Effect of Passive Body Deformation of Hawkmoth on Flight Stability

2013 ◽  
pp. 287-294
Author(s):  
Ryusuke Noda ◽  
Masateru Maeda ◽  
Hao Liu
Keyword(s):  
Flight Stability

scholarly journals A Numerical Analysis of Dynamic Flight Stability of Hawkmoth Hovering

2009 ◽  
Vol 4 (1) ◽  
pp. 105-116 ◽  
Author(s):  
Na GAO ◽  
Hikaru AONO ◽  
Hao LIU
Keyword(s):  
Numerical Analysis ◽  
Flight Stability

Lateral dynamic flight stability of hovering insects: theory vs. numerical simulation

2012 ◽  
Vol 28 (1) ◽  
pp. 221-231 ◽  
Author(s):  
Yan-Lai Zhang ◽  
Jiang-Hao Wu ◽  
Mao Sun
Keyword(s):  
Numerical Simulation ◽  
Flight Stability

scholarly journals Flight Stability Analysis of a Symmetrically-Structured Quadcopter Based on Thrust Data Logger Information

Symmetry ◽  
2018 ◽  
Vol 10 (7) ◽  
pp. 291 ◽  
Author(s):  
Endrowednes Kuantama ◽  
Ioan Tarca ◽  
Simona Dzitac ◽  
Ioan Dzitac ◽  
Radu Tarca
Keyword(s):  
Flight Control ◽  
Data Retrieval ◽  
Time Signal ◽  
Data Logger ◽  
Rotational Angle ◽  
Flight Stability ◽  
Axis Position ◽  
Parallel Axis ◽  
The Stability ◽  
Speed Adjustment

Quadcopter flight stability is achieved when all of the rotors–propellers generate equal thrust in hover and throttle mode. It requires a control system algorithm for rotor speed adjustment, which is related with the translational vector and rotational angle. Even with an identical propeller and speed, the thrusts generated are not necessarily equal on all rotors–propellers. Therefore, this study focuses on developing a data logger to measure thrust and to assist in flight control on a symmetrically-structured quadcopter. It is developed with a four load cells sensor with two-axis characterizations and is able to perform real-time signal processing. The process includes speed adjustment for each rotor, trim calibration, and a proportional integral derivative (PID) control tuning system. In the data retrieval process, a quadcopter was attached with data logger system in a parallel axis position. Various speeds between 1200 rpm to 4080 rpm in throttle mode were analyzed to determine the stability of the resulting thrust. Adjustment result showed that the thrust differences between the rotors were less than 0.5 N. The data logger showed the consistency of the thrust value and was proved by repeated experiments with 118 s of sampling time for the same quadcopter control condition. Finally, the quadcopter flight stability as the result of tuning process by the thrust data logger was validated by the flight controller data.

Optimal wing hinge position for fast ascent in a model fly

2018 ◽  
Vol 849 ◽  
pp. 498-509
Author(s):  
R. M. Noest ◽  
Z. Jane Wang
Keyword(s):  
Stability Analysis ◽  
Body Length ◽  
Weak Dependence ◽  
The Body ◽  
Simplified Model ◽  
Centre Of Mass ◽  
Flight Stability ◽  
Hinge Position ◽  
Stroke Amplitude ◽  
Aerodynamic Lift

It was thought that the wing hinge position can be tuned to stabilize an uncontrolled fly. However here, our Floquet stability analysis shows that the hinge position has a weak dependence on the flight stability. As long as the hinge position is within the fly’s body length, both hovering and ascending flight are unstable. Instead, there is an optimal hinge position, $h^{\ast }$, at which the ascending speed is maximized. $h^{\ast }$ is approximately half way between the centre of mass and the top of the body. We show that the optimal $h^{\ast }$ is associated with the anti-resonance of the body–wing coupling, and is independent of the stroke amplitude. At $h^{\ast }$, the torque due to wing inertia nearly cancels the torque due to aerodynamic lift, minimizing the body oscillation thus maximizing the upward force. Our analysis using a simplified model of two coupled masses further predicts, $h^{\ast }=(m_{t}/2m_{w})(g/\unicode[STIX]{x1D714}^{2})$. These results suggest that the ascending speed, in addition to energetics and stability, is a trait that insects are likely to optimize.

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