Design of a Hand-Launched Solar-Powered Unmanned Aerial Vehicle (UAV) System for Plateau
Abstract
:1. Introduction
2. Conceptual Design Method
2.1. Power of Level Flight
2.2. Solar Energy Obtained during the Day
2.3. Weight Estimation Model
3. Detailed Design
3.1. Layout Design
3.2. Aerodynamic Design
3.3. Structure and Avionics
4. UAV Flight Control
4.1. Lateral-Directional Nonlinear Dynamic Model
4.2. Analysis of Stability and Flight Quality
4.3. Analysis of Lateral-Directional Maneuverability
4.4. Successive Loop Closure Flight Control
4.4.1. Longitudinal Control Law
4.4.2. Lateral-Directional Control Law
5. Field Experiment
5.1. Experiment Environment
5.2. Flight Parameters of HighAltitude Experiment
6. Conclusions
Author Contributions
Funding
Conflicts of Interest
References
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Parameter | Value | Unit | Description |
---|---|---|---|
0.8 | - | Lift coefficient | |
0.04 | - | Drag coefficient | |
950 | [W/m2] | Maximum irradiance | |
0.89 | Temperature influence factor (5 °C) | ||
290 | [Wh/kg] | Energy density of Li-ion battery | |
0.29 | [kg/m2] | Mass density of solar cells | |
0.13 | [kg/m2] | Mass density of encapsulation | |
0.0042 | [kg/W] | Mass to power ratio of MPPT | |
0.008 | [kg/W] | Mass to power ratio of propulsion group | |
0.44/9.81 | [kg/m3] | Structural mass constant | |
0.11 | [kg] | Mass of autopilot system | |
0.8 | - | Efficiency of step-down converter | |
0.2 | - | Efficiency of solar cells | |
0.9 | - | Efficiency of the curved solar panels | |
0.95 | - | Efficiency of battery charge | |
0.95 | - | Efficiency of motor controller | |
0.95 | - | Efficiency of battery discharge | |
0.9 | - | Efficiency of motor | |
0.97 | - | Efficiency of MPPT | |
0.85 | - | Efficiency of propeller | |
1.5 | [W] | Power of autopilot system | |
3.1 | - | Airframe mass wingspan exponent | |
−0.25 | - | Airframe mass aspect ratio exponent |
Parameter | Value | Unit | Description |
---|---|---|---|
0.1 | [kg] | Payload mass | |
0.85 | - | Irradiance margin factor | |
2 | [W] | Payload power consumption | |
0.78 | [kg/m3] | Air density (4500 m) | |
14.3 | [h] | Summer day duration (34.3° N) |
Parameter | Value | Unit | Description |
---|---|---|---|
AR | 10.6 | - | Aspect ratio |
b | 3.2 | m | Wingspan |
Swin | 0.934 | m2 | Wing area |
Sele | 0.06 | m2 | Horizontal tail area |
Svert | 0.08 | m2 | Vertical tail area |
Srud | 0.017 | m2 | Rudder area |
VH | 0.21 | - | Horizontal tail volume |
VV | 0.28 | - | Vertical tail volume |
m | 2.9 | kg | Total mass |
mbat | 1.2 | kg | Battery mass |
mMpld | 0.6 | kg | Max payload mass |
V | 10 | m/s | Flight speed |
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Zhao, X.; Zhou, Z.; Zhu, X.; Guo, A. Design of a Hand-Launched Solar-Powered Unmanned Aerial Vehicle (UAV) System for Plateau. Appl. Sci. 2020, 10, 1300. https://doi.org/10.3390/app10041300
Zhao X, Zhou Z, Zhu X, Guo A. Design of a Hand-Launched Solar-Powered Unmanned Aerial Vehicle (UAV) System for Plateau. Applied Sciences. 2020; 10(4):1300. https://doi.org/10.3390/app10041300
Chicago/Turabian StyleZhao, Xin, Zhou Zhou, Xiaoping Zhu, and An Guo. 2020. "Design of a Hand-Launched Solar-Powered Unmanned Aerial Vehicle (UAV) System for Plateau" Applied Sciences 10, no. 4: 1300. https://doi.org/10.3390/app10041300
APA StyleZhao, X., Zhou, Z., Zhu, X., & Guo, A. (2020). Design of a Hand-Launched Solar-Powered Unmanned Aerial Vehicle (UAV) System for Plateau. Applied Sciences, 10(4), 1300. https://doi.org/10.3390/app10041300