AERIAL VEHICLE

• US 20160122010A1
• Filed: 06/26/2015
• Published: 05/05/2016
• Est. Priority Date: 10/31/2014
• Status: Abandoned Application

• Current Assignee: Hon Hai Precision Industry Co., Ltd.
• Original Assignee: Hon Hai Precision Industry Co., Ltd.
• Inventors: TANG, PEI-CHONG
• Application Number:
  US14/752,385
• Publication Number:
  US 20160122010A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: A63H 27/12 Helicopters A63H27/04 takes precedence; Flying tops
• CPC Class Codes: B64U 10/14 with four distinct rotor axes, e.g. quadcopters
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: G01C 19/02 Rotary gyroscopes

Abstract

An aerial vehicle includes a body, a plurality of rotors coupled to the body and configured to provide lift, a plurality of driving devices coupled to the rotors respectively and configured to drive the rotors to rotate, and a control device coupled to the body and the driving devices. The control device includes a gyroscope and a controller. The gyroscope is configured to collect information of rotation speed of the body and transmit the information of the rotation speed to the controller. The controller is configured to provide a driving power for adjusting the rotation speed of the body according the information of the rotation speed, and produce and transmit a control signal of the driving power to the driving devices to output the driving power to corresponding rotors to adjust the rotation speed of the body.

Claims

1. An aerial vehicle comprising:

a body;

a plurality of rotors coupled to the body and configured to provide lift;

a plurality of driving devices coupled to the rotors respectively, and configured to drive the rotors to rotate; and

a control device coupled to the body and the driving devices, the control device comprising a gyroscope and a controller, the gyroscope configured to collect information of rotation speed of the body and transmit the information of the rotation speed to the controller;

wherein, the controller is configured to provide a driving power for adjusting the rotation speed of the body according the information of the rotation speed and to produce and transmit a control signal of the driving power to the driving devices to output the driving power to corresponding rotors to adjust the rotation speed of the body.

2. The aerial vehicle of claim 1, wherein when the aerial vehicle is hovering, the body rotates.

3. The aerial vehicle of claim 2, wherein when the aerial vehicle is hovering, the rotation speed of the body is less than a rotation speed of the rotors.

4. The aerial vehicle of claim 2, wherein body rotates intermittently or with a preset rotation angle.

5. The aerial vehicle of claim 2, further comprising an alarm detection device coupled to the body.

6. The aerial vehicle of claim 5, wherein the alarm detection device comprises a plurality of alarm detectors coupled to the body.

7. The aerial vehicle of claim 6, wherein alarm detectors rotate following rotation of the body.

8. The aerial vehicle of claim 7, wherein the body comprises a ceiling portion, a bottom portion opposite to the ceiling portion and a lateral portion connecting the ceiling portion and the bottom portion, the alarm detection device comprising a first alarm detector coupled to the ceiling portion, a second alarm detector coupled to the bottom portion, and a third alarm detector coupled to the lateral portion.

9. The aerial vehicle of claim 2, wherein the rotors are divided to a first unit and a second unit, the rotors of the first unit rotate anticlockwise, the rotors of the second unit rotate clockwise, rotation speed of the rotors are adjusted by adjusting driving power output from corresponding driving devices to realize flight attitudes of level flight, level rotation, vertical flight, hovering of the aerial vehicle.

10. The aerial vehicle of claim 9, wherein the plurality of rotors comprise four rotors, the two rotors at a diagonal line are belong to the first unit, the other two rotors at another diagonal line are belong to the second unit.

11. The aerial vehicle of claim 2, wherein the control device further comprises an accelerator configured to measure accelerated velocity of the body in flight for stabling balance of the body, and a magnetic compass configured to measure geomagnetic angle for marking nose direction of the aerial vehicle.

12. The aerial vehicle of claim 2, further comprising a plurality of arms integrally extending outwards from the body.

13. The aerial vehicle of claim 12, wherein the driving devices are coupled to distal ends of corresponding arms.