Inertial navigation resolving method suitable for steady-state navigation and capable of saving two-axis strapdown gyroscope

A gyroscope and solution technology, applied in the field of inertial navigation solution, can solve the problem of unusable magnetic compass, and achieve the effect of saving cost and reducing volume

Active Publication Date: 2020-04-07
中国船舶重工集团公司第七0五研究所
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Problems solved by technology

However, the magnetic compass is extremely vulnerable to the magnetic interference of the use environment, which is also a very significant

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  • Inertial navigation resolving method suitable for steady-state navigation and capable of saving two-axis strapdown gyroscope
  • Inertial navigation resolving method suitable for steady-state navigation and capable of saving two-axis strapdown gyroscope
  • Inertial navigation resolving method suitable for steady-state navigation and capable of saving two-axis strapdown gyroscope

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Embodiment Construction

[0027] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0028] In the present invention, the one-time target mine adopts the scheme of magnetic compass + strapdown technology. Considering the volume cost, an inertial navigation solution technology that can save two-axis strapdown gyro has been developed. The invention is an unconventional strapdown inertial navigation solution method, which is suitable for the navigation parameter extraction technology of the aircraft whose volume and weight are seriously limited, and the aircraft has no large pitch roll, violent maneuvering motion, and steady-state navigation.

[0029] The working principle of the strapdown inertial navigation system is to use three single-axis strapdown gyroscopes (or two two-axis, or one three-axis gyroscope) and three accelerometers to form an inertial measurement unit (IMU). In the strapdown inertial navigation algorithm, the rotation m...

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Abstract

The invention provides an inertial navigation resolving method suitable for steady-state navigation and capable of saving a two-axis strapdown gyroscope. According to the invention, two horizontal axial gyroscopes are removed; a single-axis gyroscope of an azimuth channel is reserved, an accelerometer in a magnetic compass is used for extracting the difference between a pitching horizontal attitude angle and a rolling horizontal attitude angle in the non-maneuvering navigation process to form an angle increment, the angle increment and the single-axis gyroscope jointly form complete description of the moving work of the aircraft along three axial spaces, and updating of a mathematical platform is achieved. Due to the fact that strapdown inertial navigation calculation of the single-axis gyroscope magnetizing compass can be achieved, a two-axis strapdown gyroscope is omitted on the basis of traditional strapdown inertial navigation configuration, the size can be reduced, and cost is saved.

Description

technical field [0001] The invention relates to the field of inertial navigation calculation, in particular to a gyroscope inertial navigation calculation method. Background technique [0002] At present, the strapdown inertial navigation technology is the mainstream technology to realize the attitude extraction of the aircraft. The disposable target mine itself has a diameter of φ110 and requires 10 hours of sailing. Acoustic simulation and magnetic simulation should be completed in the last half hour of sailing, and position information of key waypoints should also be provided. The error divergence of pure strapdown inertial navigation technology over time is its basic characteristic, and relying on pure inertial navigation cannot meet the use requirements at all. [0003] In order to solve the problem of strapdown inertial navigation error divergence, countless technical measures have been taken by different application objects. In summary, it starts with improving the a...

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Application Information

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IPC IPC(8): G01C21/16
CPCG01C21/16
Inventor 国琳娜高卓程树明魏鹤怡
Owner 中国船舶重工集团公司第七0五研究所
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