11 results about "Insect wing" patented technology

The invention discloses an insect flapping frequency inversion method based on initial phase calculation, and relates to the technical field of radar measurement. The method comprises the following steps: establishing an insect flapping motion radar echo model containing an amplitude initial phase and a phase initial phase, and obtaining a micro-motion signal from collected insect echoes based on the insect flapping motion radar echo model to generate a micro-Doppler spectrogram; based on the micro-Doppler spectrogram, calculating an initial phase value of the phase of the insect flapping wing, and based on the initial phase value, constructing a phase compensation factor to obtain a flapping wing parameter plane; and detecting an energy peak value in the flapping parameter plane based on the phase compensation factor, and determining the flapping frequency of the insect based on the position of the energy peak value. According to the method, the phase initial phase and the amplitude initial phase are introduced, the double physical processes of wing movement and body micro movement during insect flapping are restored, a radar echo model is highly matched with a real signal generation mechanism, errors are reduced, and the anti-interference capability is improved.

The utility model discloses a bionic insect lamp which comprises an insect-shaped shell, opposite shell sliding grooves are formed in the side faces of the two sides of the inner side of the shell respectively, a swing rod capable of swinging up and down in the shell is arranged in the middle of the shell, a sector gear is arranged at the end, located on the inner side of the shell, of the swing rod, and sliding blocks are arranged in the shell sliding grooves. Racks meshed with the sector gears are arranged on the sliding block, an eccentric transmission disc and a motor are sequentially arranged on the rear side of the sliding block in the shell, wings are connected to the end, located on the outer side of the shell, of the swing rod, wing lamp strips are arranged in the wings, antenna lamp strips extending forwards are arranged at the head of the shell, and the motor drives the eccentric transmission disc to rotate. The sliding block drives the swing rod to swing, the swing rod drives the wings to swing, the swing flying action of the insect wings is simulated, the overall attractiveness and vividness are improved, meanwhile, the internal overall structure is greatly simplified, the number of parts is reduced, production and assembly are facilitated, and cost is greatly reduced.

The invention relates to an energy collection structure based on insect flapping. The energy collection structure comprises a piezoelectric ceramic energy collection module, a displacement amplification structure and a flexible piezoelectric film structure, the piezoelectric ceramic module adopts a rhombus and Z-shaped structure formed by connecting non-resonant bicrystal piezoelectric patches in parallel, and is connected through a nickel-titanium alloy sheet, so that efficient energy conversion is realized, and the piezoelectric ceramic module adapts to various vibration frequencies; the displacement amplification structure uses a lever system formed by a flexible TPU hinge and a carbon fiber tube to amplify infinitesimal displacement generated by flapping wings of the insects, so that the energy collection efficiency is further improved; the flexible piezoelectric film structure is provided with a wing surface deformation part and a wing tail deformation part, and mechanical energy is effectively collected through transverse deformation and longitudinal deformation. The device has the characteristics of high energy conversion rate, light weight, flexibility and insect conformalization, does not remarkably interfere with natural wing flapping behaviors of insects, and can stably work in various vibration environments. The structure can be applied to power supply of semi-mechanical insect robots, power supply of biological monitoring systems and other scenes.

The invention discloses a tiny insect flapping wing flight and wing measurement and control modeling test device and method, and the device comprises a test platform which is provided with a linear driving device and a support, the linear driving device is connected with a load platform in a sliding manner, and the load platform is provided with a camera; a transparent channel is mounted on the bracket; the insect wing measurement and control system comprises a driving support and a wing driving device installed on the driving support, the wing driving device comprises a servo motor, a wing support is installed on an output shaft of the servo motor, a piezoelectric driver is installed on the wing support, the piezoelectric driver is connected with a connecting rod through a hinge, and the connecting rod is connected with the driving support. The wing bracket and the connecting rod are also connected with a wing mounting rod through a hinge, and wings are fixed on the wing mounting rod; and training a deep neural network model in a controller by using the obtained data to obtain a relation model of the flight parameters and the aerodynamic force. The problem that a high-speed camera cannot stably focus, the problem that flight motion data and a vortex structure cannot be measured, the problem that flight power cannot be measured, and the problem that no reliable flight model exists in the aspect of flight models in the prior art are solved.

To suppress generation of a peak dip in a diaphragm.SOLUTION: A diaphragm 1 is formed in a predetermined shape in which a length of one axial direction and a length in the other axial direction are different in the two axial direction which are orthogonal in a planar view and both sides in a length direction which is one axial direction consist of curves. The diaphragm 1 comprises a first reinforcement part 3 which extends in the length direction, and a second reinforcement part 4 which is mesh-like unevenness provided adjacently to the first reinforcement part 3 in a width direction. Insect wings are imitated on the second reinforcement part 4.SELECTED DRAWING: Figure 1

The utility model relates to the technical field of specimen tools, and particularly discloses a magnetic type insect wing spreading device which comprises a base, a groove formed in the center of the base, sliding grooves symmetrically formed in the inner wall of the base, a pull rod assembly arranged in the sliding grooves and a rotating assembly installed on the pull rod assembly. The bottom of the other end of the wing spreading plate is rotationally connected with a vertical rod which is clamped with the base; a groove is formed in the wing spreading plate, a foam plate is detachably connected in the groove, magnets on the upper side and the lower side of the wing spreading plate are connected with a plurality of magnet buckles, transparent pressing strip paper used for pressing wings of insect specimens is connected between the magnet buckles, and a plurality of magnet blocks capable of being magnetically connected with the wing spreading plate are arranged on the transparent pressing strip paper.

The invention provides an unmanned ship stabilization device based on a bionic dynamic variable diameter ratio and an optimization method aiming at the comprehensive performance improvement requirement of an unmanned ship rotary column stabilizer under a full-speed working condition. According to the method, a lift-drag integrated model fusing the Magnus effect and a variable diameter ratio parameter is established, and a three-layer collaborative bionic variable diameter ratio function is innovatively constructed on the basis: a basic form layer guarantees basic lift characteristics by referring to a plant stem macroscopic form, and a main fluctuation layer simulates a bamboo joint mesoscopic periodic structure to optimize flow characteristics; insect wing vein micro-textures are introduced into the high-frequency fluctuating layer to achieve fine control over the boundary layer. And a multi-dimensional reward objective function including smoothness, bionic types, variation amplitude, surface fluctuation and a variable diameter ratio range is further proposed, and full-speed optimal shape design is realized by combining multi-algorithm collaborative optimization. Through simulation verification, the method has the advantages that the full-speed average lift force is increased by 53.3%, the full-speed average lift-drag ratio is increased by 28.9%, and the full-speed adaptability and stability of the unmanned ship stabilization device are effectively enhanced.

The present invention discloses a flapping wing structure optimization method based on stiffness similarity, which belongs to the field of aircraft structure optimization. The present invention uses a variable density method to perform structural topology optimization on a finite element model, achieving the optimal minimum compliance of the flapping wing structure, thereby improving the structural stiffness of the flapping wing. Furthermore, based on insect wing stiffness experiments, the relationship between the flapping wing's spanwise bending stiffness and span length is established, and a stiffness similarity criterion is established using principal component analysis. A linear linear function of the flapping wing model's spanwise bending stiffness as a function of span length is solved, and the spanwise bending stiffness at different span lengths of the flapping wing is determined. With minimum structural mass as the optimization goal, the parameters of each vein line width function are used as variables, and the spanwise bending stiffness at different span lengths and the upper and lower boundaries of the line width that meet the structural strength, processing size, and engineering precision requirements of the insect wing are used as constraints, the flapping wing is optimized, thereby determining the flapping wing's veined structural layout and improving the flapping wing's lift and aerodynamic performance.

The utility model discloses a kind of curved insect governance systems, it includes environmental regulation device, screen window barrier device and atomization barrier device, environmental regulation device includes humidity sensor, frequency conversion sprayer and controller, controller is electrically connected humidity sensor and frequency conversion sprayer;Screen window barrier device includes several insect-proof screen window, atomization barrier device includes several high-pressure micro-mist sprayer.In the utility model, environmental regulation device can be adjusted and maintain environment relative humidity to not less than 80%, to make curved insect be in non suitable breeding interval, to inhibit curved insect hatching rate;Insect-proof screen window blocks curved insect into, and prevents and treats bird into curved room;Multiple high-pressure micro-mist sprayer forms water mist barrier outside insect-proof screen window, to wet curved insect wing, to inhibit curved insect flight ability, to avoid curved insect fly to insect-proof screen window;Summarized above, the curved insect governance system can improve curved insect control effect.

The present invention discloses a mechanical flapping-wing aircraft with variable flapping amplitude, mimicking the wings of an insect. The aircraft comprises a fuselage frame, a wing assembly with forewings and hindwings, a fuselage muscle assembly located within the fuselage frame and connected to the wing assembly for driving the flapping of the forewings and hindwings, a forewing muscle assembly connected to the wing assembly for varying the flapping amplitude of the forewings, a hindwing muscle assembly connected to the wing assembly for varying the flapping amplitude of the hindwings, and a head power assembly located within the fuselage frame and connected to the fuselage muscle assembly for generating power to the fuselage muscle assembly. The invention can change the flapping phase, amplitude, and frequency of the forewings and hindwings to achieve longitudinal and lateral attitude control of the aircraft, addressing the problem of flapping-wing aircraft's lack of maneuverability and difficulty in hovering.

The utility model relates to the technical field of bionic devices, in particular to a bionic flapping wing device which comprises a shell, two transmission parts, two bionic wings and a driving assembly, the number of the transmission parts is two, the number of the bionic wings is two, the two transmission parts are meshed with each other, the two bionic wings are both rotationally connected with the shell, and the driving assembly is connected with the shell. The two bionic wings are arranged in the shell and are correspondingly meshed with the transmission parts respectively, and the driving assembly is installed in the shell and drives one of the transmission parts to rotate so as to drive the bionic wings to swing synchronously through the two transmission parts respectively. According to the bionic flapping wing device, movement of the two bionic wings is transmitted and controlled through the transmission piece, the distance and the swing position between the two bionic wings can be controlled more accurately, the distance and the swing position of the bionic wings are made to better conform to the movement rule of wings of birds or insects, and the bionic flapping wing device is more convenient to use. The purpose of remarkably improving the bionic effect of the bionic flapping wing device is achieved.