Rotorcraft autopilot and methods

Patent metadata

Field	Value
Publication number	US-10926872-B2
Application number	US-201916510897-A
Country	US
Kind code	B2
Filing date	Jul 13, 2019
Priority date	Feb 10, 2012
Publication date	Feb 23, 2021
Grant date	Feb 23, 2021

Abstract

A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

First claim

What is claimed is:

1. An autopilot system for a helicopter, said autopilot system comprising:
an inner loop that is configured at least for providing a true attitude estimate for the flight of the helicopter including a given level of reliability applied to the inner loop that meets applicable certification requirements; and
an outer, autopilot loop that is configured for providing at least one navigation function with respect to the flight of the helicopter including a lower level of redundancy than the inner loop.

2. The autopilot system of claim 1 wherein the inner loop is configured with triplex processors for triple redundancy in the inner loop.

3. The autopilot system of claim 2 wherein the inner loop is further configured such that the triplex processors each simultaneously generate a motor control signal.

4. The autopilot system of claim 3 wherein the inner loop is configured to receive a control command from the outer loop on each iteration of the inner loop as part of generating the motor control signal of each triplex processor.

5. The autopilot system of claim 4 wherein the outer loop is configured to perform one-for-one iteration with the inner loop.

6. The autopilot system of claim 3 wherein each triplex processor is configured to compare the motor control signal that is generated by that triplex processor to the motor control signal that is generated by each of the other two triplex processors and, based on the comparison, to cast a first vote for or against a first one of the other two triplex processors and a second vote for or against a second one of the other two triplex processors.

7. The autopilot system of claim 6 wherein first and second given ones of the triplex processors are each in control communication with at least one actuator motor and a third triplex processor generates said motor control signal and casts said votes but the third triplex processor is not in control communication with an actuator motor.

8. The autopilot system of claim 6 including a voting manager that disables motor control signal influence for any particular one of the triplex processors when the votes of both of the other two triplex processors are against the particular triplex processor to indicate a failure thereof.

9. The autopilot system of claim 8 wherein the inner loop and the outer loop remain fully operational responsive to a failure of a single one of the triplex processors.

10. The autopilot system of claim 3 including a pitch actuator and a roll actuator for applying pitch actuations and roll actuations, respectively, to a control linkage of the helicopter and each of which actuators includes a redundant electric motor set at least including a first motor and a second motor, and a first triplex processor generates first processor motor control signals to control the first motor of the pitch actuator and the first motor of the roll actuator and a second triplex processor generates second processor motor control signals that control the second motor of the pitch actuator and the second motor of the roll actuator.

11. The autopilot system of claim 10 wherein the pitch actuator and the roll actuator each include an output shaft and are each configured such that either one of the first and second motor and/or both of the first motor and second motor of a given one of the actuators can rotate a given output shaft of the given actuator to provide control linkage actuations.

12. The autopilot system of claim 1 wherein the inner loop is configured with triplex processors for triple redundancy in the inner loop and further comprising a set of triplex sensor suites such that each triplex processor reads one of the sensor suites that is dedicated to that triplex processor to produce sensor data.

13. The autopilot system of claim 12 wherein each triplex processor is configured to share the sensor data from a dedicated one of the sensor suites with the other two triplex processors.

14. The autopilot system of claim 13 wherein each triplex processor is configured to determine a median set of sensor data based on the sensor data from all of the triplex processors and to determine said motor control signal based on the median set of sensor data.

15. The autopilot system of claim 14 wherein each triplex processor is configured to reject any erroneous sensor data.

16. The autopilot system of claim 15 wherein each triplex processor is configured to identify the erroneous sensor data based, at least in part, on a comparison of three sensor outputs with each sensor output produced by a given sensor of each one of the sensor suites.

17. The autopilot system of claim 1 wherein the outer loop is configured to operate based on a set of control laws for a particular helicopter.

18. The autopilot system of claim 1 wherein said helicopter includes a cyclic control and wherein the system further comprises an actuator arrangement for actuating the cyclic control to provide said attitude hold and said navigation function.

Assignees

• Merlin Technology Inc

Inventors

• Mercer John E
• Albion Nicholas
• Bartel Mark
• Feifel Marc
• Marvin Mark

Classifications

• G05D1/0816

  to ensure stability · CPC title

• G05D1/0077

  using redundant signals or controls · CPC title

• G05D1/0858

  specially adapted for vertical take-off of aircraft · CPC title

• G05D1/102

  specially adapted for vertical take-off of aircraft · CPC title

• G05D1/00

  Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots (drive control systems specially adapted for autonomous road vehicles B60W60/00) · CPC title