傳統(tǒng)固定翼飛行器為滿足不同條件飛行的需求采用了包容性的設計方案,使得飛行器在不同飛行環(huán)境下的性能均不能處于最優(yōu)狀態(tài)。為滿足多任務飛行的需求,近年來國內外基于仿生學角度提出多種隨外界環(huán)境變化而相應改變自身氣動布局的變體飛行器,并對其進行靜力學、動力學以及氣動性能等方面分析研究�；诜律鷮W原理分析多種可變構型,提出一種新型仿脊柱弦向可變形機翼結構（簡稱ACM翼）,并配備不可逆驅動系統(tǒng);該機翼結構可以隨外界環(huán)境的變化產(chǎn)生相應的變形,可以應用于后緣襟翼的設計。弦向可變形機翼結構主要包括剛性翼梁、梁式脊柱、支撐桁條、預拉伸蒙皮以及驅動系統(tǒng)五個部分,其中對比多種驅動方式氣動系統(tǒng)采用電機驅動碳纖維腱滑輪傳動的方式實現(xiàn)致動。為消除驅動過程中蒙皮屈曲褶皺問題,結合有限元仿真分析軟件ANSYS,進行了預拉伸蒙皮力學特性分析;在預拉伸蒙皮的基礎上,結合有限元仿真分析軟件ANSYS,分析機翼撓度與驅動力的關系,評估變形驅動所需力矩。結合流體分析軟件Fluent,對比基礎NACA 0012機翼、帶襟翼NACA 0012機翼以及仿脊柱可變形機翼結構的升阻特性,分析三種機翼氣動效率。模擬不同飛行速度、不同攻角、不同... 

【文章來源】：哈爾濱工業(yè)大學黑龍江省 211工程院校 985工程院校

【文章頁數(shù)】：96 頁

【學位級別】：碩士

【文章目錄】：
摘要
Abstract
Nomenclature
Chapter 1. Introduction
    1.1 Background and motivation
    1.2 Research significance
    1.3 Literature review
        1.3.1 History
        1.3.2 Current scenario
        1.3.3 Morphing types
        1.3.4 Advantages of morphing wing
    1.4 Main research content
    1.5 Overview
Chapter 2. Active Camber morphing Concept
    2.1 Morphing design and analyzation criteria
        2.1.1 Analysis criterion of morphing
        2.1.2 Key component of the structure
    2.2 Aerostructure shape optimization
        2.2.1 Morphing leading edge
        2.2.2 Morphing trailing edge
    2.3 Probable design configuration
        2.3.1 Initial design configuration of active camber morphing
        2.3.2 Probable actuation device
        2.3.3 Elastomeric matrix composite polymer skin
        2.3.4 Material screening establishment
    2.4 Summary
Chapter 3. Modeling of ACM spine
    3.1 Theoretical approach of the mechanism
        3.1.1 Wing size estimation
        3.1.2 Actuation mechanism determination
    3.2 Detail design of ACM spine
        3.2.1 Spar
        3.2.2 Beam Spline
        3.2.3 Stringers
        3.2.4 Trailing edge strip
        3.2.5 Actuation system
        3.2.6 Skin
    3.3 Pre-tensioning mechanism
        3.3.1 Per-tensioning procedure
        3.3.2 Pre-tensioning analysis
    3.4 Mechanism analysis
        3.4.1 Data mapping of the initial stresses
        3.4.2 Analysis of the actuation system
    3.5 Summary
Chapter 4. Analysis and evaluation of ACM spine
    4.1 Aerodynamic structure modeling
        4.1.1 General aerodynamic modeling
        4.1.2 Estimation of turbulence model
    4.2 Fluent aerodynamic performance analysis procedure
        4.2.1 Importing and meshing the mechanism
        4.2.2 Key parameter selection
    4.3 Aerodynamic simulation results
        4.3.1 Analyzation of NACA 0012 airfoil
        4.3.2 Pressure and velocity contour
        4.3.3 Effect of velocity
        4.3.4 Effect of angle of attack （α）
    4.4 Summary
Conclusion
結論
Recommendation
Reference
Acknowledgement
APPENDIXES
    Appendix A – Velocity analysis result data
    Appendix B – AOA analysis result data
    Appendix C – MATLAB Codes
        Ⅰ. Lift polar
        Ⅱ. Drag polar
        Ⅲ. Lift efficiency



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