Aircraft Vehicle and a Fixing Sleeve

• US 20150108862A1
• Filed: 10/22/2013
• Published: 04/23/2015
• Est. Priority Date: 10/22/2013
• Status: Active Grant

• Current Assignee: Shenzhen Hubsan Intelligent Co., Ltd.
• Original Assignee: Shenzhen Hubsan Technology Co., Ltd.
• Inventors: Chen, Guangyao
• Granted Patent: US 9,099,902 B2
• Time in Patent Office: Days
• US Class Current: 310/91
• 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 20/40 Modular UAVs
• CPC Class Codes: B64U 20/83 Electronic components structurally integrated with aircraft elements, e.g. circuit boards carrying loads
• CPC Class Codes: B64U 30/291 Detachable rotors or rotor supports
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 70/99 Means for retaining the UAV on the platform, e.g. dogs or magnets
• CPC Class Codes: H02K 11/33 Drive circuits, e.g. power electronics H02K11/38 takes precedence
• CPC Class Codes: H02K 16/00 Machines with more than one rotor or stator machines for transmitting mechanical power from a driving shaft to a driven shaft and comprising structurally interrelated motor and generator parts H02K51/00; permanent magnet machines with multiple rotors or stators relatively rotated for vectorially combining the excitation fields or the armature voltages H02K21/029
• CPC Class Codes: H02K 5/22 Auxiliary parts of casings not covered by groups H02K5/06-H02K5/20, e.g. shaped to form connection boxes or terminal boxes
• CPC Class Codes: H02K 5/225 Terminal boxes or connection arrangements specially adapted for submersible motors H02K5/132

Abstract

This disclosure provides an aircraft vehicle, which comprises a circuit board, and at least one power component mounted on said circuit board. The at least one power component comprises a rotor, a drive unit and a fixing sleeve. Said drive unit is electrically connected to said circuit board and drives the rotor to rotate. Said fixing sleeve comprises a receiving space with an opening at a top. Said fixing sleeve comprises at least one first stopping piece and at least one second stopping piece projected on an outer surface of the fixing sleeve. Said drive unit is accommodated in the receiving space and is secured in the fixing sleeve. Said circuit board comprises at least one positioning hole corresponding to the power component. The fixing sleeve is configured to pass through the positioning hole so that the circuit board is retained between the first stopping piece and the second stopping piece. This disclosure also provides a fixing sleeve. Thus, when the aircraft vehicle falls or collides with another object, the fixing sleeve ensures that the drive unit does not separate from the circuit board, therefore enhancing the performance of the aircraft vehicle.

Claims

1. An aircraft vehicle comprising:

a circuit board and at least one power component mounted on said circuit board;

wherein each of the at least one power component comprises a rotor, a drive unit and a fixing sleeve;

wherein the drive unit is electrically connected to said circuit board and drives the rotor to rotate;

wherein the fixing sleeve comprises a receiving space with an opening at a top;

wherein the fixing sleeve comprises at least one first stopping piece and at least one second stopping piece projected on an outer surface of the fixing sleeve;

wherein the drive unit is configured to be accommodated in the receiving space and is configured to be secured in the fixing sleeve;

wherein the circuit board comprises at least one positioning hole corresponding to the power component; and

wherein the fixing sleeve is configured to pass through the positioning hole so that the circuit board is retained between the first stopping piece and the second stopping piece.

2. The aircraft vehicle of claim 1, wherein the fixing sleeve comprises a base and a pair of oppositely positioned walls;

wherein each wall extends from an edge of the bottom;

wherein the base and the walls together form the receiving space;

wherein the second stopping piece is provided on an outer surface of the wall; and

wherein the first stopping piece is provided between said walls.

3. The aircraft vehicle of claim 2, wherein a pair of oppositely positioned first notches is formed between the walls;

wherein the fixing sleeve comprises a pair of first stopping pieces;

wherein each of the first stopping pieces bends and extends respectively from a bottom of the first notch toward a top of the fixing sleeve;

wherein the circuit board is configured to be secured between an end of the first stopping piece and the second stopping piece.

4. The aircraft vehicle of claim 3, wherein a size of the first notch gradually decreases from a top toward a bottom of the fixing sleeve.

5. The aircraft vehicle of claim 2, wherein a gap forms between said first stopping piece and the walls.

6. The aircraft vehicle of claim 2, wherein an inside of the receiving space of the fixing sleeve is provided with steps;

wherein an end of the wall extends radially toward a center of the receiving space to form a stopping block;

wherein the drive unit is configured to be secured between the steps and the stopping block.

7. The aircraft vehicle of claim 2, wherein a projected piece is provided on an outer surface of the wall;

wherein an inner wall of the positioning hole is provided with a positioning groove in communication with the positioning hole;

wherein the projected piece is configured to be accommodated in the positioning groove.

8. The aircraft vehicle of claim 1, wherein the aircraft vehicle comprises a pair of first power components and a pair of second power components;

wherein the circuit board further comprises a main body, a pair of first support arms that corresponds to the pair of the first power components, and a pair of second support arms that corresponds to the pair of the second power components;

wherein the first support arms and the second support arms extend away respectively from edges of the main body in a radial direction;

wherein one of the first support arms and one of the second support arms are aligned on a straight line, and the other one of the first support arms and the other one of the second support arms are aligned on another straight line;

wherein the circuit board further comprises two pairs of positioning holes respectively provided on ends of the first support arms and ends the second support arm.

9. The aircraft vehicle of claim 8, wherein the first support arms and the second support arms form a X-shape with the main body as a center of said X-shape.

10. The aircraft vehicle of claim 8, wherein the first support arms and the second support arms are provided respectively with hollow regions.

11. The aircraft vehicle of claim 10, wherein the aircraft vehicle further comprises a battery and a battery cover;

wherein the battery is configured to be secured on the main body of the circuit board;

wherein the battery cover shields the battery and is configured to be secured on the circuit board.

12. The aircraft vehicle of claim 11, wherein the battery cover comprises a cover body and a plurality of hooks corresponding to the hollow regions;

wherein the hooks are formed by extending and projecting from an edge of the cover body;

wherein the battery is configured to be accommodated inside the cover body, and the hooks are configured to insert into the corresponding hollow regions to hold against a bottom of the circuit board.

13. The aircraft vehicle of claim 12, wherein the cover body comprises a plurality of second through holes.

14. The aircraft vehicle of claim 8, wherein the aircraft vehicle is configured to be mounted on a support box;

wherein the support box comprises a body with an opening at its bottom;

wherein a top of the body is provided with a pair of first positioning portions corresponding to the first power components, and a pair of second positioning portions corresponding to the second power components;

wherein the fixing sleeve further comprises a pair of retaining pieces at a bottom of the fixing sleeve;

wherein the first positioning portion is configured to engage with the corresponding retaining pieces of the fixing sleeve of the first power component, and wherein the second positioning portion is configured to engage with the corresponding retaining pieces of the second power component of the fixing sleeve, to secure the aircraft vehicle on the support box.

15. The aircraft vehicle of claim 14, wherein each of the first positioning portions comprises a first positioning groove, a tongue piece and a first locking block;

wherein the tongue piece extends from an end of the first positioning groove in a direction parallel to the top surface of the circuit board;

wherein the first locking block is provided in a recess on another end of the first positioning groove;

wherein the retaining pieces of the fixing sleeve of the first power component are configured to clamp and be secured at a bottom of the first locking piece, and the tongue piece is configured to stop and retain the bottom of the retaining pieces of the fixing sleeve.

16. The aircraft vehicle of claim 15, wherein each of the second positioning portions comprises a second positioning groove, a guiding piece and a second locking block;

wherein the guiding piece is provided in a recess of the second positioning groove and connects two ends of the second positioning groove;

wherein the second locking piece is provided at an end further away from the first positioning portion, and is on top of the guiding piece;

wherein the retaining pieces of the fixing sleeve of the second power component are configured to clamp and be secured at a bottom of the second locking block.

17. The aircraft vehicle of claim 16, wherein the retaining piece extends from a bottom of the fixing sleeve away from a top of the fixing sleeve;

wherein an end of the retaining piece bends and extends radially towards a center direction of the fixing sleeve;

wherein a second notch is formed between the ends of the retaining pieces;

wherein the bottom of the fixing sleeve of the first power component is configured to press the corresponding tongue piece of the first positioning portion;

wherein said tongue piece is configured to be accommodated in the second notch of the corresponding fixing sleeve, so that the retaining pieces of the fixing sleeve are configured to slide along the tongue piece and are configured to clamp and be secured at the bottom of the corresponding first locking piece;

wherein the guiding piece of the second positioning portion is configured to be accommodated in the second notch of the corresponding fixing sleeve, so that the retaining pieces of the fixing sleeve are configured to slide along the guiding piece and are configured to clamp and be secured at the bottom of the corresponding second locking piece.

18. The aircraft vehicle of claim 14, wherein the support box further comprises a bottom plate;

wherein the bottom plate is provided at a bottom of the body and shields the body.

19. The aircraft vehicle of claim 1, wherein the circuit board further comprises a connection terminal on the circuit board, and a projecting piece at a bottom of the circuit board;

wherein a connector corresponding to the connection terminal is provided with a receiving slot which is in communication with a jack of the connector;

wherein the connection terminal is configured to insert into the jack, and the projecting piece is configured to be accommodated in the receiving slot, so that the connector is electrically connected to the connection terminal.

20. The aircraft vehicle of claim 18, wherein the connection terminal comprises a pair of copper foils printed on the circuit board.

21. The aircraft vehicle of claim 19, wherein the connection terminal is a charging terminal of the aircraft vehicle.

22. The aircraft vehicle of claim 1, wherein the drive unit is a motor, and the motor is cylindrical in shape.

23. A fixing sleeve with the following characteristics:

wherein the fixing sleeve is configured to secure a power component of an aircraft vehicle on a circuit board;

wherein the power component comprises a rotor and a drive unit that drives the rotor to rotate;

wherein the circuit board comprises positioning holes;

wherein the drive unit is configured to be electrically connected to the circuit board;

wherein the fixing sleeve comprises a receiving space with an opening at a top;

wherein said fixing sleeve further comprises at least one first stopping piece and at least one second stopping piece projected on an outer surface of the fixing sleeve;

wherein the drive unit is configured to be accommodated in the receiving space and secured in the fixing sleeve;

wherein the fixing sleeve is configured to pass through the positioning hole so that the circuit board is configured to be retained between the first stopping piece and the second stopping piece.

24. The fixing sleeve of claim 23, wherein the fixing sleeve comprises a base and a pair of oppositely positioned walls;

wherein each said wall extends from an edge of the bottom;

wherein the base and the walls together form the receiving space;

wherein the second stopping piece is provided on an outer surface of the wall;

wherein the first stopping piece is provided between said walls.

25. The fixing sleeve of claim 24, wherein a pair of oppositely positioned first notches is formed between the walls;

wherein the fixing sleeve comprises a pair of first stopping pieces;

wherein each of the first stopping pieces bends and extends respectively from a bottom of the first notch toward a top of the fixing sleeve;

wherein the circuit board is configured to be retained between an end of the first stopping piece and the second stopping piece.

26. The fixing sleeve of claim 25, wherein the size of the first notch gradually decreases from a top toward a bottom of the fixing sleeve.

27. The fixing sleeve of claim 24, wherein a gap forms between said first stopping piece and the walls.

28. The fixing sleeve of claim 24, wherein an inside of the receiving space of the fixing sleeve is provided with steps;

wherein an end of the wall extends radially toward a center of the receiving space to form a stopping block;

wherein the drive unit is configured to be secured between the steps and the stopping block.

29. The fixing sleeve of claim 24, wherein a projected piece is provided on an outer surface of the wall;

wherein an inner wall of the positioning hole is provided with a positioning groove in communication with the positioning hole;

wherein the projected piece is configured to be accommodated in the positioning groove.

30. The fixing sleeve of claim 23, wherein a bottom of the wall is provided with a first through hole which is in communication with the receiving space.