High authority stability and control augmentation system

Patent metadata

Field	Value
Publication number	US-10712752-B2
Application number	US-201815872651-A
Country	US
Kind code	B2
Filing date	Jan 16, 2018
Priority date	May 21, 2014
Publication date	Jul 14, 2020
Grant date	Jul 14, 2020

Abstract

A system and method of increasing the control authority of redundant stability and control augmentation system (SCAS) actuators by utilizing feedback between systems such that one system may compensate for the position of a failed actuator of the other system. Each system uses an appropriate combination of reliable and unreliable inputs such that unreliable inputs cannot inappropriately utilize the increased authority. Each system may reconfigure itself when the other system actuator fails at certain positions so that the pilot or other upstream input maintains sufficient control authority of the aircraft.

First claim

What is claimed is:

1. A method for increasing the authority of a stability and control augmentation system, comprising:
providing a first actuator;
grouping robust inputs into a first group of inputs;
grouping non-robust inputs into a second group of inputs;
processing the first group of inputs into trusted commands for the actuator;
processing the second group of inputs into un-trusted commands for the actuator;
providing a set of limits for the un-trusted commands;
limiting the contribution of the un-trusted commands based on the set of limits to form limited un-trusted commands; and
summing the trusted commands with the limited un-trusted commands,
wherein the robust inputs are monitored.

2. The method according to claim 1 , wherein the step of summing the trusted commands with the limited un-trusted commands is utilized to move the first actuator.

3. The method according to claim 1 , wherein the robust inputs are attitude rates.

4. The method according to claim 1 , wherein the robust inputs are pitch rates.

5. The method according to claim 1 , wherein the non-robust inputs are airspeeds.

6. A rotary aircraft having a rotary system carried by a fuselage, the rotary system comprising:
a first flight control computer carried by the fuselage, the first flight control computer having;
a first processor for commanding a first actuator along a first axis; and
a second processor for commanding the first actuator along the first axis;

a second flight control computer carried by the fuselage;
a first actuator commanded by the first flight control computer for manipulating the rotary system along the first axis;
a second actuator commanded by the second flight control computer for manipulating the rotary system along the first axis; and
a third actuator for manipulating the rotary system along the first axis;
wherein the first actuator compares commands from the first processor of the first flight control computer to commands from the second processor of the first flight control computer to find a failure in the first actuator; and
wherein an output of the first actuator is summed with an output of the second actuator and summed with a control input for manipulating the rotary system with full authority in only the first axis by controlling the third actuator.

7. The rotary aircraft according to claim 6 , wherein the first and second processors in the first flight control computer group inputs by reliability.

8. The rotary aircraft according to claim 7 , wherein the first actuator is limited by unreliable inputs.

9. The rotary aircraft according to claim 6 , wherein the failure in the first actuator forces the first actuator fixed.

10. The rotary aircraft according to claim 9 , wherein the second actuator adjusts automatically due to, the failure in the first actuator.

11. A rotary aircraft having a rotary system carried by a fuselage, the rotary system comprising:
a first flight control computer carried by the fuselage, the first flight control computer having;
a plurality of processors;

a second flight control computer carried by the fuselage, the second flight control computer having;
a plurality of processors;

a first actuator commanded by the first flight control computer for manipulating the rotary system along a first axis;
a second actuator commanded by the second flight control computer for manipulating the rotary system along the first axis; and
a third actuator for manipulating the rotary system along the first axis;
wherein the first actuator compares commands between the processors of the first flight control computer to find a failure in the first actuator; and
wherein an output of the first actuator is summed with an output of the second actuator and summed with a control input for manipulating the rotary system with full authority in only the first axis by controlling the third actuator.

12. The rotary aircraft according to claim 11 , wherein the plurality of processors in the first flight control computer group inputs by reliability.

13. The rotary aircraft according to claim 12 , wherein the first actuator is limited by unreliable inputs.

14. The rotary aircraft according to claim 12 , wherein the second actuator adjusts automatically due to the failure in the first actuator.

15. The rotary aircraft according to claim 11 , wherein the failure in the first actuator forces the first actuator fixed.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Atkins Brady G
• Harris James E
• Griffith Carl D

Classifications

• G05D1/0077 Primary

  using redundant signals or controls · CPC title

• B64C13/341

  having duplication or stand-by provisions · CPC title

• B64C27/58

  Transmitting means, e.g. interrelated with initiating means or means acting on blades (means acting on blades B64C27/72) · CPC title

• G05D1/0833 Primary

  using limited authority control · CPC title

• B64C27/001

  Vibration damping devices · CPC title