Intersecting double-rotor-wing unmanned helicopter
An unmanned helicopter and dual-rotor technology, which is applied in the directions of rotorcraft, unmanned aerial vehicles, motor vehicles, etc., can solve the problems of large reactive power loss and low hovering efficiency of unmanned helicopters, and achieves low useless power loss, The overall flight performance is improved and the overall structure is compact.
Active Publication Date: 2017-06-27
飞灵智控(北京)科技有限公司
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Problems solved by technology
[0003] The purpose of the present invention is to provide a cross-rotor unmanned helicopter, which aims to solve the technical problems of low hovering efficiency and large non-functional loss of the prior art unmanned helicopter
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[0047] Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. Attached below by reference Figure 1-13 The described embodiments are exemplary and are intended to explain the present invention, but should not be construed as limiting the present invention.
[0048] In describing the present invention, it should be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", The orientation or positional relationship indicated by "horizontal", "top", "bottom", "inner", "outer", etc. are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than Nothing indicating or implying that a referenced device o...
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The invention relates to the technical field of small unmanned helicopters, in particular to an intersecting double-rotor-wing unmanned helicopter which comprises a helicopter body undercarriage, a rotor wing system mounted on the helicopter body undercarriage, a power device used for controlling the rotor wing system to work and an avionic system connected with the power device to achieve a navigation effect. The rotor wing system comprises two main rotor wing mechanisms arranged above the helicopter body undercarriage. Each main rotor wing mechanism comprises a propeller blade, a rotor wing propeller hub and a rotary shaft. The two rotary shafts are rotatably connected with the power device, and an included angle is formed between the two rotary shafts. The two propeller blades are separately mounted at the ends of the two rotary wing propeller hubs and staggered when rotating. According to the intersecting double-rotor-wing unmanned helicopter, the two rotor wing propeller hubs are both connected with the power device which simultaneously drives the two rotor wing propeller hubs to work, the two rotor wing propeller hubs jointly work to provide large lifting force, reactive torque between the two rotor wing propeller hubs can be counteracted, and the helicopter has stable and reliable maneuvering performance even under extreme conditions.
Description
technical field [0001] The invention relates to the technical field of small unmanned helicopters, in particular to a crossed double-rotor unmanned helicopter. Background technique [0002] Most of the existing small and medium-sized unmanned helicopters are single-rotor and coaxial dual-rotor helicopters. The hovering efficiency of single-rotor helicopters is lower than that of double-rotors. The layout of the tail rotor is only to offset the counter torque and does not provide lift, which belongs to the power loss part; and The coaxial dual-rotor helicopter has a large vertical dimension of the dual-rotors, and the control stability of the helicopter is poor, and under extreme conditions, paddles are prone to occur between the upper and lower rotors. In addition, traditional helicopters have a separate design between the main reducer and the rotor system, as well as between the starter and the generator, resulting in complex structures, heavy weight of additional structure...
Claims
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IPC IPC(8): B64C27/08B64C27/12B64C27/59B64C27/80B64D33/04B64D33/10
CPCB64C27/08B64C27/12B64C27/59B64C27/80B64D33/04B64D33/10B64U10/10B64U30/20Y02T50/40
Inventor 徐旻
Owner 飞灵智控(北京)科技有限公司