Controlled flight of a multicopter experiencing a failure affecting an effector

Patent metadata

Field	Value
Publication number	US-12473076-B2
Application number	US-202318100010-A
Country	US
Kind code	B2
Filing date	Jan 23, 2023
Priority date	Jun 9, 2013
Publication date	Nov 18, 2025
Grant date	Nov 18, 2025

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 experiencing a failure during flight, the multicopter comprising,
a body; and at least four effectors attached to the body, each configured to produce both a torque and a thrust force which can cause the multicopter to fly when not experiencing said failure, the method comprising the steps of, receiving at a control unit data which is representative of an orientation of a primary axis of said body with respect to a predefined reference frame; and receiving at the control unit data which is representative of an angular velocity of said multicopter; when a failure has occurred in one or more of said at least four effectors, wherein the failure is such that said at least four effectors are unable to collectively produce sufficient thrust force to maintain the vehicle airborne, controlling, using the control unit, one or more of said at least four effectors, based on said received data which is representative of the orientation of the primary axis and said received data which is representative of the angular velocity, such that said one or more of said at least four effectors collectively produce a torque and a thrust force which moves the vehicle into a target orientation so that the vehicle is in said target orientation upon landing.

2 . A method according to claim 1 further comprising controlling, using the control unit, one or more of said at least four effectors, based on said received data which is representative of the orientation of the primary axis and said received data which is representative of the angular velocity, such that said one or more of said at least four effectors collectively produce a torque and a thrust force which moves the vehicle such that the vehicle approaches the landing surface from a predefined direction.

3 . A method according to claim 1 wherein said target orientation is such that a selected part of the vehicle will be first to impact the landing surface.

4 . A method according to claim 3 wherein the selected part of the vehicle is a part of the vehicle which is less susceptible to damage than other parts of the vehicle.

5 . A method according to claim 3 wherein the selected part of the vehicle is a part of the vehicle which would cause less cause harm to a person upon impact, than other parts of the vehicle.

6 . A method according to claim 5 wherein the selected part of the vehicle is a part of the vehicle which will absorb more impact force that said other parts of the vehicle.

7 . A method according to claim 1 further comprising controlling, using the control unit, one or more of said at least four effectors, based on said received data which is representative of the orientation of the primary axis and said received data which is representative of the angular velocity, such that said one or more of said at least four effectors collectively produce a torque and a thrust force which moves the vehicle in a predefined direction.

8 . A method according to claim 1 wherein the method further comprises,
determining, based on the failure which has occurred, a plurality of different orientations which the vehicle could be orientated into prior to impacting the landing surface,
selecting one of the different orientations to be said target orientation.

9 . A method according to claim 8 wherein the step of selecting one of the different orientations to be said target orientation comprises,
for each of said different orientations identifying the part of the vehicle that will be first to impact the landing surface when the vehicle is in that orientation,
comparing the different identified parts of the vehicle to identify the part which is the most robust;
selecting the orientation in which the most robust part will impact the landing surface to be the target orientation.

10 . A method according to claim 1 wherein said failure is a failure in an effector which results in a decrease in the torque and/or the thrust force produced by said effector but said effector is still operable to produce some torque and/or thrust force.

11 . A method according to claim 1 wherein the step of controlling using the control unit comprises, controlling using the control unit one or more of said at least four effectors, based on said received data which is representative of the orientation of the primary axis and said received data which is representative of the angular velocity, such that said one or more of said at least four effectors collectively produce a torque perpendicular to said primary axis and a torque along 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 said torque along said primary axis causes said multicopter to rotate about said primary axis, and such that said one or more of said at least four effectors individually produces a thrust force along said primary axis.

12 . A method according to claim 1 wherein the step of controlling comprises controlling only the effectors which are without failure.

13 . A method according to claim 1 wherein the step of controlling comprises controlling the effectors which are without failure and also the efforts which have a failure.

14 . A multicopter comprising,
a body, at least four effectors attached to the body, each configured to produce both a torque and a thrust force which can cause the multicopter to fly when not experiencing a failure, a flight module, having a control unit, wherein said flight module is configured such that it can carry out the method comprising the steps of, receiving at a control unit data which is representative of an orientation of a primary axis of said body with respect to a predefined reference frame; and receiving at the control unit data which is representative of an angular velocity of said multicopter; when a failure has occurred in one or more of said at least four effectors, wherein the failure is such that said at least four effectors are unable to collectively produce sufficient thrust force to maintain the vehicle airborne, controlling, using the control unit, one or more of said at least four effectors, based on said received data which is representative of the orientation of the primary axis and said received data which is representative of the angular velocity, such that said one or more of said at least four effectors collectively produce a torque and a thrust force which moves the vehicle into a target orientation so that the vehicle is in said target orientation upon landing.

15 . A multicopter comprising,
a body, at least four effectors attached to the body, each configured to produce both a torque and a thrust force which can cause the multicopter to fly when not experiencing a failure, a flight module, having a control unit, wherein said flight module is configured such that it can carry out the method comprising the steps of, receiving at a control unit data which is representative of an orientation of a primary axis of said body with respect to a predefined reference frame; and receiving at the control unit data which is representative of an angular velocity of said multicopter; when a failure has occurred in one or more of said at least four effectors, defining a target acceleration for said multicopter, and using said target acceleration to compute said target orientation of said primary axis for said multicopter, and controlling using the control unit, one or more of said at least four effectors, bas

Assignees

• Eth Zuerich
• Eth Zuerich

Inventors

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

Classifications

• B64C2203/00

  Flying model aircraft, flying toy aircraft · CPC title

• B64C27/32

  Rotors · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• G05D1/617

  Safety or protection, e.g. defining protection zones around obstacles or avoiding hazards (arrangements for controlling the position or course of two or more vehicles for avoiding collisions therebetween G05D1/693; arrangements for reacting to or preventing system or operator failure G05D1/80) · CPC title

• B64U40/10

  for adjusting control surfaces or rotors · CPC title