field prediction of the aircraft;

[0008] Accuracy deficiencies: By combining distributed sensors with nonlinear models, errors under complex flow conditions can be reduced.

[0009] (II) Technical Solution

[0010] To achieve the above objectives, this utility model provides the following technical solution:

[0011] An aerodynamic data evaluation device based on distributed sensors includes an aircraft body with wings, and further includes:

[0012] Multiple pressure measuring holes are distributed on the surface of the wing to collect surface air pressure.

[0013] Multiple pressure sensors are disposed inside the main body of the aircraft and correspond one-to-one with multiple pressure measuring holes. The pressure sensors and the corresponding pressure measuring holes are connected by connecting pipes to measure air pressure data and convert it into electrical signals.

[0014] A data transmission device, electrically connected to the pressure sensor, is used to read and transmit the air pressure data;

[0015] A data processing unit, connected to the data transmission device, is configured to calculate the flight parameters of the aircraft body based on the air pressure data, thereby achieving aerodynamic performance evaluation.

[0016] Preferably, the plurality of pressure measuring holes are all disposed in the leading edge region of the wing and are respectively distributed on the upper surface and the lower surface of the wing, for optimizing global flow field prediction.

[0017] Preferably, the plurality of pressure measuring holes includes five pressure measuring holes distributed on the upper surface of the wing and two pressure measuring holes distributed on the lower surface of the wing.

[0018] Preferably, the main body of the aircraft includes a fuselage, the wings are two pieces and symmetrically arranged on the left and right sides of the fuselage, the five pressure measuring holes on the upper surface of the wings include two first holes, two second holes and one third hole, and the two pressure measuring holes on the lower surface of the wings are fourth holes;

[0019] The two first holes are symmetrically arranged on the two wings with a spacing of 0.8m, and the distance between the first hole and the leading edge of the wing is less than or equal to 3% of the wing width;

[0020] The two second holes are symmetrically arranged on the two wings and spaced 1.4m apart. The distance between the second hole and the leading edge of the wing is less than or equal to 3% of the wing width.

[0021] The third hole is located on one of the wings and 0.4m from the center of the fuselage, and the distance between the third hole and the leading edge of the wing is less than or equal to 5% of the wing width.

[0022] The two fourth holes are symmetrically arranged on the two wings with a spacing of 0.8m. The distance between the fourth hole and the leading edge of the wing is less than or equal to 3% of the wing width.

[0023] Preferably, the connecting tube is made of rubber, and the connection between the connecting tube and the pressure measuring hole, and the connection between the connecting tube and the pressure sensor are fixed with resin and foam to enhance the sealing performance.

[0024] Preferably, multiple pressure sensors are integrated inside a housing, and each pressure sensor has a pressure measuring opening located outside the housing for connecting to the connecting pipe.

[0025] Preferably, each pressure sensor includes two pressure measuring openings for measuring dynamic pressure and static pressure, respectively, and converts the pressure signal into a voltage output.

[0026] Preferably, the data transmission device includes an Arduino development board for reading voltage signals and storing data.

[0027] Preferably, the data processing unit is configured to use Matlab software to process the measured data, establish a nonlinear aerodynamic model to calculate flight parameters and reduce errors.

[0028] Preferably, it also includes a battery unit to power the pressure sensor, the data transmission device, and the data processing unit.

[0029] (III) Beneficial Effects

[0030] Compared with the prior art, the beneficial effects of this utility model are:

[0031] Global measurement capability: By distributing multiple pressure gauges on the wing, the pressure gauges cover key areas (3%-5% width range of the leading edge) of the aircraft body (upper and lower surfaces), thereby achieving dynamic capture of the flow field of the entire aircraft.

[0032] Accuracy improvement: Nonlinear aerodynamic models based on Matlab (such as dynamic / static pressure separation processing) significantly reduce errors caused by complex airflow interference;

[0033] Structural reliability: The connection points between the connecting pipe and the pressure measuring hole, as well as the connection points between the connecting pipe and the pressure sensor, are fixed and sealed with resin and foam to ensure consistent air pressure transmission. Attached Figure Description

[0034] The accompanying drawings are provided to further illustrate the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention, but do not constitute a limitation thereof. In the drawings:

[0035] Figure 1 A perspective view of the aerodynamic data evaluation device based on distributed sensors of this invention is shown;

[0036] Figure 2 It shows Figure 1 A 3D view from another angle;

[0037] Figure 3 It shows Figure 1 Schematic diagram of some internal structures;

[0038] Figure 4 It shows Figure 1 A sectional view of the vertical sections of the middle wing passing through the first and fourth holes;

[0039] Figure 5 A schematic diagram of the pressure sensor in this invention is shown.

[0040] In the diagram: 1. Pressure measuring hole; 11. First hole; 12. Second hole; 13. Third hole; 14. Fourth hole; 2. Connecting pipe; 3. Data transmission device; 4. Shell; 5. Data cable; 6. Aircraft body; 61. Wing; 62. Fuselage. Detailed Implementation

[0041] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0042] See appendix Figure 1 -Appendix Figure 3 and appendix Figure 5 This utility model discloses an aerodynamic data evaluation device based on distributed sensors, including an aircraft body 6 with wings 61, multiple pressure measuring holes 1, multiple pressure sensors, a data transmission device 3, and a data processing unit. The multiple pressure measuring holes 1 are distributed on the surface of the wings 61 for collecting surface air pressure. The multiple pressure sensors are all located inside the aircraft body 6 and correspond one-to-one with the multiple pressure measuring holes 1. The pressure sensors and their corresponding pressure measuring holes 1 are connected by connecting pipes 2 for measuring air pressure data and converting it into electrical signals. The data transmission device 3 is electrically connected to the pressure sensors for reading and transmitting air pressure data. The data processing unit is connected to the data transmission device 3 and configured to calculate the flight parameters of the aircraft body 6 based on the air pressure data to achieve aerodynamic performance evaluation.

[0043] Based on the above scheme, the basic framework for global flow field measurement is established through the steps of "pressure measurement port 1 collecting air pressure → connecting pipe 2 transmitting → pressure sensor converting electrical signals → data transmission → parameter calculation". Among them, since multiple pressure measurement ports 1 are distributed on the wing 61, the measurement blind zone caused by the concentration of sensors at the nose position in traditional aircraft is overcome, and the prediction of the global flow field of the aircraft body 6 can be realized. Since the data processing unit can calculate the flight parameters of the aircraft body 6 based on the air pressure data, thereby evaluating aerodynamic performance, the error in complex flow field environment can be reduced.

[0044] See appendix Figure 1 and attached Figure 2In order to optimize the layout area of ​​the pressure measuring holes 1 to improve the prediction accuracy, the following design is made in this embodiment. Specifically, multiple pressure measuring holes 1 are set in the leading edge area of ​​the wing 61 and are distributed on the upper surface and the lower surface of the wing 61, respectively, to optimize the global flow field prediction.

[0045] Based on the above scheme, holes are simultaneously placed on the upper and lower surfaces of the leading edge region of the wing 61 to capture key flow field changes, overcoming the blind spots caused by the concentrated layout of the flow field in the nose of traditional aircraft and enhancing the comprehensiveness of the data.

[0046] See appendix Figure 1 and attached Figure 2 There are several ways to arrange multiple pressure measuring holes 1 on the wing 61. This embodiment introduces one of them. Specifically, the multiple pressure measuring holes 1 include five pressure measuring holes 1 distributed on the upper surface of the wing 61 and two pressure measuring holes 1 distributed on the lower surface of the wing 61.

[0047] The design of the above structure clarifies the number and distribution of pressure measuring holes 1, enabling multiple pressure measuring holes 1 to cover the key areas of the wing 61, thus balancing measurement density and structural feasibility.

[0048] See appendix Figure 1 -Appendix Figure 4 To further clarify the specific locations of the multiple pressure measuring holes 1, the following design was implemented in this embodiment. Specifically, the aircraft body 6 includes a fuselage 62, and two wings 61 are symmetrically arranged on the left and right sides of the fuselage 62. The five pressure measuring holes 1 on the upper surface of the wings 61 include two first holes 11, two second holes 12, and one third hole 13. The two pressure measuring holes 1 on the lower surface of the wings 61 are fourth holes 14. The two first holes 11 are symmetrically arranged on the two wings 61 with a spacing of 0.8m. The distance between the first hole 11 and the leading edge of the wing 61 is less than [missing information]. The width of the fuselage 61 is equal to 3%; two second holes 12 are symmetrically arranged on the two wings 61 with a spacing of 1.4m, and the distance between the second hole 12 and the leading edge of the wing 61 is less than or equal to 3% of the width of the wing 61; a third hole 13 is arranged on one of the wings 61 and 0.4m away from the center of the fuselage 62, and the distance between the third hole 13 and the leading edge of the wing 61 is less than or equal to 5% of the width of the wing 61; two fourth holes 14 are symmetrically arranged on the two wings 61 with a spacing of 0.8m, and the distance between the fourth hole 14 and the leading edge of the wing 61 is less than or equal to 3% of the width of the wing 61.

[0049] Through the design of the above structure, the position of pressure measuring hole 1 on the wing 61 was located, avoiding ambiguity in the position of pressure measuring hole 1 and ensuring that the measurement process and results are reproducible.

[0050] See appendix Figure 3To address the risk of air leakage in the connecting pipe, the following design was implemented in this embodiment: Specifically, the connecting pipe 2 is made of rubber, and the connection points between the connecting pipe 2 and the pressure measuring hole 1, as well as the connection points between the connecting pipe 2 and the pressure sensor, are fixed with resin and foam to enhance sealing.

[0051] Through the design of the above structure, the rubber material is elastic. Through the elasticity of the connecting tube 2 itself and the fixation of resin and foam, the firmness and sealing of the connecting tube 2 after being connected with other components can be guaranteed, preventing slippage and air leakage, ensuring that the air pressure at both ends of the connecting tube 2 is equal, that is, the air pressure transmission is not distorted, thereby ensuring the accuracy of air pressure measurement.

[0052] It should be noted that the connecting pipe 2 should be located inside the main body 6 of the aircraft to ensure that the surface of the wing 61 is smooth and to avoid affecting the air pressure measurement.

[0053] See appendix Figure 3 To avoid the multiple pressure sensors being too scattered and difficult to disassemble and assemble in the main body 6 of the aircraft, the following design is adopted in this embodiment. Specifically, multiple pressure sensors are integrated inside a housing 4, and each pressure sensor is provided with a pressure measuring opening located outside the housing 4 for connecting to the connecting pipe 2.

[0054] The above structural design simplifies the assembly and disassembly of multiple pressure sensors, resulting in a neater and more organized installation.

[0055] To separate dynamic and static pressure measurements and improve data accuracy, this embodiment is designed as follows: Specifically, each pressure sensor includes two pressure measurement openings, used to measure dynamic and static pressure respectively, and converts the pressure signal into a voltage output.

[0056] Based on the above scheme, the pressure sensor's dual pressure measuring openings independently process dynamic and static pressure signals, which can effectively reduce interference from complex flow and thus improve the accuracy of the measured data.

[0057] See appendix Figure 3 To reduce the complexity of data transmission, the following design was implemented in this embodiment. Specifically, the data transmission device 3 includes an Arduino development board for reading voltage signals and storing data.

[0058] The above structure simplifies hardware integration.

[0059] To address computational errors in complex flow environments, this embodiment incorporates the following design: Specifically, the data processing unit is configured to use Matlab software to process the measured data, establish a nonlinear aerodynamic model to calculate flight parameters, and reduce errors.

[0060] Based on the above approach, nonlinear models (such as aerodynamic equations) are established using Matlab software to process the raw data. Compared with linear models, this can significantly reduce calculation errors and thus improve the calculation accuracy in complex flow environments.

[0061] To ensure the continuous operation of the device in the flight environment, the following design is implemented in this embodiment. Specifically, it also includes a battery unit to power the pressure sensor, data transmission device 3, and data processing unit.

[0062] The above structural design avoids the risk of external power outages, ensuring that the aerodynamic data evaluation device can always operate stably.

[0063] Furthermore, the pressure sensor and the data transmission device 3 are electrically connected via a data cable 5.

[0064] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0065] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be construed as limiting the scope of protection of this application.

[0066] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A distributed sensor based aerodynamic data evaluation device comprising an aircraft body having a wing, characterized in that, Also includes: Multiple pressure measuring holes are distributed on the surface of the wing to collect surface air pressure. Multiple pressure sensors are disposed inside the main body of the aircraft and correspond one-to-one with multiple pressure measuring holes. The pressure sensors and the corresponding pressure measuring holes are connected by connecting pipes to measure air pressure data and convert it into electrical signals. A data transmission device, electrically connected to the pressure sensor, is used to read and transmit the air pressure data; A data processing unit, connected to the data transmission device, is configured to calculate the flight parameters of the aircraft body based on the air pressure data, thereby achieving aerodynamic performance evaluation.

2. The device for aerodynamic data evaluation based on distributed sensors according to claim 1, characterized in that Multiple pressure measurement holes are disposed in the leading edge region of the wing and are respectively distributed on the upper and lower surfaces of the wing, for optimizing global flow field prediction.

3. The device according to claim 2, characterized in that The plurality of pressure measuring holes include five pressure measuring holes distributed on the upper surface of the wing and two pressure measuring holes distributed on the lower surface of the wing.

4. The device according to claim 3, characterized in that The main body of the aircraft includes a fuselage, and the wings are two pieces symmetrically arranged on the left and right sides of the fuselage. The five pressure measuring holes on the upper surface of the wings include two first holes, two second holes and one third hole, and the two pressure measuring holes on the lower surface of the wings are fourth holes. The two first holes are symmetrically arranged on the two wings with a spacing of 0.8m, and the distance between the first hole and the leading edge of the wing is less than or equal to 3% of the wing width; The two second holes are symmetrically arranged on the two wings and spaced 1.4m apart. The distance between the second hole and the leading edge of the wing is less than or equal to 3% of the wing width. The third hole is located on one of the wings and 0.4m from the center of the fuselage, and the distance between the third hole and the leading edge of the wing is less than or equal to 5% of the wing width. The two fourth holes are symmetrically arranged on the two wings with a spacing of 0.8m. The distance between the fourth hole and the leading edge of the wing is less than or equal to 3% of the wing width.

5. The distributed sensor based aerodynamic data evaluation apparatus as claimed in claim 1, wherein, The connecting tube is made of rubber, and the connection between the connecting tube and the pressure measuring hole, as well as the connection between the connecting tube and the pressure sensor, are fixed with resin and foam to enhance the sealing performance.

6. The distributed sensor based aerodynamic data evaluation apparatus as claimed in claim 1, wherein, Multiple pressure sensors are integrated inside a housing. Each pressure sensor has a pressure measuring opening located outside the housing for connecting to the connecting pipe.

7. A device for aerodynamic data evaluation based on distributed sensors according to claim 6, characterized in that Each of the pressure sensors includes two pressure-measuring openings, used to measure dynamic pressure and static pressure respectively, and converts the pressure signal into a voltage output.

8. The distributed sensor based aerodynamic data evaluation apparatus as claimed in claim 1, wherein, The data transmission device includes an Arduino development board, which is used to read voltage signals and store data.

9. The distributed sensor-based aerodynamic data evaluation apparatus according to claim 1, wherein, The data processing unit is configured to use Matlab software to process the measured data, establish a nonlinear aerodynamic model to calculate flight parameters and reduce errors.

10. A distributed sensor based aerodynamic data evaluation device according to any of claims 1 to 9, characterized in that It also includes a battery unit to power the pressure sensor, the data transmission device, and the data processing unit.

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