An empennage adjustment mechanism with conditional decoupling of pitch and yaw for aircraft

Abstract

The invention discloses a pitching and yawing conditional decoupling empennage regulating mechanism for an aircraft. The regulating mechanism comprises an empennage fixed part and an empennage movable part arranged at the tail part of the aircraft, as well as a yawing steering engine and a pitching steering engine arranged on the aircraft body, wherein the empennage fixed part is provided with an oscillating bearing; a rotating shaft is connected in the oscillating bearing in a sleeved manner; the rotating shaft is fixedly connected with the empennage movable part; the yawing steering engine and the rotating shaft are in rigid transmission connection through a yawing connecting rod; the pitching steering engine and the empennage movable part are in rigid transmission connection through a pitching connecting rod; the pitching steering engine and the yawing steering engine are arranged in the fuselage of the aircraft body; the structural form that a driving steering engine is arranged at the tail part of the aircraft traditionally is abandoned, so that the tail part weight of the aircraft is effectively reduced. Compared with the traditional movement decoupling empennage regulating mechanism, the pitching and yawing conditional decoupling empennage regulating mechanism, disclosed by the invention, can realize mechanical decoupling of an empennage mechanism under certain path instead of decoupling through software resolving and greatly improves the reliability, stability and regulation precision of a system.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a tail adjusting mechanism of a bionic flying robot. Background technique [0002] Due to the relatively mature technology, fixed-wing aircraft and multi-rotor aircraft have been initially and widely used in the fields of disaster rescue, environmental detection, and air cruise. [0003] Among them, fixed-wing aircraft generally adopt the method of horizontal take-off and landing, relying on the lift generated by the fixed-wing for take-off, landing and cruising. , The requirements for take-off and landing runways are also high, which limits its wide application. [0004] The multi-rotor aircraft relies on the rotor to generate lift, can perform vertical take-off and landing, and has low requirements for the take-off and landing environment. In addition to vertical take-off and landing, the multi-rotor aircraft can also control the flight attitude by distributing the lift of e...

AI Technical Summary

Problems solved by technology

[0006] The tail adjustment mechanisms of existing bionic flying robots are mostly coupled with pitch and yaw, and the decoupling is realized through the calculation of the control system, which will bring disadvantages such as low decoupling efficiency, low precision, and slow response speed; and the current Part of the decoupled pitch and yaw motion tail adjustment mechanisms are all in series layout, and the steering gear is placed on the movement mechanism at the tail of the aircraft, which increases the weight of the tail of the aircraft and makes the tail of the aircraft more bloated and bulky

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