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A method for calculate nonlinear load of flying-wing unmanned aerial vehicle

A load calculation and nonlinear technology, applied in the field of flying-wing UAV, can solve the problem that the nonlinear load calculation method of flying-wing UAV is not disclosed.

Pending Publication Date: 2019-03-12
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, there is no public non-linear load calculation method and generalized design for flying-wing UAVs in China.

Method used

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  • A method for calculate nonlinear load of flying-wing unmanned aerial vehicle
  • A method for calculate nonlinear load of flying-wing unmanned aerial vehicle
  • A method for calculate nonlinear load of flying-wing unmanned aerial vehicle

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0054] A non-linear load calculation method for flying wing UAV, such as Figure 6 As shown, it mainly includes the following steps:

[0055] Step S101: Solving the flight attitude parameters: based on the aerodynamic nonlinear coefficients, the multi-degree-of-freedom coupling flight dynamics simulation model is used to calculate the aerodynamic force and dynamic flight of the aircraft, and at the same time establish the objective function, and use the optimization algorithm to solve the problems that do not meet the requirements. The results of the flight attitude parameters are optimized, and the output flight attitude parameters are used as the input of the nonlinear concentrated load calculation;

[0056] Step S102: Calculation of non-linear concentrated loads: the aerodynamic data of the geometric shape components of the aircraft, the flight attitude parameters, and the mass data of the components are used as input, and the aerodynamic loads and inertia of the components...

Embodiment 2

[0060] This embodiment is optimized on the basis of Embodiment 1. In the non-linear load calculation method based on the rudder surface coefficient increment in the step S102, the flight load after the balance of the whole machine and components should be the aerodynamic force that just produces the flight attitude. ; The data interface is the nonlinear coefficient of the stabilizer base and the nonlinear increment of each rudder surface. The calculation formula of the load of the components is as follows:

[0061] C i Wing = C i Wing (M, α, δ=0) + ΔC i Wing (M, α, δ i )+..+ΔC n Wing (M, α, δ n )

[0062] +C i Wing rudder i(M, α, δ i )+·..+C i Wing rudder n(M, α, δ n )

[0063] Among them, M, α, δ 1 ,δ 2 ,,,δ n as the dependent variable.

[0064] The establishment of nonlinear flight load calculation method mainly includes the following two aspects:

[0065] (1) Logical design of flight load calculation of the whole aircraft and components:

[0066] Such as i...

Embodiment 3

[0073] The present embodiment optimizes on the basis of embodiment 2, mainly comprises the following steps:

[0074] 1. Analysis of the aerodynamic characteristics of multiple control surfaces in the aerodynamic layout of the flying wing UAV

[0075] The aerodynamic layout of a typical flying-wing multi-control surface UAV is shown in figure 1 , the aerodynamic characteristics and rudder effect increment of the UAV with flying wing layout have obvious nonlinear characteristics. When the aircraft performs extreme maneuvers, there will often be a nonlinear section with a large angle of attack and a large rudder deflection angle. See figure 2 .

[0076] 2. Establish a high-precision nonlinear multi-degree-of-freedom aerodynamic coefficient mathematical model

[0077] In the step S101, a nonlinear multi-degree-of-freedom aerodynamic coefficient mathematical model is established, wherein the longitudinal aerodynamic coefficient calculation formula is as follows:

[0078] C i =...

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Abstract

The invention discloses a non-linear load calculation method of a flying wing unmanned aerial vehicle, which comprises the steps of solving flight attitude parameters. A multi-degree-of-freedom coupling flight dynamics simulation model is adopted for aerodynamic and dynamic flight calculation of the aircraft based on aerodynamic non-linear coefficients in solving the flight attitude parameters, Atthe same time, an objective function is established to optimize the flight attitude parameters which do not meet the requirements by using the optimization algorithm, and the output flight attitude parameters are used as the input of the nonlinear concentrated load calculation. As for that aerodynamic non-linearity characteristic of the whole aircraft of the unmanned aerial vehicle (UAV), the invention adopt a flight dynamics simulation model of multi-degree-of-freedom coupling to solve the flight attitude parameters of three-axis couple non-linearity on the basis of the aerodynamic non-linearity coefficient; Thus, the nonlinear load calculation of flying-wing UAV is realized, which has good practicability.

Description

technical field [0001] The invention belongs to the technical field of flying-wing drones, and in particular relates to a nonlinear load calculation method of flying-wing drones. Background technique [0002] As the basis for the design of aircraft structural strength, flight load determines the flight safety and structural weight of the aircraft and affects the flight performance of the aircraft. Effective and accurate calculation results of flight loads can reduce the structural weight and improve the safety of the aircraft flight structure. Aircraft flight performance and survivability. [0003] The flight load calculation of conventional layout UAVs generally uses a simplified flight dynamics model with limited degrees of freedom. When calculating the aerodynamic load of components and the whole machine, the aerodynamic derivative incremental linear solution of the rudder surface components or the simple airfoil components are used. Calculation method of the total coeff...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F2119/06G06F30/20Y02T90/00
Inventor 赵利霞唐克兵李伟郭文夏生林谢欢李涛
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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