Inertia measurement module for unmanned aircraft

Patent metadata

Field	Value
Publication number	US-11293937-B2
Application number	US-202016817261-A
Country	US
Kind code	B2
Filing date	Mar 12, 2020
Priority date	Sep 2, 2011
Publication date	Apr 5, 2022
Grant date	Apr 5, 2022

Abstract

An unmanned aircraft includes a circuit board with an inertia sensor, and a weight block configured to have a flat surface and a recess formed on the flat surface, and a housing assembly configured to form an inner chamber to accommodate the circuit board and the weight block. The circuit board is embedded in the recess by fixedly bonding to the flat surface through adhesion.

First claim

What is claimed is:

1. An unmanned aircraft, comprising:
a first circuit board;
a second circuit board with an inertia sensor;
a weight block configured to have a flat surface and a recess formed on the flat surface, wherein the second circuit board is embedded in the recess by fixedly bonding to the flat surface through adhesion; and
a housing assembly configured to form an inner chamber to accommodate the first circuit board, the second circuit board, and the weight block, wherein the first circuit board is supported by the weight block and being snap-fitted into the housing assembly,
wherein the first circuit board, a vibration-attenuation cushion, the weight block, and the second circuit board are bonded together in sequence, the first circuit board and the second circuit board are disposed at opposite sides with respect to the weight block, and the vibration-attenuation cushion is disposed between the first circuit board and the weight block.

2. The unmanned aircraft of claim 1 , wherein the weight block is made of a metallic material to dissipate heat from the second circuit board.

3. The unmanned aircraft of claim 1 , wherein the second circuit board is further disposed on a supporting sheet that is fixedly bonded to the flat surface of the weight block through an adhesive layer.

4. The unmanned aircraft of claim 1 , wherein the weight block is configured to have a mass such that an inherent frequency of the unmanned aircraft is reduced to be less than an operation frequency of the unmanned aircraft.

5. The unmanned aircraft of claim 4 , wherein the operation frequency of the unmanned aircraft is in a range from 50 Hz to 200 Hz.

6. The unmanned aircraft of claim 1 , wherein the weight block has a weight of about 1 g to 30 g.

7. The unmanned aircraft of claim 1 , wherein the weight block has a cuboidal shape.

8. The unmanned aircraft of claim 1 , wherein the recess of the weight block has a shape and dimensions substantially matching a shape and dimensions of the second circuit board.

9. The unmanned aircraft of claim 1 , wherein the second circuit board is a flexible circuit board.

10. The unmanned aircraft of claim 1 , further comprising:
a vibration damper configured to be disposed in the inner chamber and have an elastic coefficient such that an inherent frequency of the unmanned aircraft is reduced to be less than an operation frequency of the unmanned aircraft.

11. The unmanned aircraft of claim 10 , wherein the vibration damper comprises the vibration-attenuation cushion provided in a sheet form, the vibration-attenuation cushion fixedly bonded to the second circuit board through an adhesive layer and abutting against an inner surface of the housing assembly.

12. The unmanned aircraft of claim 11 , wherein the vibration-attenuation cushion has a length of about 13 mm to 20 mm or a width of about 13 mm to 20 mm.

13. The unmanned aircraft of claim 11 , wherein the vibration-attenuation cushion has a thickness of about 3 mm to 4 mm.

14. The unmanned aircraft of claim 11 , wherein the vibration-attenuation cushion has a hollow part.

15. The unmanned aircraft of claim 14 , wherein the hollow part has a cuboidal shape, a circular shape, an elliptical shape, a rhombus shape, or a quincuncial shape.

16. The unmanned aircraft of claim 10 , wherein the vibration damper comprises the vibration-attenuation cushion provided in a sheet form and disposed on the flat surface of the weight block, the vibration-attenuation cushion extending between the weight block and the first circuit board.

17. The unmanned aircraft of claim 1 , wherein the unmanned aircraft further comprises:
a flexible signal line configured to connect the first circuit board to the second circuit board.

18. The inertia measurement of claim 17 , wherein the first circuit board includes at least one of a power source, a memory, a processor, or a circuit module.

19. The unmanned aircraft of claim 1 , wherein the housing assembly comprises a first housing member and a second housing member configured to be fitted with each other to jointly form the inner chamber.

20. The unmanned aircraft of claim 19 , wherein the first circuit board is configured to be fitted into an inner surface of the first housing member.

Assignees

• Sz Dji Technology Co Ltd

Inventors

• Wang Tao
• Zhao Tao

Classifications

• B64U2201/00

  UAVs characterised by their flight controls · CPC title

• G01C21/166

  Mechanical, construction or arrangement details of inertial navigation systems · CPC title

• G01C19/5663

  Manufacturing; Trimming; Mounting; Housings · CPC title

• G01C19/5769

  Manufacturing; Mounting; Housings · CPC title

• G01C19/56

  Turn-sensitive devices using vibrating masses, e.g. vibratory angular rate sensors based on Coriolis forces · CPC title