A method for measuring the deflection angle of strapdown inertial navigation and alignment prism installation
A technology of strapdown inertial navigation and measurement method, which is applied to measurement devices, instruments, etc., to achieve the effects of simple method, simple implementation and high measurement accuracy
Active Publication Date: 2020-06-05
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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In the actual installation process, it is difficult to achieve absolute coincidence between the strapdown inertial navigation coordinate system and the alignment prism coordinate system, and there will be a certain installation deflection angle. If the installation deflection angle is not accurately measured and soft compensation is performed, the aircraft will have a fixed alignment In this context, a set of technology is proposed to use the normal vector of the inertial navigation alignment prism reflection surface to be equal to the laser alignment vector of the autocollimation theodolite, and calculate the alignment prism and inertial navigation installation deviation between
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[0039] The present invention is described in more detail below by means of examples, but the following examples are only illustrative, and the protection scope of the present invention is not limited by the examples.
[0040] like figure 1 , figure 2 , image 3 Shown: a kind of hardware facility of strapdown inertial navigation and alignment prism installation deflection angle measurement comprises: strapdown inertial navigation (1), alignment prism (2), two-axis turntable (3), autocollimation theodolite (4 ) and the main computer, monitor and keyboard. The measurement method is:
[0041] (1) Fix the strapdown inertial navigation system (1) and the alignment prism (2) on the two-axis turntable (3), and power on the measurement system to start the measurement work.
[0042] (2) The main control computer sends instructions to the dual-axis turntable (3) Rotate the outer frame vertically and the inner frame to align the prism (2) and the autocollimation theodolite (4) at col...
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The invention provides a method for measuring an installation error coefficient of a strap-down inertial navigation system and an alignment prism. Hardware facilities comprise a two-axis turntable, a strap-down inertial navigation system, an alignment prism, an autocollimation theodolite, a main control computer, a display, a keyboard and the like. The method comprises the following steps: changing collimation positions of the strap-down inertial navigation table, the alignment prism and the autocollimation theodolite by rotating the two-axis turntable twice, recording CCD (Charge Coupled Device) misalignment angle reading and horizontal plate reading beta of the autocollimation theodolite, inside and outside frame coded disc reading alpha of the two-axis turntable and strap-down inertial navigation output parameters twice by the main control computer, and resolving the installation error coefficient between the alignment prism and the inertial navigation system after an initial alignment manner of the alignment prism to the strap-down inertial navigation system is changed into a vertical installation manner.
Description
technical field [0001] The invention belongs to the technical field of initial alignment detection and compensation for a strapdown inertial navigation system, and in particular relates to a method for measuring a strapdown inertial navigation and an alignment prism installation deflection angle. Background technique [0002] At present, the initial alignment and aiming prism of the SINS is usually installed horizontally, but in order to realize the precise alignment of the aircraft’s horizontal initial orientation and launch immediately after erecting, it is necessary to change the initial alignment and aiming prism of the SINS to be installed vertically, so that The change in the installation angle relationship between the initial alignment prism and the SINS will inevitably lead to changes in the measurement method for the installation deviation angle between the initial alignment prism coordinate system and the SINS coordinate system. In the actual installation process, ...
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IPC IPC(8): G01C25/00
CPCG01C25/005
Inventor 李春权周海王勇
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD