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Sensor tilting inertia measurement unit structure

An inertial measurement component and sensor technology, applied in the field of inertial navigation, can solve the problems of geometric center offset, inertial measurement component size, space and weight exceeding usage requirements, and space waste utilization and other problems

Active Publication Date: 2012-01-18
FLIGHT AUTOMATIC CONTROL RES INST
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Problems solved by technology

Such a design method will inevitably cause the center of mass of the inertial measurement unit and the geometric center of the inertial measurement unit to seriously shift; at least 40% of the space of the inertial measurement unit will be wasted or the utilization rate is not high, so it is easy to cause the size of the inertial measurement unit , space and weight exceed the requirements for use; a sensor with the same dynamic range as the carrier must be selected, which severely limits the selection range of the sensor

Method used

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  • Sensor tilting inertia measurement unit structure
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  • Sensor tilting inertia measurement unit structure

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Embodiment

[0049] The present invention is described in detail by taking the design of an inertial measurement component for a strapdown inertial navigation component of a missile-borne strapdown guidance system as an example. The maximum external dimension of the inertial measurement component is required to be Φ150mm×60mm; the maximum angular velocity along the missile roll axis is 1000° / s; the maximum acceleration rate along the missile roll axis is 15g; the maximum angular velocity of the other axes is 300° / s, The maximum acceleration in other axial directions is 8g; suppose a gyro is selected, its maximum external dimension is Φ68mm×20mm, and its maximum dynamic range is 600° / s; an accelerometer is selected, its maximum external dimension is 36mm×18mm×12mm, and its maximum dynamic range is 10g.

[0050] (1) The structure of the bracket

[0051] The mounting surface of the bracket is the bottom surface of the bracket, and the normal line of the mounting surface of the bracket coinci...

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Abstract

The invention, belonging to the technical field of inertial navigation, relates to a novel structure design method of an inertia measurement unit (IMU) of a strapdown inertial navigation system. The invention is characterized in that: three gyros and three accelerometers are arranged on an IMU support equlangularly symmetrically inclinedly, by the installing surface of the support, the permanent connection of the IMU and the strapdown inertial navigation system is realized; the sensitive shafts of the three gyros and three accelerometers no longer coincide with the coordinate system of the inertial navigation system or the coordinate system of the carrier. According to the invention, the dimension, volume and weight of the IMU are signally reduced; the problem of centroid shift of the IMUin traditional inertial navigation system is solved. By enlarging the measurement range of the gyros and accelerometers, the invention is very suitable for missiles or the strapdown inertial navigation system which has a high demand of dimension, weight and dynamic range. The invention can improve the space utilization rate of IMU, improve the problem of centroid shift of the IMU, and signally reduce the structure dimension, and weight of the IMU.

Description

technical field [0001] The invention belongs to the technical field of inertial navigation, and relates to an inertial measurement assembly structure with a sensor inclined. Background technique [0002] The inertial measurement unit (IMU) of the strapdown inertial navigation system includes three gyroscopes and three accelerometers, which are used to sense and measure the angular motion and linear motion of the carrier. The inertial navigation system solves the output signals of the gyroscopes and accelerometers , to obtain navigation signals such as the attitude, velocity, and position of the carrier. In many applications, such as the inertial navigation system of missiles, helicopters or guided bombs, the requirements for the size, weight and volume of the inertial measurement components are very stringent, and some missiles have very high dynamic range, and the range needs to be selected to be the same as the dynamic range of the carrier sensor. [0003] If the structu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/18
Inventor 陈江良陈璞
Owner FLIGHT AUTOMATIC CONTROL RES INST
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