Composite rotor aircraft

Abstract

The invention provides a composite rotor aircraft and relates to the aircraft technology. According to the composite rotor aircraft, by arranging an aircraft body and wings which are fused together, the exposed adverse soaking area of the aircraft body can be reduced and the aerodynamic resistance of the composite rotor aircraft can be reduced; and by mounting an integrated flaperon, the flying time of the composite rotor aircraft can be prolonged, the flying distance of the composite rotor aircraft can be extended and the loading capacity of the composite rotor aircraft can also be enhanced;and moreover, after a takeoff and landing motor power system is detached, the composite rotor aircraft is suitable for being remodeled into a fixed aircraft fused together with the wing bodies. Meanwhile, by detachably connecting a tail wing assembly with a supporting rod, the tail wing assembly can also be detached in the process of transporting, grounding or so on so that the tail wing assemblyis prevented from being knocked and the working reliability of the tail wing assembly is guaranteed.

Description

technical field [0001] The invention relates to aircraft technology, in particular to a compound rotor aircraft. Background technique [0002] Compound rotor aircraft, also known as fixed-wing four-rotor compound aircraft, is a new type of aircraft with vertical take-off and landing capabilities and high-speed cruise flight capabilities. [0003] The composite rotorcraft comprises: a fuselage, the rear end of which is provided with a propulsion propeller; wings are installed on the left and right sides of the longitudinal axis of the fuselage, and struts are arranged on both wings; Front propellers, two front propellers are symmetrically distributed along the longitudinal axis of the fuselage; two struts are equipped with rear propellers, two rear propellers are symmetrically distributed along the longitudinal axis of the fuselage, and the front propellers and rear propellers are respectively distributed On the front and rear sides of the wing; the tail ends of the two stru...

AI Technical Summary

Problems solved by technology

[0005] In the prior art, at the junction of the fuselage and the wing of the composite rotorcraft, the side of the fuselage forms a right angle with the surface of the wing, so that the composite rotorcraft has a large exposed unfavorable wetted area, resulting in the composite rotorcraft The aerodynamic resistance of the horizontal tail and the vertical tail increases; at the same time, due to the relatively low requirements for the carrying capacity of the horizontal tail and the vertical tail, in order to reduce the weight of the whole machine and reduce the cost, the weight of the horizontal tail and the vertical tail is lighter and the strength is weaker. During transportation, If the composite rotorcraft shakes, it is very easy to cause the horizontal tail or vertical tail to be damaged

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