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A implicit type structure mini inertia measurement unit

An inertial measurement unit and implicit structure technology, applied in directions such as navigation through speed/acceleration measurement, can solve the problems of low processing cost, large installation error, and low cost, and achieve low processing cost, easy integration, and high precision Effect

Inactive Publication Date: 2007-09-19
BEIHANG UNIV
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

The structural frame machined by the former method can achieve higher precision, but the installation process is more, the introduction of installation error is large, and the volume is larger, and the processing cost is high; the latter method is smaller in size and lower processing cost , but the installation accuracy is very poor, and the perpendicularity between the three axes cannot be guaranteed
In view of the above reasons, the existing IMU cannot take into account the requirements of small size, light weight, high precision and low cost of the GNC system of micro aircraft

Method used

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  • A implicit type structure mini inertia measurement unit
  • A implicit type structure mini inertia measurement unit
  • A implicit type structure mini inertia measurement unit

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Embodiment Construction

[0019] For the case of using a dual-axis accelerometer and a single-axis gyroscope, the ADXL320 type accelerometer (dual axis) and the ADXRS300 type gyroscope (single axis) are used as examples for illustration. Firstly, according to the size of the ADXL320 accelerometer and ADXRS300 gyroscope used in the GNC system of the micro-aircraft, the circuit schematic diagram and installation requirements, the size of the cube base is determined to be 10mm×10mm×10mm. The use density is 3.6g / cm 3 Aluminum nitride synthetic ceramics or silicon carbide synthetic ceramics materials are molded to form a cube base of the required size (this embodiment adopts aluminum nitride synthetic ceramics), and the shape is as shown in Figure 1 (or one of the corners or two corners of the cube are cut off. corners or three corners or four corners or five corners or six corners). After the cube base is formed, the surface of the base is ground with diamond micropowder, so that the surface parallelism i...

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Abstract

The present invention provides a miniature inertia measuring unit with an implicit structure that processing a cube base by adopting synthetical ceramic material according to a certain requirement of verticality, planeness and degree of smoothness. The circuit is plated on the surface of the base and a welding plate is attached to the surface of the base by using the character that the surface made of synthetical ceramic material with a certain degree of smoothness can be plated with a circuit according to the packaging of the accelerometer and the top, the elementary diagram of circuit and the installation requirement. The accelerometer and the top are plated on the two faces that are vertical with each other of the base to assure that the accelerometer and the top with there sensitive directions are vertical with each other. The edge of the bottom surface of the cube base is attached with a welded corner plate to make that the circuit on the bottom surface of the base can not only be connected to the lateral circuit, but also can be plated on the GNC system board of a miniature aerocraft. The base is used as a circuit board of the IMU system and as a supporting structure of the accelerometer and the top. The miniature IMU in the present invention which haves the characteristics of small, light, high-precision and low-cost can be applied in the fields of miniature aerocraft, a miniature robot, etc.

Description

technical field [0001] The invention relates to a miniature inertial measurement unit (IMU), in particular to a miniature IMU based on MEMS technology and used for a miniature aircraft navigation, guidance and control (GNC) system. It is suitable for occasions that have high requirements for IMU volume, weight, accuracy and cost. Background technique [0002] The GNC system of micro-aircraft needs its key component IMU to meet the requirements of small size, light weight, high precision and low cost at the same time. The miniaturization of the IMU has become the key to restricting the miniaturization of the GNC system. [0003] In order to calculate the position, velocity, attitude and other motion parameters of the micro-aircraft and control the flight, the navigation, guidance and control (GNC) system of the micro-aircraft needs an IMU to measure the three orthogonal directions (X, Y, , Z) acceleration, angular velocity and other parameters. In order to meet the require...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/18G01C21/10
Inventor 房建成张霄盛蔚李建利孙宏伟曹娟娟
Owner BEIHANG UNIV
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