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Title:
RADIO CONTROL AIRCRAFT
Document Type and Number:
Japanese Patent JPH0740897
Kind Code:
A
Abstract:

PURPOSE: To take off and land even when a place is narrow, and improve autonomous stability and safety at forced landing time by arranging a central girder between a column of the fuselage and a vertical tail, arranging a main wing constituting member by plane moderate angle shaped side girder materials, arranging the vertical tail, a horizontal tail and a propeller having a prime mover, and controlling these by a radio transmitter.

CONSTITUTION: A central girder material 3b on the central upper side of the fuselage 2 is fixed to a column 3d and a vertical tail 4, and plane moderate angle-shaped side girder material 3c are fixed to the front end of the central girder material 3b and both tips of a beam material 3e, and a main wing sheet 3a of a flexible raw material is fixed to these. A horizontal tail 5 whose whole wing swings is arranged on the side of the vertical tail 4. A propeller rotated by a prime mover 6 is arranged in the vicinity of the center of gravity of an aircraft body 1, and the control mechanism is controlled by a radio transmitter 13 together with a control mechanism of the vertical tail 4 and the horizontal tail 5. Since the main wing sheet 3a has the large area and the horizontal tail 5 can swing the whole wing, a ground run can be shortened even at low speed, and autonomous posture restoring force is improved.


Inventors:
Nakajima, Koji
Application Number:
JP1994000029174
Publication Date:
February 10, 1995
Filing Date:
February 02, 1994
Export Citation:
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Assignee:
OKABE KAZUO
NAKAJIMA KOJI
SATO KENSETSU KOGYO KK
International Classes:
A63H27/00; A63H27/08; A63H27/24; A63H30/04; B64C31/02; B64C31/024; B64C39/02; G05D1/00; (IPC1-7): B64C39/02; A63H27/00; B64C31/02