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Title:
ATTITUDE STABILITY CONTROL DEVICE AND VERTICAL TAKE-OFF AND LANDING AIRCRAFT
Document Type and Number:
WIPO Patent Application WO/2019/026200
Kind Code:
A1
Abstract:
In vertical take-off and landing aircraft in which ducted fans are compactly arranged such that there is one on each of the front and rear of the fuselage, since the thrust generation surface is smaller in the lateral direction than in the longitudinal direction of the fuselage and thrust is controlled by the rotational speed of a rotor, gyroscopic precession weakens during takeoff and landing and during hovering and the fuselage is more likely to roll about the roll axis, leading to an unstable attitude for the fuselage. To address the problem, the present invention provides an attitude stability control device that is mounted below the propeller of a vertical take-off and landing aircraft, the attitude stability control device being characterized by comprising: a first blade-like member which is disposed on the left side of the vertical take-off and landing aircraft; a second blade-like member which is disposed on the right side of the vertical take-off and landing aircraft; a first angle adjustment mechanism which changes the angle of attack of the first blade-like member with respect to the airflow generated by the propeller; and a second angle adjustment mechanism which changes the angle of attack of the second blade-like member with respect to the airflow generated by the propeller.

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Inventors:
MATSUMOTO HIDEKI (JP)
Application Number:
PCT/JP2017/028029
Publication Date:
February 07, 2019
Filing Date:
August 02, 2017
Export Citation:
Click for automatic bibliography generation   Help
Assignee:
MATSUMOTO HIDEKI (JP)
International Classes:
B64C29/00; B64C5/00; B64C27/20
Domestic Patent References:
WO2005072233A22005-08-11
Foreign References:
US20030136873A12003-07-24
JP2015000602A2015-01-05
JP2013107626A2013-06-06
JP2011126517A2011-06-30
JP2010208501A2010-09-24
Attorney, Agent or Firm:
INOUE & CO. et al. (JP)
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