Fuselage load-bearing structure of an oil-powered unmanned aerial vehicle
A load-bearing structure and unmanned aerial vehicle technology, applied to the fuselage, fuselage frame, aircraft parts, etc., to achieve excellent weight reduction effects, reduce wind resistance, and reduce skin area effects
Active Publication Date: 2020-09-25
沈阳旋飞航空技术有限公司
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[0008] This prior art effectively overcomes the defective of prior art, but still there is room for improvement
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[0028] In order to have a clearer understanding of the technical features, purposes and effects of the present invention, the specific implementation manners of the present invention will now be described with reference to the accompanying drawings. Wherein, the same parts adopt the same reference numerals.
[0029] As described in the background technology, the present invention proposes an improved structure for the deficiencies in the load configuration structure of the oil-powered UAV disclosed in the prior art Chinese patent application 201711089304.X, so that the UAV of the prior art It has higher structural strength and torsion resistance, and at the same time can obtain lighter structural weight, and the shape is simpler, which can further reduce the shape resistance.
[0030] Specifically, the fuselage load-bearing structure of the oil-powered UAV of the present invention is a further improvement proposed on the basis of the load configuration structure of 20171108930...
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The invention discloses an airframe bearing structure of an oil-driven unmanned aerial vehicle. The airframe bearing structure comprises an airframe support with a fully-symmetric structure; the airframe support is provided with a transverse symmetry axis vertical to a longitudinal symmetry axis; the airframe support comprises two carbon fiber girders arranged to be symmetric to the longitudinal symmetry axis as well as two engine bearing rib plates, undercarriage bearing rib plates, cantilever bearing rib plates and tail end bearing rib plates which are arranged to be symmetric to the transverse symmetry axis; and the engine bearing rib plates, the undercarriage bearing rib plates, the cantilever bearing rib plates and the tail end bearing rib plates are sequentially arranged from a symcenter of the airframe support along two sides of the longitudinal symmetry axis. According to the airframe bearing structure disclosed by the application, sufficient torsional property and strength canbe obtained by the fully-carbon airframe support with the fully-symmetric structure and a web structure with smaller height, meanwhile, an existing metal member can be removed, so that the structuralweight is greatly reduced. In addition, the smaller airframe height can be obtained, so that the wind resistance is reduced, the skin area is reduced, and the weight reducing effect is excellent.
Description
technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a multi-rotor oil-powered unmanned aerial vehicle, and in particular to a fuselage bearing structure of an oil-powered unmanned aerial vehicle. Background technique [0002] Unmanned aircraft, referred to as "UAV", is an unmanned aircraft controlled by radio remote control equipment and its own program control device. According to the application field, UAV can be divided into military and civilian. In terms of military use, UAVs are divided into reconnaissance aircraft and target aircraft. Civilian drones are widely used in aerial photography, agriculture, plant protection, micro-selfies, express delivery, disaster relief, observation of wild animals, monitoring of infectious diseases, surveying and mapping, news reports, power inspections, disaster relief, film and television shooting and other fields. [0003] Existing multi-rotor drones are usually electric...
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IPC IPC(8): B64C1/06
CPCB64C1/068Y02T50/40
Inventor 刘新民庞振岳孔令超鲁明张建飞孙卫华宗宁
Owner 沈阳旋飞航空技术有限公司