# Research on the Flight Performance of Biomimetic Moth Based on Flapping Function Control
## 5 Conclusions  
This paper constructs a periodic function composed of two sine functions with different frequencies as the flapping function for the control of biomimetic flapping-wing aircraft. Through the creation of a rigid wing flapping lift computation model, the critical parameters within the flapping function that influence lift--the flapping amplitude, the flapping frequency, and the med-position angles--have been isolated, and their effects on lift have been initially analyzed. To verify the accuracy and practicality of the modeling analysis results, two parts of work are carried out: simulation calculation and flight experiment. On the one hand, XFlow software is used for simulation calculation to verify and expand the results of modeling analysis; on the other hand, through biomimetic mechanism research, a biomimetic moth flapping-wing aircraft prototype for experiments is designed and manufactured, and a series of flight experiments such as lift test are carried out, and the flapping function is applied to the control of the aircraft. The comparison between the simulation and experimental results is shown in Table 13. Combining simulation and experiment, the impact of key parameters on the flight control of flapping-wing aircraft is as follows:  
1. Flapping amplitude and flapping frequency are the key factors affecting the generation of lift of the flapping-wing aircraft. Increasing the flapping amplitude and flapping frequency can significantly improve the flight performance of the flapping-wing aircraft;
2. The difference in flapping amplitude between the left and right wings can make the flapping-wing aircraft turn, and the larger the amplitude difference, the tighter the turning radius;
3. The impact of the initial mid-position angle on the lift is the same as the results of the simulation calculation analysis. Increasing the mid-position angle can slightly improve the aerodynamic performance;
4. During flight, the change in the absolute value of the mid-position angle has the same impact on lift as the calculation results of the lift calculation model. At the same time, it will also affect the flight altitude of the flapping-wing aircraft. Increasing the absolute value of the mid-position angle can make the flapping-wing aircraft pitch forward and dive, and the flight altitude will decrease; decreasing the absolute value of the mid-position angle can make the flapping-wing aircraft pitch backward and climb, and the flight altitude can rise for a short time. The research shows that by changing the key parameters and adjusting the flapping function of the two wings, the flight control of the flapping-wing aircraft can be realized. Furthermore, simultaneously adjusting multiple flapping function parameters can make the control of the aircraft more stable. For example, although decreasing the absolute value of the mid-position angle alone can make the flapping-wing aircraft climb for a short time during flight, the insufficient lift will quickly lead to stall and fall while simultaneously increasing the flapping amplitude and flapping frequency can make up for the lack of lift, so that the flight altitude can rise and keep flying stably. For another example, when turning the flapping-wing aircraft by using the amplitude difference alone, the flapping-wing aircraft tends to descend while simultaneously adjusting the absolute value of the mid-position angle to decrease and the flapping frequency to increase, which can offset this descending trend. In general, this study clarifies the key control parameters of flight control, which is helpful to optimize the existing control strategy of the flapping-wingaircraft and improve the maneuverability and controllability of the aircraft; at the same time, the real-time controllable biomimetic flapping-wing prototype also provides reliable, practical support for the design and manufacturing of practical flapping-wing aircraft.