US 12,239,863 B2
Aircraft and aircraft system using same
Hisayoshi Suefuku, Tokyo (JP)
Filed by Hisayoshi Suefuku, Tokyo (JP)
Filed on Apr. 26, 2023, as Appl. No. 18/307,226.
Application 18/307,226 is a division of application No. 16/628,326, granted, now 11,679,873, previously published as PCT/JP2018/025787, filed on Jul. 6, 2018.
Claims priority of application No. 2017-132469 (JP), filed on Jul. 6, 2017.
Prior Publication US 2023/0312093 A1, Oct. 5, 2023
Int. Cl. A62C 29/00 (2006.01); A47L 11/38 (2006.01); B08B 1/32 (2024.01); B64D 1/18 (2006.01); B64U 10/13 (2023.01); B64U 10/60 (2023.01); B64U 30/20 (2023.01); B64U 40/10 (2023.01); B64U 50/13 (2023.01); B64U 50/19 (2023.01); A62C 31/00 (2006.01); B64U 101/29 (2023.01); B64U 101/40 (2023.01); B64U 101/45 (2023.01); B64U 101/47 (2023.01); G05D 1/00 (2006.01)
CPC A62C 29/00 (2013.01) [A47L 11/38 (2013.01); B08B 1/32 (2024.01); B64D 1/18 (2013.01); B64U 10/13 (2023.01); B64U 10/60 (2023.01); B64U 30/20 (2023.01); B64U 40/10 (2023.01); B64U 50/13 (2023.01); B64U 50/19 (2023.01); A62C 31/00 (2013.01); B64U 2101/29 (2023.01); B64U 2101/40 (2023.01); B64U 2101/45 (2023.01); B64U 2101/47 (2023.01); B64U 2201/104 (2023.01); B64U 2201/20 (2023.01); G05D 1/0094 (2013.01)] 9 Claims
OG exemplary drawing
 
1. An aircraft, comprising:
an airframe;
one or a plurality of first rotary blade portions having a first rotary blade arranged on the airframe so as to rotate in a plane substantially perpendicular to a center axis of the airframe and first driving means for rotating/driving the first rotary blade;
a nozzle fixed to the airframe and to which a hose for sending out a liquid is attached;
a plurality of second rotary blade portions having a second rotary blade arranged on the airframe so as to obtain a propelling force against a reaction force when the liquid is discharged to an outside from the nozzle through the hose and second driving means for rotating/driving the second rotary blade; and
flight control means for controlling a flight of the airframe by controlling driving of each of the first driving means and each of the second driving means, wherein
the plurality of second rotary blade portions include an upper second rotary blade portion arranged vertically above the airframe and a lower second rotary blade portion arranged vertically below the airframe;
the nozzle is arranged at a position where a distance from a center of the airframe to the nozzle is smaller than a distance from the center of the airframe to each of the second rotary blades; and
the flight control means controls the driving of each of the second driving means so that the airframe is not rotated by a moment of force by the reaction force at the liquid discharge from the nozzle and the propelling force by each of the second rotary blades.