Inertia measurement module for unmanned aircraft

Abstract

An unmanned aircraft includes a circuit board with an inertia sensor, a vibration damper configured to attenuate vibration of the inertia sensor, a weight block configured to provide support for positioning the circuit board, and a housing assembly configured to form an inner chamber to accommodate the circuit board and the weight block. The vibration damper includes a first vibration-attenuation cushion and a second vibration-attenuation cushion bonded respectively to a first side and a second side of the circuit board. The weight block is disposed between the first vibration-attenuation cushion and the circuit board.

1 . (canceled) 
     
     
         2 . An unmanned aircraft, comprising:
 a circuit board with an inertia sensor;   a vibration damper configured to attenuate vibration of the inertia sensor, the vibration damper comprising a first vibration-attenuation cushion and a second vibration-attenuation cushion bonded respectively to a first side and a second side of the circuit board;   a weight block configured to provide support for positioning the circuit board, the weight block being disposed between the first vibration-attenuation cushion and the circuit board; and   a housing assembly configured to form an inner chamber to accommodate the circuit board and the weight block.   
     
     
         3 . The unmanned aircraft of  claim 2 , wherein at least one of the first and second vibration-attenuation cushions is made of an elastic material having a predetermined number of cavities associated with an elastic performance of the elastic material. 
     
     
         4 . The unmanned aircraft of  claim 2 , wherein the second vibration-attenuation cushion is fixed bonded to the circuit board through an adhesive layer having a predetermined size. 
     
     
         5 . The unmanned aircraft of  claim 2 , wherein a bonding area between the second vibration-attenuation cushion and the circuit board is in a range between 12.6 mm 2  and 50.2 mm 2 . 
     
     
         6 . The unmanned aircraft of  claim 2 , wherein the circuit board is embedded into a recess formed on a flat surface of the weight block and is disposed on a supporting sheet that is fixedly bonded to the flat surface through adhesion. 
     
     
         7 . The unmanned aircraft of  claim 2 , wherein the weight block has a weight of about 1 g to 30 g. 
     
     
         8 . The unmanned aircraft of  claim 6 , wherein the recess of the weight block has a shape and dimensions substantially matching a shape and dimensions of the circuit board. 
     
     
         9 . The unmanned aircraft of  claim 2 , wherein the circuit board is a flexible circuit board. 
     
     
         10 . The unmanned aircraft of  claim 2 , wherein the vibration damper is disposed in the inner chamber and has 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 2 , wherein each of the first vibration-attenuation cushion and the second vibration-attenuation cushion is fixedly bonded to the circuit board respectively through an adhesive layer and abutting against an inner surface of the housing assembly. 
     
     
         12 . The unmanned aircraft of  claim 2 , wherein the first vibration-attenuation cushion is in a sheet form for facilitating close attachment to the weight block. 
     
     
         13 . The unmanned aircraft of  claim 2 , wherein the weight block is in a sheet form or a lump form for facilitating tight connection with the circuit board. 
     
     
         14 . The unmanned aircraft of  claim 2 , wherein the second 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 2 , wherein the circuit board is a second circuit board, and the unmanned aircraft further comprises:
 a first circuit board,   wherein the first vibration-attenuation cushion is extended between the weight block and the first circuit board.   
     
     
         17 . The unmanned aircraft of  claim 2 , wherein the circuit board is a second circuit board, and the unmanned aircraft further comprises:
 a sensing assembly, including:
 a first circuit board; 
 the second circuit board; and 
 a flexible signal line configured to connect the first circuit board to the second circuit board. 
   
     
     
         18 . The unmanned aircraft of  claim 17 , wherein the sensing assembly further comprises a signal input interface terminal and a signal output interface terminal both connected to the first circuit board in an asynchronous serial manner. 
     
     
         19 . The unmanned aircraft of  claim 18 , wherein the inner chamber opens at two ends, and the signal input interface terminal and the signal output interface terminal are disposed within the inner chamber and snapped fitted to the two ends of the inner chamber. 
     
     
         20 . The unmanned aircraft of  claim 2 , wherein the housing assembly comprises a first housing member and a second housing member configured to be snap-fitted with each other to form the inner chamber. 
     
     
         21 . The unmanned aircraft of  claim 20 , wherein the circuit board is a second circuit board, and the unmanned aircraft further comprises:
 a first circuit board configured to be fitted into an inner surface of the first housing member.