A body structure optimization design method of a flying wing layout unmanned aerial vehicle group
A drone and layout technology, applied in computing, special data processing applications, instruments, etc., to achieve the effect of expanding usage and types and improving reliability
Pending Publication Date: 2019-06-18
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS +2
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[0004] Compared with the traditional single-type unmanned aerial vehicle body structure optimization design, the present invention has the following advantages: (1) Utilizes the multidisciplinary and multi-objective optimization method, common components are shared among the various models of the unmanned aerial vehicle family, and the common modules and problems in the initial stage are solved. The definition of optimization parameters for special modules, as well as the data transfer of various constraints and parameters in the optimization process of different types of UAVs; To ensure the reliability of the optimization method, it is beneficial to expand the use and type of flying-wing layout aircraft products, to meet different mission requirements, and to give an effective flying-wing layout UAV family structure optimization design method
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[0012] A body structure optimization design method for a flying-wing layout unmanned aerial vehicle family, comprising the following steps:
[0013] Step 1. According to the design requirements of the UAV family, determine the overall configuration of the UAV family, and divide the structural components of the general module and the special module respectively.
[0014] It is determined that the UAV family contains two configurations, namely, the strike UAV with a small aspect ratio and the reconnaissance UAV with a large aspect ratio. The wings act as dedicated modules. By matching the wings of different lengths on the fuselage platform to complete the corresponding task requirements, the schematic diagram of the scheme is as follows: figure 1 shown.
[0015] Step 2, according to the overall design plan, extract the key geometric parameters, and use CATIA secondary development technology to establish the aerodynamic shape parametric models of strike and reconnaissance UAVs ...
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The invention provides a body structure optimization design method of a flying wing layout unmanned aerial vehicle group. The method comprises: dividing the configuration of an unmanned aerial vehiclegroup into a general module and a special module, wherein the general module comprises the structural size of a fuselage component shared by different types of unmanned aerial vehicles, and the special module comprises the structural sizes of wing components of different types of unmanned aerial vehicles; setting aerodynamic configuration parameterization models of different types of unmanned aerial vehicles and stress types of the bearing components, generating a structural finite element model of the unmanned aerial vehicle and carrying out static analysis; and carrying out general module and special module optimization on the structure finite element model of the unmanned aerial vehicle to select an optimal design scheme.
Description
technical field [0001] The invention relates to a structure design technology of an unmanned aerial vehicle, in particular to a body structure optimization design method of an unmanned aerial vehicle family with flying wing layout. Background technique [0002] A UAV family is a collection of UAV models, in which each model has common components or subsystems, but each model has different performance and use requirements to meet different mission requirements. The drone family strategy can greatly shorten the development cycle of developing different types of drones, which is conducive to reducing maintenance costs in the later stage and has strong adaptability to market demand. The structural optimization method of a single type of flying-wing layout UAV is relatively mature, but the structural design optimization method of the modular flying-wing layout UAV family needs to be further explored. Contents of the invention [0003] The object of the present invention is to ...
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IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 尹海莲岳志星王宇余雄庆
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS