Multicopter

Patent metadata

Field	Value
Publication number	US-10875635-B2
Application number	US-201816108716-A
Country	US
Kind code	B2
Filing date	Aug 22, 2018
Priority date	Aug 28, 2017
Publication date	Dec 29, 2020
Grant date	Dec 29, 2020

Abstract

There is provided a multicopter having a frame, four rotors attached to the frame and each having an input shaft, four motor-generators installed one on each of the rotors and each having an input-output shaft, a single gas-turbine engine connected to the motor-generators and having an output shaft. The input shaft of each rotor, the input-output shaft of each motor-generator and the output shaft of the engine are respectively connected with each other by a speed reducer mechanism having a sun gear, ring gear and planetary carrier.

First claim

What is claimed is:

1. A multicopter, comprising:
a frame;
multiple rotors attached to the frame and each having an input shaft;
multiple motor-generators installed one on each of the multiple rotors and each having an input-output shaft;
an engine connected to the multiple motor-generators and having an output shaft; and
multiple speed reducer mechanisms each comprising a planetary gear mechanism installed on one of the multiple rotors; the planetary gear mechanism having a sun gear, ring gear and planetary carrier which connects planetary gears;
wherein the input shaft of each rotor, the input-output shaft of each motor-generator and the output shaft of the engine are connected with each other by each speed reducer mechanism.

2. The muliticopter according to claim 1 , wherein the output shaft of the engine is connected to the planetary carrier of the planetary gear mechanism, the input-output shaft of the motor-generator is connected to the sun gear of the planetary gear mechanism, and the ring gear of the planetary gear mechanism is connected to the input shaft of the rotor.

3. The multicopter according to claim 1 , wherein the output shaft of the engine is connected to the sun gear of the planetary gear mechanism, the input-output shaft of the motor-generator is connected to the planetary carrier of the planetary gear mechanism, and the ring gear of the planetary gear mechanism is connected to the input shaft of the rotor.

4. The multicopter according to claim 1 , wherein the output shaft of the engine is connected to the sun gear of the planetary gear mechanism, the input-output shaft of the motor-generator is connected to the ring gear of the planetary gear mechanism, and the planetary carrier of the planetary gear mechanism is connected to the input shaft of the rotor.

5. The multicopter according to claim 1 , wherein the output shaft of the engine is connected to the sun gear of the planetary gear mechanism, the ring gear of the planetary gear mechanism is fastened to a fixed part of the speed reducer mechanism, and the planetary carrier of the planetary gear mechanism is connected through a clutch to the input-output shaft of the motor-generator and the input shaft of the rotor.

6. The multicopter according to claim 1 , wherein the output shaft of the engine is connected to the sun gear of the planetary gear mechanism, the input-output shaft of the motor-generator is connected to the planetary carrier of the planetary gear mechanism, and the ring gear of the planetary gear mechanism is connected through a second speed reducer mechanisms to the input shaft of the rotor.

7. The multicopter according to claim 1 , further including:
a gyrosensor configured to produce an output indicating tilt angle of the frame with respect to gravity axis of the frame;
an altimeter configured to produce an output indicating altitude above ground level calculated based on a reflected wave obtained when an ultrasonic wave is transmitted from the frame toward the ground;
a GPS receiver configured to produce an output indicating position of the frame calculated based on signals received from a group of satellites;
a vision sensor configured to output captured images taken in advancing direction; and
a flight controller configured to control takeoff/landing and posture of the frame based on outputs of the gyrosensor, altimeter, GPS receiver and vision sensor.

8. The multicopter according to claim 7 , wherein the motor-generator is connected to a battery through a power drive unit equipped with a converter and an inverter in such manner that the converter converts AC power generated by the motor-generator to be stored in the battery and the inverter inverts the DC power stored in the battery to the AC power.

9. The multicopter according to claim 1 , wherein a number of the rotor is 2n (n≥2).

10. The multicopter according to claim 8 , wherein the flight controller operates the engine to rotate all of the rotors and apply power stored in the battery to the motor-generators to rotate motors to assist operation of the engine, when taking off.

11. The multicopter according to claim 8 , wherein the flight controller unitizes rotation of one of the rotors whose rotation is to be reduced to regeneration of one of the motor-generator associated with one of the rotors and electric power obtained by the regeneration is supplied to another of the motor-generators associated with another of the rotors whose rotation is to be increased, when turning.

12. The multicopter according to claim 8 , wherein the flight controller utilizes all of the rotors to regeneration of all of the motor-generators, when landing.

Assignees

• Honda Motor Co Ltd

Inventors

• Kita Akinori

Classifications

• B64U50/12

  using turbine engines, e.g. turbojets or turbofans · CPC title

• B64U50/11

  using internal combustion piston engines · CPC title

• B64C27/12 Primary

  Rotor drives · CPC title

• B64D35/04 Primary

  characterised by the transmission driving a plurality of propellers or rotors · CPC title

• B64U30/20

  Rotors; Rotor supports · CPC title