INERTIA MEASUREMENT MODULE FOR UNMANNED AIRCRAFT

• US 20140224014A1
• Filed: 09/15/2011
• Published: 08/14/2014
• Est. Priority Date: 09/02/2011
• Status: Active Grant

• Current Assignee: SZ DJI Technology Co., Ltd. (d/b/a DJI) (iFlight Technology Company Limited)
• Original Assignee: SZ DJI Technology Co., Ltd. (d/b/a DJI) (iFlight Technology Company Limited)
• Inventors: Wang, Tao, Zhao, Tao
• Granted Patent: US 9,772,343 B2
• Time in Patent Office: Days
• US Class Current: 73/504.04
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: B64U 2201/00 UAVs characterised by their flight controls
• CPC Class Codes: F16F 15/00 Suppression of vibrations in systems damping of non-rotary systems using inertia effect F16F7/10; prevention or isolation of vibrations in machine tools B23Q11/0032; suppression of driveline vibrations in hybrid vehicle transmissions B60W30/20 ; vehicle seat suspension devices B60N2/50; methods or devices for protecting against, or damping of, acoustic waves, e.g. sound G10K11/16; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion vibration absorbing or balancing means for aircraft propellers B64C11/008, for rotorcraft rotors B64C27/001 ; testing static and dynamic balance of machines or structures G01M1/00
• CPC Class Codes: F16F 7/104 the inertia member being resiliently mounted F16F7/1022 takes precedence
• CPC Class Codes: G01C 19/16 Suspensions; Bearings
• CPC Class Codes: G01C 19/56 Turn-sensitive devices using vibrating masses, e.g. vibratory angular rate sensors based on Coriolis forces
• CPC Class Codes: G01C 19/5628 Manufacturing; Trimming; Mounting; Housings
• CPC Class Codes: G01C 19/5663 Manufacturing; Trimming; Mounting; Housings
• CPC Class Codes: G01C 19/5769 Manufacturing; Mounting; Housings
• CPC Class Codes: G01C 19/5783 Mountings or housings not specific to any of the devices covered by groups G01C19/5607 - G01C19/5719
• CPC Class Codes: G01C 21/166 Mechanical, construction or arrangement details of inertial navigation systems
• CPC Class Codes: G01C 25/00 Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass testing, calibrating or compensating compasses G01C17/38
• CPC Class Codes: G01P 1/003 used for damping
• CPC Class Codes: G01P 1/023 for acceleration measuring devices
• CPC Class Codes: G01P 15/08 with conversion into electric or magnetic values
• CPC Class Codes: G01P 15/0802 Details

Abstract

The present disclosure relates to an inertia measurement module for an unmanned aircraft, which comprises a housing assembly, a sensing assembly and a vibration damper. The vibration damper comprises a first vibration-attenuation cushion; and the sensing assembly comprises a first circuit board, a second circuit board and a flexible signal line for connecting the first circuit board and the second circuit board. An inertia sensor is fixed on the second circuit board, and the first circuit board is fixed on the housing assembly. The inertia measurement module further comprises a weight block, and the second circuit board, the weight block, the first vibration-attenuation cushion and the first circuit board are bonded together. The present disclosure greatly reduces the influence of the operational vibration frequency of the unmanned aircraft on the inertia sensor and improves the measurement stability of the inertia sensor.

Claims

1. An inertia measurement module for an unmanned aircraft, comprising a housing assembly, a sensing assembly and a vibration damper, the sensing assembly and the vibration damper being disposed in the housing assembly, wherein:

the vibration damper comprises a first vibration-attenuation cushion (3) for buffering vibrations;

the sensing assembly comprises a first circuit board (1), a second circuit board (6) and a flexible signal line (7) for communicationally connecting the first circuit board (1) and the second circuit board (6), an inertia sensor is fixedly disposed on the second circuit board (6), and the first circuit board (1) is fixed on the housing assembly;

the inertia measurement module further comprises a weight block (5) for increasing weight, and the second circuit board (6), the weight block (5), the first vibration-attenuation cushion (3) and the first circuit board (1) are bonded together in sequence into one piece and then fitted into the housing assembly.

2. The inertia measurement module for the unmanned aircraft of claim 1, wherein the vibration damper further comprises a second vibration-attenuation cushion (9), which is fixedly bonded on the second circuit board (6) and abuts against an inner wall of the housing assembly.

3. The inertia measurement module for the unmanned aircraft of claim 1, wherein a bonding area S₂ between the second vibration-attenuation cushion (9) and the second circuit board (6) is in a range of 12.6 to 50.2 mm².

4. The inertia measurement module for the unmanned aircraft of claim 1, wherein the weight block (5) has a weight of 1 g to 30 g.

5. The inertia measurement module for the unmanned aircraft of claim 1, wherein a bonding area S₁ between the first vibration-attenuation cushion (3) and the second circuit board (6) is in a range of 12.6 to 50.2 mm².

6. The inertia measurement module for the unmanned aircraft of claim 1, wherein the housing assembly comprises a first housing (13) and a second housing (14) mating with and locked to each other.

7. The inertia measurement module for the unmanned aircraft of claim 1, wherein the second circuit board (6) is fixedly disposed on a supporting sheet, and the supporting sheet is fixedly bonded to the weight block (5).

8. The inertia measurement module for the unmanned aircraft of claim 1, wherein the inertia sensor comprises a gyroscope for detecting an angular speed signal and an accelerometer for detecting an acceleration signal, the angular speed signal and the acceleration signal are transmitted to the first circuit board (1) via the flexible signal line (7).

9. The inertia measurement module for the unmanned aircraft of claim 1, wherein a power source, a memory, a processor and a circuit module are fixedly disposed on the first circuit board (1).

10. The inertia measurement module for the unmanned aircraft of claim 1, wherein the sensing assembly further comprises a signal input interface terminal (11) and a signal output interface terminal (12), the signal input interface terminal (11) and the signal output interface terminal (12) are connected to the first circuit board (1) through interface signals;

and the housing assembly forms an inner chamber that opens at two ends, and the signal input interface terminal (11) and the signal output interface terminal (12) are disposed in the inner chamber and snap-fitted to the two ends of the inner chamber.