Aircraft system

• US 10,053,229 B2
• Filed: 12/18/2015
• Issued: 08/21/2018
• Est. Priority Date: 12/18/2014
• Status: Active Grant

• Current Assignee: Yuneec Technology Co., Limited
• Original Assignee: Yuneec Technology Co., Limited
• Inventors: Tian, Yu, Jiang, Wenyan
• Primary Examiner(s): Laballe, Clayton E
• Assistant Examiner(s): Smith, Linda B
• Application Number:
  US15/529,779
• Publication Number:
  US 20170305574A1
• Time in Patent Office: 977 Days
• Field of Search: 396 12
• CPC Class Codes: B64D 47/08 Arrangements of cameras
• CPC Class Codes: B64U 20/87 Mounting of imaging devices, e.g. mounting of gimbals
• CPC Class Codes: F16M 11/041 Allowing quick release of the apparatus
• CPC Class Codes: F16M 11/08 around a vertical axis , e.g. panoramic heads F16M11/12 takes precedence
• CPC Class Codes: F16M 11/10 around a horizontal axis F16M11/12 takes precedence
• CPC Class Codes: F16M 11/2035 in more than one direction
• CPC Class Codes: F16M 11/2071 for panning and rolling F16M11/2078 takes precedence
• CPC Class Codes: F16M 13/02 for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
• CPC Class Codes: G03B 15/006 Apparatus mounted on flying objects
• CPC Class Codes: G03B 17/561 Support related camera accessories
• CPC Class Codes: G03B 2206/00 Systems for exchange of information between different pieces of apparatus, e.g. for exchanging trimming information, for photo finishing
• CPC Class Codes: H04N 23/63 by using electronic viewfinders
• CPC Class Codes: H04N 23/661 Transmitting camera control signals through networks, e.g. control via the Internet
• CPC Class Codes: H04N 7/18 Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
• CPC Class Codes: H04N 7/185 from a mobile camera, e.g. for remote control

Abstract

An aircraft system (1) includes an aircraft apparatus (31) including an image capturing device (33) and a remote control (32). The remote control (32) includes a display (321), a first communication circuit (322) adapted for transmitting aircraft control signals to the aircraft apparatus (31), and a second communication circuit (323) adapted for receiving image signals of the image capturing device. The display (321) is adapted for displaying the image signals.

Claims

1. An aircraft system, comprising an aircraft apparatus comprising an image capturing device and a remote control, wherein:

the remote control comprises a display, a first communication circuit adapted for transmitting aircraft control signals to the aircraft apparatus, and a second communication circuit adapted for receiving image signals of the image capturing device;

the display is adapted for displaying the image signals;

the aircraft apparatus comprises a gimbal, an aircraft unit is connected with the image capturing device through the gimbal;

the gimbal is connected with the aircraft unit through a gimbal connector;

the gimbal connector comprises a connecting body;

two buckling parts respectively outwardly extend from a front side and a rear side of the connecting body, so as to buckle with the gimbal for limiting the movement of the gimbal in the vertical direction and the front and rear directions;

an upper shock absorption plate is disposed between the gimbal connector and the gimbal;

two buckling components, respectively corresponding to the two buckling parts, are disposed at a top surface of the upper shock absorption plate;

the two buckling components are respectively buckled with the two buckling parts;

a position where the top surface of the upper shock absorption plate is close to the two buckling components has two channels, each of the two buckling components has an L-shaped cross section;

the two channels are respectively located under the two buckling components;

two first limit parts respectively outwardly extend from a front side and a rear side at a right end portion of the connecting body, and are respectively against a right end portion of the two buckling components;

the connecting body has an accommodating groove at a left end portion thereof;

a second limit part is disposed at a left end face of the accommodating groove, is located in the accommodating groove, and is against the left end face of the upper shock absorption plate.

2. The aircraft system, as recited in claim 1, wherein the aircraft apparatus comprises a power supply circuit for providing the image capturing device with power.

3. The aircraft system, as recited in claim 1, wherein the first communication circuit is a 2.4 GHz communication circuit, the second communication circuit is a 5.8 GHz communication circuit.

4. The aircraft system, as recited in claim 1, wherein the aircraft apparatus comprises an aircraft control circuit;

the gimbal comprises a first motor, a second motor, a third motor, an image transmission unit and an inertial measurement unit, wherein the first motor, the second motor and the third motor are respectively adapted for controlling the rotation along three axial directions of a three-dimensional coordinate system;

the aircraft control unit is adapted for respectively electrically connecting with the first motor, the second motor and the third motor through three-phase wires, and is also adapted for electrically connecting with the inertial measurement unit through communication wires.

5. The aircraft system, as recited in claim 1, wherein the second communication circuit is a 5.8 GHz Wi-Fi communication circuit.

6. The aircraft system, as recited in claim 2, wherein the aircraft apparatus comprises an aircraft control circuit;

the gimbal comprises a first motor, a second motor, a third motor, an image transmission unit and an inertial measurement unit, wherein the first motor, the second motor and the third motor are respectively adapted for controlling the rotation along three axial directions of a three-dimensional coordinate system;

the aircraft control unit is adapted for respectively electrically connecting with the first motor, the second motor and the third motor through three-phase wires, and is also adapted for electrically connecting with the inertial measurement unit through communication wires.

7. The aircraft system, as recited in claim 2, wherein the second communication circuit is a 5.8 GHz Wi-Fi communication circuit.

8. The aircraft system, as recited in claim 2, wherein the first communication circuit is a 2.4 GHz communication circuit, the second communication circuit is a 5.8 GHz communication circuit.

9. The aircraft system, as recited in claim 3, wherein the aircraft apparatus comprises an aircraft control circuit;

the gimbal comprises a first motor, a second motor, a third motor, an image transmission unit and an inertial measurement unit, wherein the first motor, the second motor and the third motor are respectively adapted for controlling the rotation along three axial directions of a three-dimensional coordinate system;

the aircraft control unit is adapted for respectively electrically connecting with the first motor, the second motor and the third motor through three-phase wires, and is also adapted for electrically connecting with the inertial measurement unit through communication wires.

10. The aircraft system, as recited in claim 3, wherein the second communication circuit is a 5.8 GHz Wi-Fi communication circuit.

11. The aircraft system, as recited in claim 4, wherein the second communication circuit is a 5.8 GHz Wi-Fi communication circuit.

12. The aircraft system, as recited in claim 6, wherein the second communication circuit is a 5.8 GHz Wi-Fi communication circuit.

13. The aircraft system, as recited in claim 8, wherein the aircraft apparatus comprises an aircraft control circuit;

the gimbal comprises a first motor, a second motor, a third motor, an image transmission unit and an inertial measurement unit, wherein the first motor, the second motor and the third motor are respectively adapted for controlling the rotation along three axial directions of a three-dimensional coordinate system;

the aircraft control unit is adapted for respectively electrically connecting with the first motor, the second motor and the third motor through three-phase wires, and is also adapted for electrically connecting with the inertial measurement unit through communication wires.

14. The aircraft system, as recited in claim 8, wherein the second communication circuit is a 5.8 GHz Wi-Fi communication circuit.

15. The aircraft system, as recited in claim 9, wherein the second communication circuit is a 5.8 GHz Wi-Fi communication circuit.

16. The aircraft system, as recited in claim 13, wherein the second communication circuit is a 5.8 GHz Wi-Fi communication circuit.