Multi-Rotor Aircraft

• US 20160137298A1
• Filed: 03/07/2014
• Published: 05/19/2016
• Est. Priority Date: 03/14/2013
• Status: Active Grant

• Current Assignee: Curtis Youngblood
• Original Assignee: Curtis Youngblood
• Inventors: Youngblood, Curtis
• Granted Patent: US 9,499,263 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: A63H 27/12 Helicopters A63H27/04 takes precedence; Flying tops
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/14 with four distinct rotor axes, e.g. quadcopters
• CPC Class Codes: B64U 20/70 Constructional aspects of the UAV body
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/297 Tilting rotors
• CPC Class Codes: B64U 40/10 for adjusting control surfaces or rotors
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 50/23 with each propulsion means having an individual motor

Abstract

Disclosed is a multi-rotor aircraft having a hollow center boom from which extends three or more leg booms disposed generally perpendicular to the center boom and on which is mounted rotor bases that have rotor rotation means and rotor blades. In another aspect the invention is programmed means for control of the craft described above and methods of control of the craft in flight.

Claims

1. A multi-rotor aircraft comprising a center boom from which extends three or more leg booms, the leg booms disposed generally perpendicular to the center boom, and on which is mounted rotor bases that have rotor rotation means and rotor blades.

2. The multi-rotor aircraft of claim 1 also comprising:

a drive means capable of connection to rotor drive means on the rotor bases to rotate rotor blades;

a radio control receiver;

a flight control module;

servomotors capable of receiving signals from the flight controller that are connected to and function to control rotor blade pitch.

3. The multi-rotor aircraft of claim 1 wherein the rotor arms are disposed relative to the center boom in the same plane as the center boom or are tilted upward or downward from the horizontal plane of the center boom.

4. The multi-rotor aircraft of claim 1 wherein the rotor bases and the rotor blades are tilted forward or backward relative to the perpendicular plane of the center boom.

5. The multi-rotor aircraft of claim 1 wherein there are separate drive means for each rotor, each capable of separate control.

6. The multi-rotor aircraft of claim 2 wherein the drive means is selected from the group consisting of electric motor, nitro motor, gas powered motor and turbine.

7. The multi-rotor aircraft of claim 6 comprising servomotors capable of receiving signals from the flight controller that are connected to and function to control rotor blade pitch angle.

8. The multi-rotor aircraft of claim 1 also comprising a drive shaft located in the hollow center boom connected to the drive means and to means to drive each rotor.

9. The multi-rotor aircraft of claim 8 wherein the drive means for each rotor is a motor connected to a drive shaft.

10. The multi-rotor aircraft of claim 1 also comprising a canopy pivot/latching system and centrally supported landing struts.

11. The multi-rotor aircraft of claim 1 wherein the dimensions, materials and configuration of the components provide flexibility and specific rotor set configurations make use of twisting of the front boom relative to the back boom through the center boom for improved Yaw performance.

12. A flight control module comprising a programmable electronic computational unit that is capable of receiving varying multiple input signals, adjusting and/or modifying the input signals, generating signals from the adjusted or modified input to provide output signals to control means to adjust flight functions of a multi-rotor aircraft.

13. The flight control module of claim 12 programmed to apply the functions from the groups consisting of those steps schematically shown in FIG. 8, FIG. 8A, Figure, 9, FIGS. 10 and 11, FIG. 12, FIG. 13 and FIG. 14.

14. The flight control module of claim 12 programmed to apply functions to control stability of take-off flight and/or to apply functions to control stability of landings, in which certain functions are disabled and/or to apply functions to place the craft into Car mode of operation

15. The flight control module of claim 12 programmed to apply functions to limit control near/in the “

reverse zone”

in flight and/or to apply functions to control collective step to avoid zero lift issue.

16. The flight control module of claim 12 programmed to apply functions to control Reversing Rudder when going from positive to negative collective position.

17. A method for controlling the flight of a multi-rotor aircraft having separate drive means for each rotor, each capable of separate control comprising manipulating means for adjusting rotor rpm and rotor blade pitch to achieve a desired flight control effects.

18. The method of claim 17 wherein the control effect is the simultaneous input of rotor rpm and blade pitch or variable application of one relative to the other to obtain a desired flight control effect.

19. The method of claim 17 wherein the control effect is alteration of rotor rpm around zero within a set range of collective to allow for drops through Zero pitch range.

20. The method of claim 17 wherein the control effect is used when pitch change is limited to efficient blades range, rotor RPM is varied to retain large lifting control range.

21. The method of claim 17 wherein the control effect is for use a variable pitch rotor reaches a control limit the range of lift is expanded by increasing the rpm.

22. The method of claim 17 wherein the control effect is to achieve automatic gain change, either up or down, in response to variations in rotor rpm.