Aircraft as well as cruise level flight method

Abstract

The invention discloses an aircraft as well as a cruise level flight method. The aircraft includes: an aircraft body and a support frame; at least one group of fixed rotor wing units, each of which isfixedly connected to the aircraft body; and at least one group of rotatable rotor wing units, each of which is fixedly connected to the support frame. During flight, the aircraft has at least to twoflight attitudes: one is a cruise level flight mode and the other is a taking-off / landing mode. The support frame is rotatably connected to the aircraft body and can swing relative to the aircraft body, so that the support frame is expanded / closed relative to the aircraft body and can drive the rotatable rotor wing units to rotate so as to be switched between the cruise level flight mode and the taking-off / landing mode; or the support frame is fixed to the aircraft body, so that when the aircraft flies in the cruise level flight mode, the rotatable rotor wing units supply forward pushing forceto the aircraft. According to the technical scheme, the acceleration performance and maximum level flight speed of the aircraft under the cruise level flight mode are improved, and responding speed on adjustment of the forward pushing force is also increased.

Description

technical field [0001] The invention relates to the technical field of aviation flight power machinery, in particular to an aircraft and a method for cruising and leveling the aircraft. Background technique [0002] With the rapid development of science and technology and the improvement of people's living standards, drones, airliners and other aircraft have been widely used in people's lives, especially multi-rotor aircraft, which are increasingly used in the field of small drones and flying cars. However, the conventional multi-rotor aircraft has the following disadvantages: the conventional multi-rotor aircraft generates forward thrust by raising the nose, that is, reducing the pitch angle of the aircraft fuselage. However, there is a certain lower limit for the reduction of the pitch angle (the lower limit is generally -20 to -35 degrees), otherwise sufficient lift cannot be guaranteed, and lowering the nose will increase the aerodynamic resistance of the fuselage in cru...

AI Technical Summary

Problems solved by technology

However, the conventional multi-rotor aircraft has the following disadvantages: the conventional multi-rotor aircraft generates forward thrust by raising the nose, that is, reducing the pitch angle of the aircraft fuselage.

However, there is a certain lower limit for the reduction of the pitch angle (the lower limit is generally -20 to -35 degrees), otherwise sufficient lift cannot be guaranteed, and lowering the nose will increase the aerodynamic resistance of the fuselage in cruising and level flight.

Therefore, the flight speed of conventional multi-rotors is usually relatively low

2) The change of the forward thrust of the conventional multi-rotor needs to be realized indirectly through the process of changing the pitch angle, and there is a time lag, which reduces the response speed of the adjustment of the forward thrust

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