Fuselage internal-structure optimization method of unmanned helicopter
An unmanned helicopter and internal structure technology, applied in the field of aerospace science, can solve problems such as unsatisfactory strength and reliability, achieve the effect of simplifying the application method and speeding up the calculation speed
Inactive Publication Date: 2018-10-16
BEIHANG UNIV
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Problems solved by technology
The internal structure of the fuselage initially designed can neither meet the requirements of strength and reliability, but also has a certain room for optimization in terms of weight.
Method used
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[0041] A certain type of unmanned helicopter development project, using the above method to optimize the internal structure of the fuselage. First, according to the requirements of step 1 and step 2, a simplified structure and external load model were established in the ABAQUS finite element modeling software, and an overload of 5g in the vertical direction and 2g in other directions was selected as the external load; then, the fuselage was selected according to step 3 The thickness values of the 16 beam models in the internal structure were used as optimization parameters, and the optimization direction was determined to be at the stress limit of 183MPa to minimize the weight of the structure; finally, empirical optimization and algorithm optimization based on ISIGHT optimization software were performed according to step 4.
[0042] Quality changes during optimization see attached Figure 4 .
[0043] The maximum stress change during optimization is shown in the attached ...
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The invention relates to a fuselage internal-structure optimization method of an unmanned helicopter. The method comprises: step 1, establishing a finite-element model of a fuselage internal-structure; step 2, determining external loads; step 3, selecting optimization parameters; and step 4, carrying out structure optimization calculation. According to the method, curved surfaces and line frames are employed to carry out simplified modeling on the real structure to facilitate application of beam and plate shell members in finite elements for simulation; fixing supporting connection and hingingsupporting connection are employed to respectively apply boundary conditions, and the inherent characteristics of all connection manners in structure connection are preserved; gravity and additionalforce of overloads are both simplified into the additional force of the overloads, and an application manner of the external loads is simplified; thickness of beam elements is selected to be used as optimization parameters, and the shape of a main-body frame is not changed; a manner of combining experience optimization and algorithm optimization is employed, and calculation speed of the optimization method is increased. In summary, the method of the invention is a highly efficient and universal fuselage internal-structure optimization method of the unmanned helicopter.
Description
technical field [0001] The invention relates to the field of aerospace science and technology, and proposes a method for optimizing the internal structure of an unmanned helicopter fuselage. Background technique [0002] An unmanned helicopter refers to a rotor-powered unmanned aircraft that can take off and land vertically through radio ground remote control or autonomous control. It has the characteristics of vertical takeoff, hovering in the air, and flying around. The high maneuverability and lightness and concealment of unmanned helicopters have made countries around the world list it as an important content of military development. It has a wide range of uses in military battlefields, mainly including military reconnaissance and military communications; It is mainly used in surveying, aerial photography, line inspection, fire fighting and disaster relief, etc. [0003] The main space inside the fuselage of a manned helicopter is the cockpit of the driver and passenger...
Claims
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Login to View More IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/17G06F30/23
Inventor 周尧明马云鹏王凯鹏
Owner BEIHANG UNIV