Compound Aircraft Control System and Method

• US 20100324758A1
• Filed: 06/29/2010
• Published: 12/23/2010
• Est. Priority Date: 08/16/2006
• Status: Active Grant

• Current Assignee: Andrew S. Greenjack, Frank N. Piasecki, Joseph F. Horn
• Original Assignee: Andrew S. Greenjack, Frank N. Piasecki, Joseph F. Horn
• Inventors: Horn, Joseph F., Greenjack, Andrew S., Piasecki, Frank N.
• Granted Patent: US 8,463,465 B2
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64C 2027/8236 including pusher propellers
• CPC Class Codes: B64C 2027/829 comprising a V-tail units
• CPC Class Codes: B64C 27/26 characterised by provision of fixed wings
• CPC Class Codes: B64C 27/82 characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
• CPC Class Codes: G05D 1/0858 specially adapted for vertical take-off of aircraft

Abstract

The Invention is a control system for a compound aircraft. A compound aircraft has features of both a helicopter and a fixed wing aircraft and provides redundant control options. The control system allows an authorized person to select any of plurality of operational objectives each of which is designed to achieve any particular command.

Claims

1. A compound aircraft, the compound aircraft comprising:

a. a fuselage;

b. a rotor, said rotor being rotatably attached to said fuselage, said rotor being configured to have a selectable cyclic pitch;

c. a wing, said wing being attached to said fuselage;

d. a plurality of control effectors attached to said fuselage;

e. a microprocessor operably connected to said plurality of control effectors, said microprocessor being configured to operate said control effectors;

f. A computer memory operably connected to said microprocessor;

g. a plurality of selectable overall operational objectives stored within said computer memory;

h. a selector, said selector being configured to select a one of said overall operational objectives from among said plurality of overall operational objectives, said selector being operably connected to said microprocessor;

i. a sensor, said sensor being configured to detect a condition of the compound aircraft, said sensor being operably connected to said microprocessor;

i. a plurality of combinations of trim control settings to control at least a one of a roll, a pitch and a yaw of the compound aircraft, said plurality of combinations of trim control settings being stored within said computer memory;

j. said microprocessor being configured to receive a command, said microprocessor being programmed to select a one of said plurality of said combinations of trim control settings in response to said command, said microprocessor being programmed to select said one of said plurality of said combinations of trim control settings;

(i) based upon said selected one of said overall operational objectives, and

(ii) based upon said condition of the compound aircraft, and

(iii) based upon said command.

2. The compound aircraft of claim 1 wherein said selected one of said plurality of said combinations of trim control settings includes said trim control settings for said wing and said cyclic pitch to control said roll of the compound aircraft.

3. The compound aircraft of claim 2, the compound aircraft further comprising:

a plurality of combinations of weighting factors, said plurality of combinations of said weighting factors being stored in said computer memory, said microprocessor being programmed to select a one of said plurality of said combinations of weighting factors in response to said command, said selected one of said plurality of said combinations of weighting factors being associated with said selected one of said overall operational objectives and said condition of the compound aircraft, said selected one of said plurality of said combinations of weighting factors including said weighting factors to control said roll of the compound aircraft in maneuvering flight utilizing said wing and said cyclic pitch.

4. The compound aircraft of claim 1, the compound aircraft further comprising an elevator, said elevator being attached to said fuselage, said selected one of said plurality of said combinations of trim control settings including said trim control settings for said elevator and said cyclic pitch to control said pitch of the compound aircraft.

5. The compound aircraft of claim 4, the compound aircraft further comprising:

a plurality of combinations of weighting factors, said plurality of combinations of said weighting factors being stored in said computer memory, said microprocessor being programmed to select a one of said plurality of said combinations of weighting factors in response to said command, said selected one of said plurality of said combinations of weighting factors being associated with said selected one of said overall operational objectives and said condition of the compound aircraft, said selected one of said plurality of said combinations of weighting factors including said weighting factors to control said pitch of the compound aircraft in maneuvering flight utilizing said elevator and said cyclic pitch.

6. The compound aircraft of claim 1, the compound aircraft including at least two of a rudder attached to said fuselage, a sector attached to said fuselage, a vane attached to said fuselage and a collective pitch of said rotor, said at least two of said rudder, said sector, said vane and said collective pitch each being configured to apply a selectable yawing moment to said fuselage, said selected one of said combinations of trim control settings including trim settings for said at least two of said rudder, said sector, said vane and said collective pitch to control said yaw of the compound aircraft.

7. The compound aircraft of claim 6, the compound aircraft further comprising:

a plurality of combinations of weighting factors, said plurality of combinations of said weighting factors being stored in said computer memory, said microprocessor being programmed to select a one of said plurality of said combinations of weighting factors in response to said command, said selected one of said plurality of said combinations of weighting factors being associated with said selected one of said overall operational objectives and said condition of the compound aircraft, said selected one of said plurality of said combinations of weighting factors including said weighting factors to control said yaw of the compound aircraft in maneuvering flight utilizing said at least two of said rudder, said sector, said vane and said collective pitch.