UNMANNED AIRCRAFT SYSTEM (UAS) WITH ACTIVE ENERGY HARVESTING AND POWER MANAGEMENT

• US 20170297707A1
• Filed: 12/23/2016
• Published: 10/19/2017
• Est. Priority Date: 09/28/2012
• Status: Active Grant

• Current Assignee: John P. Waszczak, Scott B. Rollefstad
• Original Assignee: John P. Waszczak, Scott B. Rollefstad
• Inventors: Rollefstad, Scott B., Waszczak, John P.
• Granted Patent: US 9,938,011 B2
• Time in Patent Office: Days
• CPC Class Codes: B64D 41/00 Power installations for auxiliary purposes
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 2201/104 using satellite radio beacon positioning systems, e.g. GPS
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/293 Foldable or collapsible rotors or rotor supports
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 50/34 In-flight charging photovoltaics B64U50/31
• CPC Class Codes: B64U 80/00 Transport or storage specially adapted for UAVs
• CPC Class Codes: G05D 1/0005 with arrangements to save energy
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

A method of harvesting and managing energy from air currents, by small unmanned aircraft systems (UAS) having a plurality of powered and unpowered rotors, to increase the aircraft'"'"'s flight time, especially where the mission requires extensive hovering and loitering, is provided. Conventional powered rotors create lift for the aircraft. Unpowered rotors can either be: 1) Free-wheeling rotors which increase the plan form area of aircraft as they rotate, increasing lift, and reducing the power draw on the battery, and/or 2) Rotors connected to micro-generators, which serve as a brake on the unpowered rotors, create electrical power to charge the aircraft batteries or directly power the aircraft'"'"'s electronics. The invention'"'"'s folding rotor arm design results in a compact package that is easily transported by a single user (man portable). The aircraft can be removed from its protective tube, unfolded and launched for flight in less than a minute. Extended flight times, compact easily transported design, and ability to host flight software on a user'"'"'s tablet/PC result in low total cost of ownership.

Claims

1. A battery optimization system for a rotary-wing aircraft comprising:

a. a battery-powered airframe having a plurality of powered and unpowered rotors, data and power buses, and sensors selected from the group consisting of a wind speed/direction sensor, an altimeter and a magnetometer;

b. an on-board GNC system in electronic communication with said data and power buses through which said autopilot is connected to said sensors, said autopilot also being in electronic communication with said powered and unpowered rotors;

c. one or more batteries in electrical communication with said system;

d. electric motors connected to and for driving each powered rotor, said electric motors being in electrical communication with said system;

e. a micro-generator connected to each unpowered rotor, said micro-generator being in electrical communication with said system;

f. a battery controller for, when in hover, loiter, or in-flight mode, directing power from said micro-generators to either one or more batteries thereby recharging it/them, or directing power to said power bus thereby powering said aircraft electronics whereby battery drain is minimized.

2. The system of claim 1 wherein said sensors further comprise a GPS system and a 3-axis gyroscope/accelerometer.

3. The system of claim 1 wherein said electric motor is a direct current brushless motor.

4. The system of claim 3 wherein each brushless DC motor is in electrical communication with an ESC.

5. The system of claim 1 wherein said autopilot comprises software that receives data from a wind speed sensor and if the wind speed exceeds a pre-set value, the autopilot orients the aircraft substantially upwards and into the wind.

6. The system of claim 1 wherein said autopilot comprises software that allows at least one unpowered rotor connected to a micro-generator to freewheel and subsequently signals said battery controller to direct the current generated to either recharge at least one of the batteries or to power the aircraft electronics.

7. The system of claim 6 wherein said battery controller comprises software that will direct current to power the aircraft electronics operations if all batteries are fully charged.

8. The system of claim 6 wherein the battery controller comprises software that will compare battery charge levels and direct current to the battery with the lowest charge.

9. The system of claim 1 wherein said electric motors or micro-generators are connected to an articulating knuckle that is connected to the aircraft.