Technology Research On Anti-UAV Warhead Structure Based On Carbon Fiber Winding

The development of UAV technology is changing with each passing day.However,many “black flying” phenomena have been brought along.They threaten military,personal privacy,economic,public security and other areas,and have seriously affected air traffic order and social security.Therefore,the development of man-machine devices is extremely important.According to the literature and the reports,the existing methods of anti-UAV are mainly based on kinetic energy strikes,laser irradiation,and other hard damages.However,there are few reports on soft damage methods.In this paper,the soft damage method based on carbon fiber filament winding UAV is studied.The main research contents are as follows:(1)Through a large number of literature and reports on domestic and foreign UAV and anti-UAV technologies,know the research status of UAV structure and anti-UAV devices.Meanwhile,according to the existing problems,the research program for this paper is established.(2)According to the system configuration of the quad-rotor aircraft,the vulnerability analysis of the multi-rotor UAV was carried out,and the feasibility of the method of using fiber filament wound UAV propeller was obtained.On this basis,the overall design of the warhead of the low incidental soft damage anti-UAV system is carried out,and the choice of the kill element drive method,the arrangement structure of the driver and the kill element are mainly designed in detail.(3)Make some basic assumptions for the features of kill element.,and a kill element flight trajectory model was established to simulate the flight status of the kill element in the air.At the same time,the damage area formed by the kill element space was analyzed.(4)According to the overall scheme design and the mathematical model established above,the ABAQUS finite element analysis software was used to simulate the process of fiber filament winding UAV propeller,and the cross section shape,length,and curtain density of the fiber filament were analyzed.And the influence of propeller winding efficiency and conclusions are drawn:(1)From the perspective of the propeller velocity drop,the cross-sectional shape of fiber filament has almost no influence on the propeller winding efficiency.(2)As the length of fiber filament increases,the entanglement efficiency of the propeller is better.(3)The denser the density of the fiber curtain,the better the propeller winding performance.(5)Adopt the exhaustive method,the finite element software was used to simulate and analyze the winding efficiency of UAV propeller with the fiber filament length and the density of the fiber screen curtain.And the results show that under the condition that the propeller rotation speed was 88r/s and the rectangular section fiber filament was selected.The longest of the filaments and the best density of the fiber screens for the UAV propeller windings were 990 mm and 18,respectively.At the same time,the effect of three factors on the winding efficiency of the propeller from the fitted linear equation was ranked as follows: density of fiber screen,length of fiber filaments,and cross-sectional shape of filaments.The conclusion of the study can provide a theoretical reference for the engineering design of soft-injured anti-UAV products.