Dual rotor, rotary wing aircraft

Patent metadata

Field	Value
Publication number	US-11021241-B2
Application number	US-201515514595-A
Country	US
Kind code	B2
Filing date	Sep 29, 2015
Priority date	Oct 1, 2014
Publication date	Jun 1, 2021
Grant date	Jun 1, 2021

Abstract

An aircraft is provided and includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe, at least one sensor and at least one inertial measurement unit (IMU) to sense current flight conditions of the aircraft, an interface to execute controls of a main rotor assembly in accordance with control commands and at least one flight control computer (FCC) to issue the control commands. The at least one FCC includes a central processing unit (CPU) and a memory having logic and executable instructions stored thereon, which, when executed, cause the CPU to issue the control commands based on the current flight conditions and a result of an execution of the logic for the current flight conditions.

First claim

What is claimed is:

1. An aircraft comprising:
an airframe;
an extending tail;
a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly;
a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe;
at least one sensor and at least one inertial measurement unit (IMU) to sense current flight conditions of the aircraft;
an interface to execute controls of a main rotor assembly in accordance with control commands, the interface including a rotor interface, which is coupled to the upper rotor assembly and the lower rotor assembly the rotor interface being operable to manipulate the upper rotor assembly and the lower rotor assembly independently; and
at least one flight control computer (FCC) to issue the control commands and comprising a central processing unit (CPU) and a memory having logic and executable instructions stored thereon, which, when executed, cause the CPU to issue the control commands based on the current flight conditions and a result of an execution of the logic for the current flight conditions,
wherein the logic generates:
differential collective pitch control commands for setting respective collective pitching of the upper and lower rotor assemblies in an event the speed of the aircraft is below a first speed;
a mix of differential collective and differential cyclic pitch control commands for setting respective collective and cyclic pitching of the upper and lower rotor assemblies in an event the speed of the aircraft is above the first speed and below a second speed; and
angle control commands for setting an angling of active rudders in an event the speed of the aircraft is above the second speed.

2. The aircraft according to claim 1 , wherein the current flight conditions comprise a speed of the aircraft.

3. The aircraft according to claim 2 , wherein the rotor interface selectively controls collective and cyclic pitching of the upper rotor assembly independently of the lower rotor assembly.

4. The aircraft according to claim 3 , wherein the logic comprises at least one of a fly-by-wire (FBW) or smart-control database and an algorithm.

5. The aircraft according to claim 4 , wherein:
the FBW or smart-control database indexes the speed of the aircraft to control commands for setting respective collective pitching of the upper and lower rotor assemblies, and
the algorithm computes control commands for setting respective collective pitching of the upper and lower rotor assemblies.

6. A fly-by-wire (FBW) or smart-control system of a coaxial, counter-rotating aircraft, the FBW or smart-control system comprising:
at least one sensor and at least one inertial measurement unit (IMU) to sense current flight conditions of the aircraft;
interfaces including a rotor interface execute controls to: manipulate an upper rotor assembly independently of a lower rotor assembly of a main rotor assembly, control a translational thrust system, manipulate controllable surfaces, and control an engine in accordance with respective control commands; and
at least one flight control computer (FCC) to issue the control commands and comprising a central processing unit (CPU) and a memory having logic and executable instructions stored thereon, which, when executed, cause the CPU to issue the control commands based on the current flight conditions and a result of an execution of the logic for the current flight conditions,
wherein the logic generates:
differential collective pitch control commands for setting respective collective pitching of the upper and lower rotor assemblies in an event the speed of the aircraft is below a first speed;
a mix of differential collective and differential cyclic pitch control commands for setting respective collective and cyclic pitching of the upper and lower rotor assemblies in an event the speed of the aircraft is above the first speed and below a second speed; and
angle control commands for setting an angling of active rudders in an event the speed of the aircraft is above the second speed.

7. The FBW or smart-control system according to claim 6 , wherein the current flight conditions comprise a speed of the aircraft.

8. The FBW or smart-control system according to claim 7 , wherein the interfaces further comprise:
a translational thrust interface, which is coupled to the translational thrust system to control collective pitch or a power setting of the translational thrust system;
an elevator and rudder actuation interface, which is coupled to active elevators and the active rudders to control an angling thereof;
an engine interface, which is coupled to the engine to control an RPM thereof; and
a propeller clutch interface which is coupled to the propeller clutch to control the propeller engagement state.

9. The FBW or smart-control system according to claim 8 , wherein the logic comprises at least one of an FBW or smart-control database and an algorithm.

10. The FBW or smart-control system according to claim 9 , wherein the FBW or smart-control database indexes the speed of the aircraft to control commands for setting respective collective pitching of the upper and lower rotor assemblies.

11. The FBW or smart-control system according to claim 9 , wherein the algorithm computes control commands for setting respective collective pitching of the upper and lower rotor assemblies.

12. The FBW or smart-control system according to claim 9 , wherein the logic generates envelope control commands for applying respective control envelopes to the upper and lower rotor assemblies.

13. The FBW or smart-control system according to claim 9 , wherein the logic generates a single control command for setting engine RPMs and collective pitch or a power setting of the translational thrust system.

14. The FBW or smart-control system according to claim 9 , wherein the logic generates a control command for setting an RPM schedule to maintain a predefined mach number of the upper and lower rotor assemblies.

15. A fly-by-wire (FBW) or smart-control system of a coaxial, counter-rotating aircraft, the FBW or smart-control system comprising:
at least one sensor and at least one inertial measurement unit (IMU) to sense current flight conditions of the aircraft;
interfaces including a rotor interface execute controls to: manipulate an upper rotor assembly independently of a lower rotor assembly of a main rotor assembly, control a translational thrust system, manipulate controllable surfaces, and control an engine in accordance with respective control commands; and
at least one flight control computer (FCC) to issue the control commands and comprising a central processing unit (CPU) and a memory having logic and executable instructions stored thereon, which, when executed, cause the CPU to issue the control commands based on the current flight conditions and a result of an execution of the logic for the current flight conditions,
wherein the logic generates:
differential collective pitch control commands for setting respective collective pitching of the upper and lower rotor assemblies in an event the speed of the aircraft is below a first speed;
a mix of differential collective and differential cyclic pitch control commands for setting respective collective and cyclic pitching of the upper and lower rotor assemblies in an event the speed of the aircraft is above the first speed and below a second speed; and
angle control commands for setting an angling of active rudders in an event the speed of the aircraft is above the second speed;

wherein the current

Assignees

• Sikorsky Aircraft Corp

Inventors

• Bredenbeck Kevin L
• Cotton Bryan S
• Arifian Kenneth C
• Eller Erez
• Luszcz Matthew T

Classifications

• B64U10/10

  Rotorcrafts · CPC title

• B64C27/08

  with two or more rotors · CPC title

• B64C1/0009

  Aerodynamic aspects · CPC title

• G05D1/0816

  to ensure stability · CPC title

• G05D1/0858

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