Uav with transformable arms

Abstract

An unmanned aerial vehicle (UAV) includes a central body and a plurality of arms extending from the central body. Each of the plurality of arms supports one or more propulsion units. At least one arm of the plurality of arms is configured to transform between (1) a flight configuration that provides lift while the UAV is in flight and (2) a landing configuration in which the at least one arm is configured to function as a landing support that bears weight of the UAV while the UAV is not in flight. The at least one arm is configured to transform between the flight configuration and the landing configuration in response to operation of the one or more propulsion units supported by the at least one arm.

What is claimed is: 
     
         1 . An unmanned aerial vehicle (UAV) comprising:
 a central body;   a plurality of arms extending from the central body, each of the plurality of arms supporting one or more propulsion units,   wherein at least one arm of the plurality of arms is configured to transform between (1) a flight configuration that provides lift while the UAV is in flight and (2) a landing configuration in which the at least one arm is configured to function as a landing support that bears weight of the UAV while the UAV is not in flight, and   wherein the at least one arm is configured to transform between the flight configuration and the landing configuration in response to operation of the one or more propulsion units supported by the at least one arm.   
     
     
         2 . The UAV of  claim 1 , wherein an orientation of a distal end of the at least one arm is changed when the at least one arm is transformed between the flight configuration and the landing configuration. 
     
     
         3 . The UAV of  claim 1 , wherein when the at least one arm is transforming to the flight configuration, a landing gear portion of the at least one arm is retracted away from an underlying surface in response to the one or more propulsion units supported by the at least one arm generating lift to lift the landing gear portion away from the underlying surface. 
     
     
         4 . The UAV of  claim 3 , further comprising a limiting structure that prevents the landing gear portion from exceeding a preset configuration. 
     
     
         5 . The UAV of  claim 1 , wherein when the at least one arm is transforming to the landing configuration, a landing gear portion of the at least one arm is opened toward an underlying surface in response to the one or more propulsion units supported by the at least one arm reducing an amount of propulsion such that gravity brings the landing gear portion toward the underlying surface. 
     
     
         6 . The UAV of  claim 1 , wherein a distal end of the at least one arm extends beyond a location of the one or more propulsion units supported by the at least one arm. 
     
     
         7 . The UAV of  claim 6 , wherein:
 the distal end of the at least one arm is a landing gear configured to contact an underlying surface while the UAV is not in flight, and   the distal end of the at least one arm has a greater area than a cross-sectional area of the at least one arm where the one or more propulsion units are supported.   
     
     
         8 . The UAV of  claim 6 , wherein the at least one arm further comprises an auxiliary support extending substantially perpendicular from the distal end of the at least one arm, wherein the auxiliary support is configured to contact an underlying surface of the UAV in a substantially parallel manner while the UAV is not in flight. 
     
     
         9 . The UAV of  claim 8 , wherein the auxiliary support comprises an extension disposed at the distal end on a side opposing the one or more propulsion units, the extension being configured to avoid running into another object when the at least one arm is automatically transforming while the UAV is landing. 
     
     
         10 . The UAV of  claim 8 , wherein the auxiliary support comprises an extension disposed at the distal end on a side adjacent to the one or more propulsion units, the extension being configured to protect the one or more propulsion units. 
     
     
         11 . The UAV of  claim 1 , wherein at least half of the plurality of arms are configured to transform between the flight configuration and the landing configuration. 
     
     
         12 . The UAV of  claim 1 , wherein the one or more propulsion units include rotor blades, and adjusting a speed of rotation of the one or more rotor blades affects whether the at least one arm is in the flight configuration or the landing configuration. 
     
     
         13 . The UAV of  claim 1 , wherein the plurality of arms are substantially coplanar while the UAV is in flight. 
     
     
         14 . A method for unmanned aerial vehicle (UAV) operation, comprising:
 supporting one or more propulsion units on each of a plurality of arms extending from a central body; and   transforming at least one of the plurality of arms between (1) a flight configuration that provides lift while the UAV is in flight and (2) a landing configuration in which the at least one arm is configured to function as a landing support that bears weight of the UAV while the UAV is not in flight,   wherein the at least one arm is configured to transform between the flight configuration and the landing configuration in response to operation of the one or more propulsion units supported by the at least one arm.   
     
     
         15 . The method of  claim 14 , wherein transforming the at least one arm between the flight configuration and the landing configuration comprises changing an orientation of a distal end of the at least one arm. 
     
     
         16 . The method of  claim 14 , wherein transforming to the flight configuration comprises retracting a landing gear portion of the at least one arm away from an underlying surface in response to the one or more propulsion units supported by the at least one arm generating lift to lift the landing gear portion away from the underlying surface. 
     
     
         17 . The method of  claim 16 , further comprising providing a limiting structure that prevents the landing gear portion from exceeding a preset configuration. 
     
     
         18 . The method of  claim 16 , wherein transforming to the landing configuration comprises opening a landing gear portion of the at least one arm toward an underlying surface in response to the one or more propulsion units supported by the at least one arm reducing an amount of propulsion such that gravity brings the landing gear portion toward the underlying surface. 
     
     
         19 . The method of  claim 14 , wherein a distal end of the at least one arm extends beyond a location of the one or more propulsion units supported by the at least one arm. 
     
     
         20 . The method of  claim 19 , wherein:
 the distal end of the at least one arm is a landing gear configured to contact an underlying surface while the UAV is not in flight, and   the distal end of the at least one arm has a greater area than a cross-sectional area of the at least one arm where the one or more propulsion units are supported.