Design method for reducing dynamic stress level of composite rotor wing
A composite material and design method technology, applied in the field of helicopters, can solve problems such as the inaccurate aerodynamic model of the rotor, the inability to accurately simulate the complex aerodynamic environment of the rotor, and the reduction of the dynamic stress level of the rotor.
Active Publication Date: 2020-11-17
BEIHANG UNIV
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Problems solved by technology
The aerodynamic model of the rotor in the above method is not accurate enough to accurately simulate the complex aerodynamic environment of the rotor. Therefore, the purpose of reducing the dynamic stress level of the rotor cannot be effectively achieved
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Embodiment 1
[0068] A hinged composite material rotor blade is designed by using the above-mentioned design method for reducing the dynamic stress level of the composite material rotor blade provided by the present invention. There are 4 blades in the rotor, the diameter is 2.5m, there is no geometric torsion, the rotational speed Ω=800r / min, and the airfoil is NACA0015. Comparing and analyzing the above-mentioned design method for reducing the dynamic stress level of the composite material rotor provided by the present invention and the blade vibration level obtained by the existing design method can better reflect the above-mentioned reduction of the composite material rotor dynamic stress level provided by the present invention. effectiveness of the design method. The blade vibration level index of the original blade is 14.1, 7.2, 5.1, 1.6, and the first four-order modal vibration level index of the optimized model in the above-mentioned design method for reducing the dynamic stress lev...
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The invention discloses a design method for reducing the dynamic stress level of a composite material rotor wing, which comprises the following steps: calculating generalized aerodynamic force of eachorder of mode based on calculation fluid model software, taking the composite material laying angle and thickness of a helicopter rotor wing blade as design variables, taking the vibration level index of the helicopter rotor wing blade as an objective function, taking the vibration mode node position, mass and spinning inertia requirements of the helicopter rotor blade as constraint functions, establishing an optimization model for reducing the vibration and dynamic stress levels of the helicopter rotor blade, solving the optimization model based on an optimization design method of sensitivity analysis optimization and global optimization to obtain a blade vibration level index, and outputting the optimized blade design variable. Compared with the existing method that the aerodynamic model of the rotor is not accurate enough and the complex aerodynamic environment of the rotor cannot be simulated accurately, the method has the advantages that the state space model of the aerodynamic reduced-order model of the composite rotor established on the basis of the reduced-order model is more accurate, and the dynamic stress level of the rotor blade can be effectively reduced.
Description
technical field [0001] The invention relates to the technical field of helicopters, in particular to a design method for reducing the dynamic stress level of a composite material rotor. Background technique [0002] Composite rotors are a key component of helicopters, providing lift, thrust and control for the helicopter. The periodic motion of the rotor will cause serious vibration problems to the helicopter, which will not only have a huge impact on the service life of the helicopter, the comfort of the crew members and mission effectiveness, but also limit its forward flight speed and maneuverability. Therefore, helicopter vibration reduction is one of the important issues that need to be considered in helicopter design. [0003] At present, the research on helicopter vibration reduction mainly focuses on three aspects: reducing the vibration of the fuselage, reducing the vibration transmitted from the rotor to the fuselage structure, and controlling the dynamic stress o...
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IPC IPC(8): G06F30/15G06F30/23G06F30/28G06F113/08G06F113/26G06F119/14
CPCG06F30/15G06F30/23G06F30/28G06F2113/26G06F2113/08G06F2119/14Y02T90/00
Inventor 李道春赵仕伟阚梓陈世泽李华东向锦武
Owner BEIHANG UNIV