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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars Because the wings of the Entomopter are constantly moving during flight, the output of the array will vary continuously. The total wing motion is 150°, +75° (up from the horizontal), and -75° (down from the horizontal). The curves in Figures 3-178 and 3-179 represent the output power of the wing at these three locations. The power output is given as a function of time of day for one complete day cycle. The total usable power available per stroke is given by the average power curve. This curve represents the average power available throughout a wing stroke. The output power for the total array can be obtained by multiplying the power level on the graphs (11 or 12) by 4. The output is based on a solar intensity of 590 W/m 2 and an atmospheric attenuation of 15%. The mass of the solar array, based on the CuInSe 2 array, would be 0.014 kg. As can be seen from Figures 3-173 through 3-177, the available power changes considerably as the latitude and time of year change. This is due to the inclination of Mars and the change in incident angle on the array due to the change in latitude. For the data shown, it was assumed that the Entomopter was flying east to west. The average output power per wing stroke for the total array (four panels) is shown in Figure 3- 180. The average output power can vary greatly depending on latitude and time of year. Figure 3-180 represents the extremes in average output power, the equator and near the North Pole, at the time of summer solstice. The time of year, especially at higher latitudes, can greatly effect the array output. For example, during the winter at the 85° North latitude there would be no sunlight and therefore no array output for extended periods of time. The watthours provided by the solar array for a day period based on the curves shown in Figure 3-180 are as follows: • Equator at Solstice 55.71 W-h • 85° North Latitude at Solstice 107.62 W-h This is the amount of energy available from the solar array for the given day. 3.6.6 Lithium Batteries The energy storage component of the system will be used to provide power when the solar array is either obscured from sunlight (either by being shadowed or during nighttime) or when the power demand is greater than what the array can provide. Presently, lithium polymer batteries hold the most promise for a lightweight rechargeable system. Lithium batteries can be configured in virtually any prismatic shape and can presently be made thinner than 0.039" (1 mm), to fill virtually any space efficiently. This would be a great benefit in entomopter design, because it allows the battery to be placed almost anywhere in the vehicle. It also presents the possibility of making the wing the complete power system by having the batteries within the wing and the solar cells on its surface. One potential lithium battery technology that may address this application are thin film lithium batteries. Lithium ion thin film batteries are a relatively new technology that is readily finding applications in industry and commercial products, including implantable medical devices, remote sensors, transmitters, smart cards, CMOS-SRAM memory, and other electronic devices. These batteries are rechargeable, lightweight, and flexible. They can be configured in any series/paral- 216 Phase II Final Report
Chapter 3.0 Vehicle Design 3.6 Power System lel combination to meet power system requirements and they are capable of rapid charging, obtaining 90% of their capacity in less than 20 minutes. For the Entomopter concept, they will be utilized as a means of storing the solar power from the solar arrays. The batteries will be discharged as needed to provide power for any of the onboard electronics and sensors. The batteries have the capability to provide high pulse currents ideal for discrete short duration power loading, such as burst communications transmissions. There are a number of different types of lithium ion thin film batteries. These differ in the cathode material used (such as magnesium oxides, cobalt oxides and yttrium oxide). The characteristics of thin film lithium ion batteries are well suited for use in the Entomopter power system. The batteries have long cycle lifetimes and can be charged and discharged thousands of times with little loss in capacity. This makes them applicable to long duration flights. They have a long shelf life with little self-discharge over a period of years, allows them to be fully charged and stored during interplanetary transit. In addition, they can operate over a wide range of temperatures, which enables them to operate under a wide range of environmental conditions. Lithium ion thin film batteries are constructed on a solid substrate material. Common substrates are alumina, glass, silicon, and plastic, but virtually any solid-surface material can serve as the substrate. The layers that make up the battery (current collectors, cathode, electrolyte, and anode) are deposited using standard sputtering or evaporation techniques. Batteries produced today are on the order of 4 mm thick or less. The ability to use different substrate material allows great flexibility in battery design. It may be possible to use the back side of the solar array or the composite wing structure itself as the substrate material for the battery, thereby further integrating the components. Specifications for present state-of-the-art lithium polymer batteries are given in Table 3-25. 217
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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 1.0 Introduction 1.2 Origin
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Chapter 1.0 Introduction 1.3 Missio
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1.3.3.1 Surface Imaging The Entomop
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Chapter 2.0 Entomopter Configuratio
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Chapter 3.0 Vehicle Design 3.1 Wing
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3. Density: 1.40E-2 kg/m 3 4. Press
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Chapter 3.0 Vehicle Design 3.4 Reci
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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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