Phase II Final Report - NASA's Institute for Advanced Concepts

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars From Figures 3-16 and 3-17, and Table 3-4 it can be seen that the greatest benefit in reducing the wing mass while maintaining the desired deflection is by utilizing a hollow wing. 2.5 Thickness = 2.6 cm 2 Thickness = 2.4 cm to 0.5 cm Wing Section Mass (kg) Wing Section Mass 9kg) 1.5 1 0.5 Thickness = 1.9 cm (a = 90%, b = 80%) Thickness = 1.6 cm to 0.5 cm (a = 95%, b=85%) 0 Solid Core No Taper Solid Core Taper Hollow Core No Taper Hollow Core Taper Structure Configuration Figure 3-16: Total Mass for Various Wing Structural Configurations 0.04 0.035 0.03 Solid, No Taper Solid, With Taper Hollow, No Taper Hollow, With Taper 0.025 0.02 0.015 0.01 0.005 0 Radius (m) 0 0.1 0.2 0.3 0.4 0.5 0.6 Raidus (m) Figure 3-17: Mass Distribution for Various Structural Geometries Phase II Final Report 58
Chapter 3.0 Vehicle Design 3.2 Wing Motion and Structure Analysis Table 3-4: Wing Geometry and Mass Thickness (m) (Root to Tip) 0.026 to 0.026 0.024 to 0.005 0.019 to 0.019 0.0165 to 0.005 Interior Ellipse as a Percent of Outer Wing Dimensions Solid: a = 0%, b = 0% Solid: a - 0%, b = 0% a = 90% b = 80% a = 95% b = 85% Total Wing Section Mass (kg) 2.46 1.52 0.51 0.214 Maximum Tip Deflection (m) 0.015 0.015 0.015 0.015 The tapering of the wing also had an effect but it wasn't as dramatic. The maximum loading point on the wing, used to generate the results given above, occurs when the wing is at its maximum downward position. In this position the wing sees both a maximum acceleration load as well as the gravitational load both working in the downward direction. This maximum loading profile along the wing is shown in Figure 3-18 for the base flight conditions given in Table 3-3 and the hollow tapered wing geometry shown in Table 3-4. The radial loading profile is shown in Figure 3-19. Structurally the radial loading is not significant and does not affect the wing structural design. The structural geometry will not effect the maximum loading point for the wing. It will however have an effect on the absolute value of the loading experienced. Therefore the loading profile and point of maximum loading will be consistent for each structural geometry considered. The hollow tapered geometry produced the lightest wing for a given amount of deflection. Based on these results this geometry configuration will be the baseline geometry for the wing. This baseline, as listed in Table 3-4, consists of a wing taper from 0.0165 m at the root to 0.005 m at the tip and an inner ellipse length “a” equal to 95% and thickness “b” equal to 85% of the outer ellipse dimensions respectively. For this hollow tapered geometry, the loading profile along the wing length is shown in Figure 3-20. Also shown in this figure are the subsequent shear loading and bending moment curves for this wing geometry. Variations in the wing structural geometry from the baseline values were also examined. This was done to determine what effect each of the parameters had on the wing mass and tip deflection. The results of these variations are shown in Figures 3-21 through 3-24. Figures 3-21 and 3- 22 show the effect changing the dimensions of the hollow elliptical core of the wing has on the wing section mass and wing tip deflection. As the hollow core dimensions are increased the wing section mass decreases linearly with both dimensions (a and b) as should be expected. The tip deflection is greatly effected by variations in the thickness (b) of the core ellipse. This is because the moment of inertia for the wing is greatly dependent on the ellipse thickness. From this curve it can be seen that a minimum tip deflection occurs at a hollow core thickness of approximately 85% of the overall wing thickness. This is consistent with the design point that was chosen. 59
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Planetary Exploration Using Biomime
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Table of Contents Table of Contents
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List of Tables List of Tables Table
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List of Figures List of Figures Fig
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List of Figures Figure 3-54: Pressu
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List of Figures Figure 3-138: Stere
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List of Figures Figure 4-24: Averag
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List of Contributors List of Contri
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Executive Summary Executive Summary
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Chapter 1.0 Introduction Chapter 1.
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Chapter 1.0 Introduction Figure 1-2
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Chapter 1.0 Introduction 1.1 Histor
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Chapter 3.0 Vehicle Design 3.3 Wing
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Chapter 3.0 Vehicle Design 3.5 Fuel
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Chapter 4.0 Entomopter Flight Opera
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Chapter 5.0 Potential Payload Funct
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Chapter 6.0 Media Exposure 6.1 Intr
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Chapter 6.0 Media Exposure 6.3 Onli
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Chapter 6.0 Media Exposure 6.6 Spec
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Chapter 7.0 Conclusion Chapter 7.0
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Appendix A: Mars Atmosphere Data JP
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Appendix A: Mars Atmosphere Data Ge
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Appendix A: Mars Atmosphere Data Ge
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Appendix A: Mars Atmosphere Data Ma
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Appendix B: Sizing Results Appendix
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Appendix B: Sizing Results 30 Wing
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Appendix B: Sizing Results 16 Wing
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Appendix B: Sizing Results Length 0
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Appendix B: Sizing Results Lenght 0
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Appendix C: List of References Appe
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Appendix C: List of References 41.
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Phase II Final Report - NASA's Institute for Advanced Concepts

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