Flapping wing aerial vehicles

Patent metadata

Field	Value
Publication number	US-10017248-B2
Application number	US-201514698375-A
Country	US
Kind code	B2
Filing date	Apr 28, 2015
Priority date	Apr 28, 2014
Publication date	Jul 10, 2018
Grant date	Jul 10, 2018

Abstract

An autonomous flapping wing aerial vehicle can have a vehicle body, a pair of flapping wings, tunable wing hinges, and elastic drive mechanisms. The tunable wing hinges can be coupled to the flapping wings. Each wing hinge can be constructed to deliver a force to a respective one of the flapping wings to alter end points of a stroke thereof. The elastic drive mechanisms can rotate the flapping wings about pivot points to produce the strokes of the flapping wings. The elastic drive mechanism can be driven at or near a resonance thereof. Alterations to the strokes of the flapping wings produced by the combined effect of the tunable wing hinges and the elastic drive mechanisms, operating in parallel, can provide steering control of the aerial vehicle.

First claim

The invention claimed is:

1. A flapping wing aerial vehicle comprising:
a vehicle body;
a pair of flapping wings;
tunable wing hinges coupled to the flapping wings, each wing hinge constructed to deliver a force to a respective one of the flapping wings to alter end points of a stroke of the respective flapping wing;
a motor;
a power transmission device; and
elastic drive mechanisms that rotate the flapping wings about pivot points to produce the strokes of the flapping wings,
wherein each tunable wing hinge includes an actuator magnet coupled to a drive portion of the respective flapping wing and an actuator coil that applies a magnetic force to the actuator magnet to alter the end points of the flapping wing stroke,
wherein each elastic drive mechanism comprises a nonlinear spring element coupling a drive portion of the respective flapping wing to a rigid drive arm, and
wherein the power transmission device couples the motor to the rigid drive arm of each elastic drive mechanism and converts rotational motion of the motor into linear motion at each rigid drive arm.

2. The flapping wing aerial vehicle of claim 1 , further comprising rotational drives that rotate the wing hinges about a first axis perpendicular to a direction of the flapping so as to change an inclination of a plane of the stroke of the flapping wing.

3. The flapping wing aerial vehicle of claim 2 , further comprising a controller configured to control the tunable wing hinges to alter the end points or the inclination planes of the flapping wing strokes to produce changes in at least one of roll, pitch, yaw, surge, sideslip, and heave.

4. The flapping wing aerial vehicle of claim 1 , wherein a magnetic field of the actuator magnet is parallel to a magnetic field of the respective actuator coil when the respective flapping wing is at a center of the stroke of the flapping wing.

5. The flapping wing aerial vehicle of claim 1 ,
wherein the nonlinear spring element has a first stiffness when the respective flapping wing is at a center of the stroke of the flapping wing,
wherein the nonlinear spring element has a second stiffness when the respective flapping wing is at either of the end points of the stroke of the flapping wing, and
wherein the first stiffness is greater than the second stiffness.

6. The flapping wing aerial vehicle of claim 1 , wherein the nonlinear spring element comprises a torsion spring or a cantilever spring.

7. The flapping wing aerial vehicle of claim 1 , wherein the power transmission device comprises a Cardan drive mechanism.

8. The flapping wing aerial vehicle of claim 1 ,
wherein the power transmission device comprises a gear train and a crank arm, and
wherein one end of the crank arm is coupled to the gear train and an opposite end of the crank arm is coupled to each of the drive arms.

9. The flapping wing aerial vehicle of claim 1 , further comprising a controller configured to control a speed of the motor to drive each of the elastic drive mechanisms at a frequency within a range from 10% below their resonance frequency to 1% above their resonance frequency.

10. The flapping wing aerial vehicle of claim 9 , wherein a root portion of each of the flapping wings comprises a root spring element, and the controller is configured to control a speed of the motor to drive the flapping wings at a frequency within 5% of their resonance frequency.

11. The flapping wing aerial vehicle of claim 9 , further comprising a sensor that measures angular rate of the aerial vehicle, wherein the controller is configured to control actuation of the flapping wings through the tunable wing hinges and the elastic drive mechanisms so as to cause a change in at least one of yaw rate, roll rate, and pitch rate.

12. A flapping wing aerial vehicle comprising:
a vehicle body;
a pair of flapping wings;
tunable wing hinges coupled to the flapping wings, each wing hinge constructed to deliver a force to a respective one of the flapping wings to alter end points of a stroke of the respective flapping wing;
a motor;
a power transmission device; and
elastic drive mechanisms that rotate the flapping wings about pivot points to produce the strokes of the flapping wings,
wherein each tunable wing hinge includes an actuator magnet coupled to a drive portion of the respective flapping wing and an actuator coil that applies a magnetic force to the actuator magnet to alter the end points of the flapping wing stroke,
wherein each elastic drive mechanism comprises a nonlinear spring element coupling a drive portion of the respective flapping wing to a rigid drive arm,
wherein the power transmission device couples the motor to the rigid drive arm of each elastic drive mechanism and converts rotational motion of the motor into linear motion at each rigid drive arm, and
wherein each of the flapping wings comprises a dihedral angle and a root spring element having vertical flexibility.

13. The flapping wing aerial vehicle of claim 12 , wherein the dihedral angle and the vertical flexibility of the root spring allow a membrane of the flapping wing to deform throughout the stroke, such that a pitch of the flapping wing relative to a plane of the stroke passively changes.

14. The flapping wing aerial vehicle of claim 12 , wherein, for each of the flapping wings, the stroke is along a horizontal direction so as to generate lift in a vertical direction parallel to gravity.

15. The flapping wing aerial vehicle of claim 14 , wherein, for each of the flapping wings, a location in the vertical direction of a wing tip of the respective flapping wing changes as the respective flapping wing moves through the stroke along the horizontal direction.

16. The flapping wing aerial vehicle of claim 15 , wherein as the respective flapping wing moves through the stroke the wing tip of the flapping wing follows a figure-8 pattern.

17. The flapping wing aerial vehicle of claim 6 ,
wherein the cantilever spring comprises a variable length cantilever having a first length at a center of the stroke of the flapping wing and a second length at either end point of the stroke of the flapping wing, and
wherein the second length is greater than the first length.

18. The flapping wing aerial vehicle of claim 6 ,
wherein the torsion spring has a first end coupled to the drive arm and a second end coupled to the drive portion of the flapping wing,
wherein the drive arm drives the torsion spring back and forth along a length of the torsion spring,
wherein, when the flapping wing is at a center of the stroke, motion of the drive portion is parallel to the length of the torsion spring, so as to provide a first stiffness,
wherein, when the flapping wing is at either of the end points of the stroke, motion of the drive portion is perpendicular to the length of the torsion spring, so as to provide a second stiffness, and
wherein the first stiffness is greater than the second stiffness.

19. The flapping wing aerial vehicle of claim 1 , wherein, for each of the flapping wings, the stroke is along a horizontal direction so as to generate lift in a vertical direction parallel to gravity.

20. The flapping wing aerial vehicle of claim 1 , further comprising a controller configured to control end points of the strokes of the flapping wings via the tunable wing hinges and the elastic drive mechanisms so as to cause a change in at least one of yaw rate, roll rate, and pitch rate.

Assignees

• Daedalus Flight Systems Llc
• Univ Maryland

Inventors

• Samuel Paul D
• Faruque Imraan
• Humbert James Sean

Classifications

• B64C33/02 Primary

  Wings; Actuating mechanisms therefor · CPC title

• B64C2201/025

  Operations & Transport · mapped topic

• B64C39/024

  of the remote controlled vehicle type, i.e. RPV · CPC title

• B64U10/40

  Ornithopters · CPC title