Methods and apparatus for unmanned aerial vehicle landing and launch

Abstract

An unmanned aerial vehicle (UAV), a stand for launching, landing, testing, refueling and recharging a UAV, and methods for testing, landing and launching the UAV are disclosed. Further, embodiments may include transferring a payload onto or off of the UAV, and loading flight planning and diagnostic maintenance information to the UAV.

What is claimed is: 
     
         1 . A stand configured for landing and launching an aerial vehicle, the stand comprising:
 a rotatable base;   a plurality of shafts configured to extend upward from the rotatable base to capture the aerial vehicle, each shaft configured to capture the aerial vehicle by coupling fittings of the aerial vehicle to the plurality of shafts; and   a motor configured to rotate the rotatable base to align the plurality of shafts with the coupling fittings of the aerial vehicle.   
     
     
         2 . The stand of  claim 1 , further comprising processing circuitry configured to control rotation of the rotatable base in response to yaw torque of the aerial vehicle detected by a sensor. 
     
     
         3 . The stand of  claim 2 , wherein the processing circuitry is further configured to receive yaw measurement information from the aerial vehicle and to control the motor based at least in part on the received yaw measurement information. 
     
     
         4 . The stand of  claim 1 , further comprising processing circuitry configured to perform diagnostic testing of the aerial vehicle. 
     
     
         5 . The stand of  claim 1 , further comprising processing circuitry to test at least one of a pitch force, a roll force and a yaw force of the aerial vehicle. 
     
     
         6 . The stand of  claim 1 , further comprising processing circuitry configured to perform a motor lift power test of at least one motor of the aerial vehicle. 
     
     
         7 . The stand of  claim 1 , further comprising a strain gauge load cell to generate a signal indicative of one of a lift force, a pitch force, the roll force and the yaw force. 
     
     
         8 . The stand of  claim 1 , further comprising processing circuitry configured to determine at least one of a roll stability test, a pitch stability test and a yaw stability test. 
     
     
         9 . The stand of  claim 1 , further comprising processing circuitry configured to determine at least one of a pitch, roll and yaw torque of the aerial vehicle when the aerial vehicle is captured by the stand. 
     
     
         10 . The stand of  claim 1 , further comprising processing circuitry configured to monitor an approach by the aerial vehicle to the stand. 
     
     
         11 . The stand of  claim 1 , further comprising processing circuitry configured to control a flight of the aerial vehicle during one of landing and launching of the aerial vehicle. 
     
     
         12 . The stand of  claim 1 , further comprising a sensor configured to sense a rotational alignment of the coupling fittings with the plurality of shafts. 
     
     
         13 . The stand of  claim 1 , wherein at least one shaft of the plurality of shafts is configured to capture the aerial vehicle by a magnetic force generated by at least one magnet. 
     
     
         14 . The stand of  claim 1 , further comprising an accelerometer mounted on the at least one shaft to sense contact of the coupling fittings with the at least one shaft. 
     
     
         15 . The stand of  claim 1 , further comprising processing circuitry configured to determine a rate of at least one of pitch, roll and yaw measured by at least one accelerometer of the aerial vehicle. 
     
     
         16 . The stand of  claim 1 , further comprising a plurality of electromagnets that are configurable to be energized to propel the aerial vehicle upward and to brake a descent of the aerial vehicle. 
     
     
         17 . The stand of  claim 1 , further comprising processing circuitry configured to one of activate and deactivate electromagnets on the aerial vehicle in response to detecting an approach of the aerial vehicle, the electromagnetics being configured to create a magnetic force of attraction between the aerial vehicle and the stand. 
     
     
         18 . The stand of  claim 1 , further comprising processing circuitry configure to one of activate and deactivate electromagnets on the aerial vehicle includes to one of propel the aerial vehicle in a launch direction and to reduce velocity of the aerial vehicle in a landing direction. 
     
     
         19 . The stand of  claim 1 , wherein at least one shaft of the plurality of shafts includes electromagnets configured to be at least one of activated and deactivated by the aerial vehicle. 
     
     
         20 . The stand of  claim 1 , wherein the rotatable base is translatable in at least one direction.