A general design method of unmanned transport vehicle based on scene analysis

Abstract

The application provides a kind of overall design method of unmanned transport machine based on scene analysis, comprising the following steps: S1: presetting the parameters of the transported objects and environmental parameters under different scenes;S2: determining the interval range of the unmanned aerial vehicle load parameters;S3: determining the unmanned aerial vehicle platform configuration;S4: carrying out unmanned aerial vehicle layout design and aerodynamic shape parameter design, and simultaneously carrying out power system selection and design verification;S5: carrying out unmanned aerial vehicle internal structure design;S6: checking the weight and center of gravity of the whole machine;S7: flight control parameter adjustment and ground system joint debugging, and comparing the operation efficiency of the existing unmanned aerial vehicle under the preset scene, if better, confirming the completion of the design;If lower than the existing efficiency, update the design S1 parameters and reiterate optimization, the application can help the unmanned aerial vehicle to accurately locate each design index parameter during overall design, and provide technical support for efficient operation of unmanned transport machine.

Description

[Technical Field]

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) design, and more particularly to an overall design method for unmanned transport aircraft based on scenario analysis. [Background Technology]

[0002] In recent years, my country's logistics demand has exploded, and transport drones have received significant attention in related fields. Simultaneously, with the development of lightweight materials, high-performance power systems, and high-precision satellite navigation technology, the overall performance of drones has continuously improved. They are now being used on a large scale in various logistics and transportation scenarios, demonstrating strong advantages in transportation methods and timeliness. However, because unmanned transport aircraft are still in the early stages of industry application, drone design does not match the needs of many typical application scenarios, resulting in insufficient or wasted transport capacity and relatively low system execution efficiency.

[0003] At present, the platform configuration, communication links, ground command and control, and environmental adaptability of unmanned transport aircraft in typical application scenarios are not closely linked, and cannot accurately meet the relevant transportation needs. Therefore, how to help unmanned aircraft accurately locate transportation needs and improve the transportation efficiency and environmental adaptability of unmanned aircraft systems is the focus of current research.

[0004] Therefore, it is necessary to study a scenario-based unmanned transport aircraft design method to address the shortcomings of existing technologies and solve or mitigate one or more of the aforementioned problems. [Summary of the Invention]

[0005] In view of this, the present invention provides an overall design method for unmanned transport aircraft based on scenario analysis. This method can help the UAV accurately locate various design index parameters during the overall design process, providing technical support for the efficient operation of unmanned transport aircraft.

[0006] On the one hand, the present invention provides an overall design method for unmanned transport aircraft based on scenario analysis, the unmanned transport design method comprising the following steps:

[0007] S1: Preset parameters of the object to be transported and environmental parameters for different scenarios;

[0008] S2: Determine the range of UAV payload parameters based on the parameters of the object to be transported and the environmental parameters in S1;

[0009] S3: Determine the UAV platform configuration based on the range of UAV payload parameters in S2;

[0010] S4: Based on the UAV platform configuration in S3, design the UAV layout and aerodynamic parameters, and simultaneously carry out the selection and design verification of the power system;

[0011] S5: Design the internal structure of the UAV based on the platform configuration in S3 and the UAV layout and aerodynamic parameters in S4.

[0012] S6: Perform a full weight and center of gravity check on the UAV whose internal structure design was completed in S5. The check results meet the preset load weight and loading position of the cargo to be transported.

[0013] S7: Perform flight control parameter tuning and ground system joint testing on the UAV that has been verified in S6, and compare it with the existing UAV's operational efficiency in the preset scenario. If it is better, the design is confirmed to be completed; if it is lower than the existing efficiency, update the parameters in design S1 and iterate and optimize again.

[0014] In addition to the aspects and any possible implementations described above, a further implementation is provided in which the parameters of the transported object in S1 include transport distance, flight altitude, weight of the object to be transported, and external volume of the object to be transported, and the environmental parameters include terrain, take-off and landing conditions, communication status, support requirements, and weather conditions.

[0015] In addition to the aspects and any possible implementations described above, an implementation is further provided, wherein S3 specifically comprises:

[0016] When the payload parameters of the UAV are such that the transport payload weight is between 5 and 15 kg, a multi-rotor configuration should be selected.

[0017] When the payload parameters of the UAV are that the transport payload weight is between 25 and 80 kg, a compound wing configuration should be selected.

[0018] When the payload parameters of the UAV are that the transport payload is above 150kg, a fixed-wing configuration should be selected.

[0019] In addition to the aspects and any possible implementations described above, an implementation is further provided in which the UAV layout design in S4 includes the UAV wingspan, UAV length, and UAV height.

[0020] In addition to the aspects and any possible implementations described above, an implementation is further provided in which the aerodynamic shape parameter design in S4 includes the reference area, mean aerodynamic chord length, span, wing mounting angle, and horizontal tail mounting angle of the wing, horizontal tail, and vertical tail control surfaces.

[0021] In addition to the aspects and any possible implementations described above, a further implementation is provided, wherein the design verification in S4 specifically involves: performing full-aircraft aerodynamic characteristic calculations, wind tunnel experiments, performance verification, and flight quality calculations on the designed UAV.

[0022] In addition to the aspects and any possible implementations described above, a further implementation is provided, wherein the power system selection in S4 is specifically as follows: the power system is determined according to the parameters of the object to be transported under the preset scenario, and the adaptability of the aerodynamic shape is verified according to the environmental parameters under the preset scenario.

[0023] In addition to the aspects and any possible implementations described above, a further implementation is provided in which the internal structural design in S5 includes the layout of internal avionics equipment and strength verification analysis of the loading equipment.

[0024] Compared with the prior art, the present invention can achieve the following technical effects:

[0025] The operational efficiency of the UAV after its design is completed is strongly correlated with the accuracy of capturing the demand in the application scenario. Existing design methods are difficult to guarantee the matching of capacity and demand in specific application environments. By accurately inputting the demand (with accurate and complete parameters) in typical scenarios into the design stage, the efficiency of the UAV can be significantly improved in subsequent operations, typically by more than 20%.

[0026] Of course, any product implementing this invention does not necessarily need to achieve all of the technical effects described above at the same time. [Attached Image Description]

[0027] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0028] Figure 1 This is a flowchart of an overall design method for an unmanned transport aircraft provided in one embodiment of the present invention.

Detailed Implementation Methods

[0029] To better understand the technical solution of the present invention, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0030] It should be understood that the described embodiments are merely some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0031] The terminology used in the embodiments of this invention is for the purpose of describing particular embodiments only and is not intended to limit the invention. The singular forms “a,” “the,” and “the” as used in the embodiments of this invention and the appended claims are also intended to include the plural forms unless the context clearly indicates otherwise.

[0032] like Figure 1 As shown, this invention provides an overall design method for unmanned transport aircraft based on scenario analysis. The design method includes the following steps:

[0033] S1: Preset parameters of the object to be transported and environmental parameters for different scenarios;

[0034] S2: Determine the range of UAV payload parameters based on the parameters of the object to be transported and the environmental parameters in S1;

[0035] S3: Determine the UAV platform configuration based on the range of UAV payload parameters in S2;

[0036] S4: Based on the UAV platform configuration in S3, design the UAV layout and aerodynamic parameters, and simultaneously carry out the selection and design verification of the power system;

[0037] S5: Design the internal structure of the UAV based on the platform configuration in S3 and the UAV layout and aerodynamic parameters in S4.

[0038] S6: Perform a full weight and center of gravity check on the UAV whose internal structure design was completed in S5. The check results meet the preset load weight and loading position of the cargo to be transported.

[0039] S7: Perform flight control parameter tuning and ground system joint testing on the UAV that has been verified in S6, and compare it with the existing UAV's operational efficiency in the preset scenario. If it is better, the design is confirmed to be completed; if it is lower than the existing efficiency, update the parameters in design S1 and iterate and optimize again.

[0040] The parameters of the transported object in S1 include transport distance, flight altitude, weight of the object to be transported, and external volume of the object to be transported. The environmental parameters include terrain, take-off and landing conditions, communication status, support requirements, and weather conditions.

[0041] Specifically, S3 is:

[0042] When the payload parameters of the UAV are such that the transport payload weight is between 5 and 15 kg, a multi-rotor configuration should be selected.

[0043] When the payload parameters of the UAV are that the transport payload weight is between 25 and 80 kg, a compound wing configuration should be selected.

[0044] When the payload parameters of the UAV are that the transport payload is above 150kg, a fixed-wing configuration should be selected.

[0045] The UAV layout design in S4 includes the UAV wingspan, UAV length, and UAV height.

[0046] In addition to the aspects and any possible implementations described above, an implementation is further provided in which the aerodynamic shape parameter design in S4 includes the reference area, mean aerodynamic chord length, span, wing mounting angle, and horizontal tail mounting angle of the wing, horizontal tail, and vertical tail control surfaces.

[0047] The design verification in S4 specifically involves: performing full-aircraft aerodynamic characteristic calculations, wind tunnel experiments, performance verification, and flight quality calculations on the designed UAV.

[0048] The power system selection in S4 specifically involves determining the power system based on the parameters of the object to be transported under a preset scenario, and verifying the adaptability of the aerodynamic shape based on the environmental parameters under the preset scenario. The internal structure design in S5 includes the layout of internal avionics equipment and strength verification analysis of the loading equipment.

[0049] Example 1: Taking a fixed-wing unmanned transport aircraft as an example

[0050] This invention provides an overall design method for unmanned transport aircraft based on typical application scenario analysis, comprising the following steps:

[0051] Information such as payload, total system weight, operating range, flight speed, operating environment temperature range, and takeoff and landing distance under typical operating scenarios are used as calculation inputs;

[0052] For the given range mentioned above, the configuration of the unmanned aerial vehicle platform is determined, namely, a fixed-wing unmanned transport aircraft;

[0053] After determining that the UAV platform configuration is a fixed-wing unmanned transport aircraft, the aircraft lift device configuration, cargo hold layout, power system selection, internal structural devices, communication link configuration, and avionics equipment layout are selected according to the actual situation.

[0054] Based on the above information, the overall layout and shape design are carried out to determine the wingspan, length, and height of the entire aircraft. Simultaneously, the shape parameters of the wing, horizontal stabilizer, and vertical stabilizer control surfaces are calculated, including reference area, mean aerodynamic chord length, span, wing angle of attack, and horizontal stabilizer angle of attack.

[0055] After completing the above steps, perform full-aircraft aerodynamic performance calculations to determine whether the lift-drag characteristics, stability, and flight quality of the UAV under typical operating conditions meet the usage requirements.

[0056] Simultaneously, it can select the power system for the drone, determine the power system and whether it can be adapted to the aerodynamic shape based on the typical parameters of the operating scenario;

[0057] After the aerodynamic layout is designed, the internal structure is designed, the layout of the avionics equipment inside the UAV is set, and the strength verification analysis is performed based on the loaded equipment.

[0058] The next step is to check the overall weight and center of gravity of the drone to ensure that the cargo loading weight and loading position meet the performance requirements of the drone.

[0059] Conduct flight control parameter adjustments and ground system integration testing;

[0060] Finally, the efficiency of the drones is compared with that of existing drones in typical scenarios. If the efficiency is better, the project is considered complete; if it is lower than the existing efficiency, the design input parameters are updated and iterative optimization is carried out again.

[0061] The foregoing has provided a detailed description of the overall design method for an unmanned transport aircraft based on scenario analysis, as provided in the embodiments of this application. The descriptions of the embodiments above are merely for the purpose of helping to understand the method and its core ideas; furthermore, those skilled in the art will recognize that, based on the ideas of this application, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this application.

[0062] Certain terms are used in the specification and claims to refer to specific components. Those skilled in the art will understand that hardware manufacturers may use different names to refer to the same component. This specification and claims do not distinguish components based on differences in name, but rather on differences in function. The terms "comprising" and "including" used throughout the specification and claims are open-ended and should be interpreted as "comprising / including but not limited to". "Approximately" means that within an acceptable margin of error, those skilled in the art can solve the technical problem and substantially achieve the technical effect within a certain margin of error. The following descriptions in the specification are preferred embodiments for carrying out this application; however, these descriptions are for the purpose of illustrating the general principles of this application and are not intended to limit the scope of this application. The scope of protection of this application shall be determined by the appended claims.

[0063] It should also be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a product or system comprising a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a product or system. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the product or system that includes said element.

[0064] It should be understood that the term "and / or" used in this article is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, and B existing alone. Additionally, the character " / " in this article generally indicates that the preceding and following related objects have an "or" relationship.

[0065] The foregoing description illustrates and describes several preferred embodiments of this application. However, as previously stated, it should be understood that this application is not limited to the forms disclosed herein and should not be construed as excluding other embodiments. It can be used in various other combinations, modifications, and environments, and can be altered within the scope of the application concept described herein through the foregoing teachings or techniques or knowledge in related fields. Any modifications and variations made by those skilled in the art that do not depart from the spirit and scope of this application should be within the protection scope of the appended claims.

Claims

1. A method for overall design of unmanned transport vehicle based on scenario analysis, characterized in that, The unmanned transporter overall design method comprises the following steps: S1: presetting parameters of a to-be-transported object and environmental parameters under different scenarios; S2: determining an interval range of an unmanned aerial vehicle load parameter according to the parameters of the to-be-transported object and the environmental parameters in S1; S3: determining an unmanned aerial vehicle platform configuration according to the interval range of the unmanned aerial vehicle load parameter in S2; S4: performing unmanned aerial vehicle layout design and aerodynamic shape parameter design according to the unmanned aerial vehicle platform configuration in S3, and simultaneously performing power system selection and design verification; S5: performing unmanned aerial vehicle internal structure design according to the platform configuration in S3 and the unmanned aerial vehicle layout design and aerodynamic shape parameter design in S4; S6: performing full-machine weight and gravity center checking on the unmanned aerial vehicle with the internal structure designed in S5, and checking that the checking result meets preset to-be-transported object loading weight and loading position; S7: performing flight control parameter adjustment and ground system joint debugging and testing on the unmanned aerial vehicle with the checking completed in S6, and comparing the operation efficiency of the unmanned aerial vehicle with that of an existing unmanned aerial vehicle under a preset scenario, and confirming that the design is completed if the operation efficiency is better than that of the existing unmanned aerial vehicle, and updating the design and reiteratively optimizing the parameters in S1 if the operation efficiency is lower than that of the existing unmanned aerial vehicle.

2. The unmanned vehicle overall design method of claim 1, wherein, The parameters of the to-be-transported object in S1 comprise a transportation distance, a flight height, a to-be-transported object weight, and a to-be-transported object shape volume, and the environmental parameters comprise a terrain, a take-off and landing condition, a communication state, a support demand, and a meteorological condition.

3. The unmanned vehicle overall design method of claim 1, wherein, S3 is specifically: when the unmanned aerial vehicle load parameter is a transportation load weight of 5-15 kg, a multi-rotor configuration is selected; when the unmanned aerial vehicle load parameter is a transportation load weight of 25-80 kg, a compound wing configuration is selected; when the unmanned aerial vehicle load parameter is a transportation load weight of more than 150 kg, a fixed-wing configuration is selected.

4. The unmanned vehicle overall design method according to claim 3, wherein, The unmanned aerial vehicle layout design in S4 comprises a wing span, a length, and a height of the unmanned aerial vehicle.

5. The unmanned vehicle overall design method of claim 3, wherein, The aerodynamic shape parameter design in S4 comprises a reference area of a wing flat tail vertical tail rudder surface, an average aerodynamic chord length, a span length, a wing installation angle, and a flat tail installation angle.

6. The unmanned vehicle overall design method of claim 1, wherein, The design verification in S4 is specifically: performing full-machine aerodynamic characteristic calculation, wind tunnel experiment, performance checking, and flight quality calculation on the designed unmanned aerial vehicle.

7. The unmanned vehicle overall design method of claim 1, wherein, The power system selection in S4 is specifically: determining a power system according to the parameters of the to-be-transported object under a preset scenario, and verifying the adaptability of the aerodynamic shape according to the environmental parameters under the preset scenario.

8. The unmanned vehicle overall design method of claim 1, wherein, The internal structure design in S5 comprises internal avionics equipment layout and strength checking analysis on a loading device.

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