Teetering propulsor assembly of an electric vertical takeoff and landing aircraft

Abstract

An electric vertical takeoff and landing aircraft including a teetering propulsor assembly is provided. Teetering propulsor assembly may include a propeller that includes a hub and blades. Hub of propeller may be mechanically connected to a teeter mechanism of propulsor assembly that may be configured to allow the propeller to pivot about a teeter axis relative to the electric aircraft. Thus, teeter mechanism allows for a rotational axis of propeller to move during teetering of propeller. Teeter mechanism may include one or more springs that reduce teetering or prevent teetering of the propulsor at certain rotational speeds of propeller.

What is claimed is: 
     
         1 . An electric vertical takeoff and landing aircraft including a teetering propulsor assembly, the electric vertical take-off and landing aircraft comprising:
 a motor;   a propeller driven by the motor, wherein the propeller comprises:
 a monolithic structure; and 
 a hub located longitudinally at a mid-point of the monolithic structure; 
   a teeter mechanism connected to the hub, the teeter mechanism comprising:
 a base rotatably affixed to the electric vertical takeoff and landing aircraft and configured to rotate about a rotational axis; and 
 at least a hinge connecting the base and the propellor and configured to allow the propeller to pivot about the at least a hinge. 
   
     
     
         2 . The electric vertical takeoff and landing aircraft of  claim 1 , further comprising a second motor configured to drive the propeller. 
     
     
         3 . The electric vertical takeoff and landing aircraft of  claim 1 , further comprising a boom configured to be mounted to one or more of the motor and the base. 
     
     
         4 . The electric vertical takeoff and landing aircraft of  claim 1 , wherein the monolithic structure comprises:
 a first blade located on a first side;   a second blade located on a second side; and   wherein the first blade and the second blade each have a fixed pitch.   
     
     
         5 . The electric vertical takeoff and landing aircraft of  claim 1 , wherein the electric vertical takeoff and landing aircraft is configured to be manned. 
     
     
         6 . The electric vertical takeoff and landing aircraft of  claim 1 , further comprising:
 at least a first stop configured to limit pivoting of the propeller about the at least a hinge in a first direction; and   at least a second stop configured to limit pivoting of the propeller about the at least a hinge in a second direction.   
     
     
         7 . The electric vertical takeoff and landing aircraft of  claim 1 , wherein the teeter mechanism further comprises at least a spring configured to affect pivoting of the propeller. 
     
     
         8 . The electric vertical takeoff and landing aircraft of  claim 7 , wherein the at least a spring includes a torsion spring. 
     
     
         9 . The electric vertical takeoff and landing aircraft of  claim 7 , wherein the at least a spring includes a high-capacity laminate. 
     
     
         10 . The electric vertical takeoff and landing aircraft of  claim 1 , wherein:
 the monolithic structure has a longitudinal axis; and   the propellor pivots about the at least a hinge according to a pivot axis which is non-orthogonal to the longitudinal axis of the monolithic structure.   
     
     
         11 . The electric vertical takeoff and landing aircraft of  claim 1 , wherein the hub is configured to be operatively connected to the motor. 
     
     
         12 . The electric vertical takeoff and landing aircraft of  claim 11 , wherein the hub is fixedly attached to a shaft of the motor. 
     
     
         13 . The electric vertical takeoff and landing aircraft of  claim 1 , wherein the propellor is configured to be stopped during flight. 
     
     
         14 . The electric vertical takeoff and landing aircraft of  claim 1 , wherein the teeter mechanism is at least partially disposed within a cavity of the monolithic structure. 
     
     
         15 . 
     
     
         16 . The electric vertical takeoff and landing aircraft of  claim 1 , further comprising:
 a second motor;   a second propeller driven by the second motor, wherein the second propeller comprises:
 a second monolithic structure; and 
 a second hub located longitudinally at a mid-point of the second monolithic structure; 
   a second teeter mechanism connected to the second propellor, the second teeter mechanism comprising:
 a second base rotatably affixed to the electric vertical takeoff and landing aircraft and configured to rotate about the second rotational axis; and 
 at least a second hinge connecting the base and the propellor and configured to allow the propeller to pivot about the at least a hinge. 
   
     
     
         17 . A method for an electric vertical takeoff and landing aircraft including a teetering propulsor assembly, the method comprising:
 driving, using a motor, a propeller, wherein the propeller comprises:
 a monolithic structure; and 
 a hub located longitudinally at a mid-point of the monolithic structure; 
   rotating, using a base of a teeter mechanism connected to the hub, about a rotational axis, wherein the base is rotatably affixed to the electric vertical takeoff and landing aircraft; and   pivoting, using at least a hinge connecting the base and the propellor, the propeller about the at least a hinge.   
     
     
         18 . The method of  claim 17 , further comprising affecting, using at least a of spring, the pivoting of the propeller. 
     
     
         19 . The method of  claim 17 , further comprising:
 limiting, using at least a first stop, pivoting of the propeller about the at least a hinge in a first direction; and   limiting, using at least a second stop, pivoting of the propeller about the at least a hinge in a second direction.   
     
     
         20 . The method of  claim 17 , further comprising manning the electric vertical takeoff and landing aircraft.