Installation orientation adjustment method of aircraft inertial navigation device based on gyro north finder

A technology of inertial navigation and north finder, which is applied in the field of adjusting the installation orientation of aircraft inertial navigation devices. It can solve the problems of difficulty in ensuring the adjustment accuracy, easy deformation of the suspension plate, and inconvenient operation, so as to achieve easy operation and improve adjustment accuracy. , Improve the effect of adjustment efficiency

Active Publication Date: 2017-11-10
大连长丰实业总公司
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Problems solved by technology

The traditional azimuth adjustment method is to adopt the technical solution of L-shaped hanging plate (that is, the hard connection bracket). Th

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  • Installation orientation adjustment method of aircraft inertial navigation device based on gyro north finder
  • Installation orientation adjustment method of aircraft inertial navigation device based on gyro north finder
  • Installation orientation adjustment method of aircraft inertial navigation device based on gyro north finder

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Embodiment Construction

[0030] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0031] The invention provides a device for adjusting the installation orientation of an aircraft inertial navigation device based on a gyro north finder. The optical measurement method is combined with the inertial measurement method. The coordinate system is parallel, measure the longitudinal axis direction of the aircraft, and use the mechanical interface of the inertial navigation to connect the installation environment of the inertial navigation, and directly measure and adjust the installation interface of the inertial navigation, so that the inertial navigation coordinate system is parallel to the aircraft coordinate system, so that It ensures that the inertial navigation coordinate system on the aircraft is parallel to the aircraft coordinate system, and achieves the purpose of adjusting the orientation of the inertial navigation system installed on ...

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Abstract

The invention discloses a method for adjusting the installation orientation of an aircraft inertial navigation device based on a gyro north finder. The invention can effectively realize the adjustment of the installation orientation of the inertial guide on the aircraft, and has the advantages of simple and convenient use, good reliability, high adjustment accuracy and good universality. The present invention utilizes the designed adjustment device to adjust the installation orientation of the aircraft inertial navigation system. The adjustment device includes a frame and an optical axis intercepting device and an adjustment platform installed on the frame, wherein the adjustment platform is connected by The flat plate is composed of a sight, a vertical collimator, a north finder and a spirit level installed on the connecting plate; the present invention measures the vertical axis direction of the aircraft by adopting a measurement method combining optics and inertia, and adopts the mechanical function of the inertial navigation itself. The interface is connected to the installation environment of the inertial navigation system itself, and the direct measurement and adjustment of the inertial navigation installation interface can achieve high adjustment accuracy, and the operation is simple, which can greatly improve the adjustment efficiency.

Description

technical field [0001] The invention relates to the technical field of inertial measurement, in particular to a method for adjusting the installation orientation of an aircraft inertial navigation device based on a gyro north finder. Background technique [0002] The inertial navigation device (inertial navigation system for short) is installed on the aircraft. Due to long-term body deformation or other reasons, the installation orientation of the inertial navigation system drifts, which affects the flight accuracy and target hitting accuracy of the aircraft. Therefore, regular orientation adjustments are required. The so-called azimuth adjustment is to adjust the inertial navigation azimuth and the aircraft azimuth (the direction of the longitudinal axis of the aircraft) to be consistent. The traditional azimuth adjustment method is the technical solution of using an L-shaped hanging plate (that is, a hard connection bracket). The disadvantages are that the hanging plate is...

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Application Information

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IPC IPC(8): G01C25/00
Inventor 杨宝华王芳郑晔孟海英杨峻岭倪雷
Owner 大连长丰实业总公司
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