Controlled flight of a multicopter experiencing a failure affecting an effector

Patent metadata

Field	Value
Publication number	US-10308349-B2
Application number	US-201715833385-A
Country	US
Kind code	B2
Filing date	Dec 6, 2017
Priority date	Jun 9, 2013
Publication date	Jun 4, 2019
Grant date	Jun 4, 2019

Abstract

According to a first aspect of the invention, there is provided a method for operating a multicopter experiencing a failure during flight, the multicopter comprising a body, and at least four effectors attached to the body, each operable to produce both a torque and a thrust force which can cause the multicopter to fly when not experiencing said failure. The method may comprise the step of identifying a failure wherein the failure affects the torque and/or thrust force produced by an effector, and in response to identifying a failure carrying out the following steps, (1) computing an estimate of the orientation of a primary axis of said body with respect to a predefined reference frame, wherein said primary axis is an axis about which said multicopter rotates when flying, (2) computing an estimate of the angular velocity of said multicopter, (3) controlling one or more of said at least four effectors based on said estimate of the orientation of the primary axis of said body with respect to said predefined reference frame and said estimate of the angular velocity of the multicopter. The step of controlling one or more of said at least four effectors may be performed such that (a) said one or more effectors collectively produce a torque along said primary axis and a torque perpendicular to said primary axis, wherein (i) the torque along said primary axis causes said multicopter to rotate about said primary axis, and (ii) the torque perpendicular to said primary axis causes said multicopter to move such that the orientation of said primary axis converges to a target orientation with respect to said predefined reference frame, and (b) such that said one or more effectors individually produce a thrust force along said primary axis.

First claim

The invention claimed is:

1. A method for operating a multicopter, the multicopter comprising,
a body; and
at least four effectors attached to the body, each configured such that it can produce both a torque and a thrust force;
and a control unit which can control the flight of the multicopter;

the method comprising the step of,
using the control unit to carry out the steps of,
when there is no failure in any of said one or more effectors, controlling one or more of said at least four effectors, based on the orientation of a primary axis of said body with respect to a predefined reference frame, wherein said primary axis is an axis aligned with a sum of thrust forces produced by said one or more of said at least four effectors over a predefined time with respect to the predefined reference frame, such that one or more of said at least four effectors produce a torque perpendicular to said primary axis, wherein the torque perpendicular to said primary axis causes said multicopter to move such that the orientation of said primary axis converges to a target orientation with respect to said predefined reference frame, and such that one or more of said at least four effectors produce a thrust force along said primary axis;
when a failure occurs in any of said one or more effectors, wherein said failure affects the torque and/or the thrust three produced any one or more of said at least four effectors, then, controlling the one or more effectors which are without a failure, based on the orientation of the primary axis of said body with respect to the predefined reference frame and the angular velocity of said multicopter, such that said one or more of said at least four effectors which are without a failure collectively produce a torque along said primary axis and a torque perpendicular to said primary axis, wherein the torque along said primary axis causes said multicopter to rotate about said primary axis, and the torque perpendicular to said primary axis causes said multicopter to move such that the orientation of said primary axis converges to a target orientation with respect to said predefined reference frame, and such that said one or more of said at least four effectors which are without a failure collectively produces a thrust force along said primary axis.

2. A method according to claim 1 wherein the method further comprises the steps of, using the control unit to carry out the further steps of,
computing an estimate of the orientation of the primary axis of said body with respect to a predefined reference frame; and
computing an estimate of the angular velocity of said multicopter;
and wherein said steps of controlling one or more of said at least four effectors, based on the orientation of the primary axis of said body with respect to the predefined reference frame, and based on the angular velocity of the multicopter, such that one or more of said at least four effectors produce a torque perpendicular to said primary axis, wherein the torque perpendicular to said primary axis causes said multicopter to move such that the orientation of said primary axis converges to a target orientation with respect to said predefined reference frame, and such that one or more of said at least four effectors produce a thrust force along said primary axis, comprise,

controlling one or more of said at least four effectors, based on said estimate of the orientation of the primary axis of said body with respect to the predefined reference frame, and based on said estimate of the angular velocity of the multicopter, such that one or more of said at least four effectors produce a torque perpendicular to said primary axis, wherein the torque perpendicular to said primary axis causes said multicopter to move such that the orientation of said primary axis converges to a target orientation with respect to said predefined reference frame, and such that one or more of said at least four effectors produce a thrust force along said primary axis.

3. A method according to claim 1 , wherein the multicopter further comprises an evaluation unit, wherein the method further comprises the step of,
identifying, using an evaluation unit, a failure wherein said failure affects the torque and/or the thrust force produced by an effector;
in response to identifying a failure, using a control unit to control one or more of said at least four effectors which are without a failure, based on the orientation of the primary axis of said body with respect to the predefined reference frame, and based on the angular velocity of said multicopter,
such that said one or more of said at least four effectors which are without a failure collectively produce a torque along said primary axis and a torque perpendicular to said primary axis, wherein the torque along said primary axis causes said multicopter to rotate about said primary axis, and the torque perpendicular to said primary axis causes said multicopter to move such that the orientation of said primary axis converges to a target orientation with respect to said predefined reference frame,
and such that said one or more of said at least four effectors which are without a failure collectively produces a thrust force along said primary axis.

4. A method according to claim 3 , wherein said step of identifying, using an evaluation unit, a failure, comprises,
identifying, using said evaluation unit, a failure, based on data representative of the motion of said multicopter.

5. The method according to claim 1 , further comprising the step of
defining a target thrust force magnitude, and wherein,
said step of controlling one or more of said at least four effectors based on said orientation of the primary axis of said body with respect to the predefined reference frame and said angular velocity of the multicopter, comprises, controlling said one or more effectors such that the magnitude of the sum of each of said thrust forces produced individually by said one or more effectors along said primary axis, averaged over a predefined time period, equals said target thrust force magnitude.

6. The method according to claim 1 , further comprising the step of
defining a target altitude position, and wherein
said step of controlling one or more of said at least four effectors based on said orientation of the primary axis of said body with respect to the predefined reference frame and said angular velocity of the multicopter, comprises controlling said one or more effectors such that the thrust forces produced by said one or more of said at least four effectors along said primary axis cause the altitude position of the multicopter to converge to said target altitude position.

7. The method according to claim 1 , wherein said multicopter is a quadrocopter.

8. The method according to claim 1 , wherein said multicopter rotates about the primary axis when said failure occurs in any of said one or more effectors.

9. The method according to claim 8 , wherein said torque along said primary axis causes said multicopter to rotate about said primary axis at a speed greater than 0.5 revolutions per second.

10. The method according to claim 1 , wherein controlling the one or more effectors which are without a failure, is based on the configuration resulting from the failure occurring in any of said one or more effectors.

Assignees

• Eth Zuerich

Inventors

• Mueller Mark W
• Lupashin Sergei
• D'Andrea Raffaello
• Waibel Markus

Classifications

• B64U2101/30

  for imaging, photography or videography · CPC title

• B64U2201/20

  Remote controls · CPC title

• B64U2201/10

  autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS] · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B64C13/24 Primary

  Transmitting means · CPC title