Semi-strapdown structure suitable for high-rotating-speed flying-body attitude measurement
A flying body, semi-strapdown technology, applied in the field of inertial navigation measurement, can solve problems such as the inapplicability of inertial navigation systems
Inactive Publication Date: 2011-09-07
ZHONGBEI UNIV
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[0003] In order to solve the problem that the traditional inertial navigation system is not suitable for the attitude measurement of high-speed flying objects, the present invention provides a semi-strapdown structure suitable for the attitude measurement of high-speed flying objects
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[0009] A semi-strapdown structure suitable for attitude measurement of high-speed flying objects, including axial load bearing area, radial load bearing area, inertial measurement combination and solving circuit area, mass offset area, and outer frame; The load-bearing area includes the first hemisphere 1 and the second hemisphere 3; the radial load-bearing area includes the first ball bearing 4 and the second ball bearing 10; the inertial measurement combination and solution circuit area includes the front axle 6, the inner cylinder 7, and Rear axle 8; Wherein, outer frame front end is provided with outer mounting platform 5, and outer frame rear end is provided with support 11; The first hemisphere 1, the second hemisphere 3 are installed on the outer mounting platform 5, and the first hemisphere 1 and the second hemisphere The two hemispheres 3 are in contact with each other; the outer ring of the first ball bearing 4 is installed on the outer mounting platform 5, the outer ...
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The invention relates to an inertia navigation measurement technology, in particular to a semi-strapdown structure suitable for high-rotating-speed flying-body attitude measurement, solving the problem that the traditional inertia navigation system is not suitable for high-rotating-speed flying-body attitude measurement. The semi-strapdown structure suitable for high-rotating-speed flying-body attitude measurement comprises an axial load bearing region, a radial load bearing region, an inertia measurement combination and calculation circuit region, a mass offset region and an external frame, wherein the axial load bearing region comprises a first hemisphere and a second hemisphere; the radial load bearing region comprises a first ball bearing and a second ball bearing; and the inertia measurement combination and calculation circuit region comprises a front axle, an inner cylinder and a rear axle. The invention realizes that a micro inertia measurement combination is not in strapdown with a carrier in the rotating direction and is in strapdown with the carrier in other two directions, thereby effectively solving the problem that the traditional inertia navigation system is not suitable for the high-rotating-speed flying-body attitude measurement and being suitable for the high-rotating-speed flying-body attitude measurement.
Description
technical field [0001] The invention relates to inertial navigation measurement technology, in particular to a semi-strapdown structure suitable for attitude measurement of high-speed flying objects. Background technique [0002] Inertial navigation is an autonomous navigation technology developed in the middle of the 20th century. This technology measures the angular rate and acceleration information of the carrier relative to the inertial space through the inertial measurement unit (IMU), and then uses Newton's law of motion to calculate the carrier's instantaneous attitude, velocity and Position information has the characteristics of not relying on external information, not radiating energy to the outside world, free from interference, and good concealment; traditional inertial navigation systems are divided into platform inertial navigation systems and strapdown inertial navigation systems. The platform inertial navigation system installs the inertial measurement device ...
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Inventor 刘俊李杰张文栋杨卫段晓敏石云波张晓明郭涛秦丽马喜宏鲍爱达唐军
Owner ZHONGBEI UNIV