Abstract

The invention relates to a multirotor drone (1) comprising a fuselage and a plurality of engine units driving a plurality of rotors (4), each rotor comprising two blades (5) mounted in a facing arrangement on either side of a blade tilting axis BP, such that each of the blades (5) has one rotational degree of freedom about said blade tilting axis BP.

IPC Classes  ?

• B64C 39/02 - Aircraft not otherwise provided for characterised by special use
• B64C 27/43 - Rotors having articulated joints with flapping hinge or universal joint, common to the blades see-saw type, i.e. two-bladed rotor

Abstract

The invention relates to a drone comprising a fuselage and a plurality of housing structures (3) for a plurality of engine units (4), the mechanical connection between each engine unit (4) and each housing structure (3) for the engine unit (4) comprising: a ball joint (10) arranged in the axis of rotation of the engine unit (4), opposite the rotor (6); and a flexible connecting member (20) connecting the engine unit (4) to the housing structure (3) for the engine unit (4).

IPC Classes  ?

• B64C 27/00 - RotorcraftRotors peculiar thereto
• B64C 39/02 - Aircraft not otherwise provided for characterised by special use

Abstract

Multirotor drone (1) the lift of which, in the air, is obtained by means of the use of at least three non-coaxial rotors each contributing a significant proportion of the overall lift required for flight, comprising a cell (3) connected to a plurality of motorized spindles (13) spaced apart, each motorized spindle (13) being connected to a variable-pitch rotor assembly (10) comprising a module for varying the collective pitch and twisted blades (12).

IPC Classes  ?

• B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
• B64C 39/02 - Aircraft not otherwise provided for characterised by special use