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Horizontal aiming result compensation method under horizontal state

A technology of horizontal aiming and compensation method, which is applied in the direction of measuring devices, instruments, surveying and navigation, etc. It can solve the problems of shortening the launch preparation time and the inability to obtain the aiming angle of the secondary aircraft, so as to shorten the launch preparation time, simple design, and principle clear effect

Active Publication Date: 2018-08-28
BEIJING INST OF ELECTRONICS SYST ENG
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AI Technical Summary

Problems solved by technology

However, in order to better meet the requirements of actual combat, the improved two-stage aircraft shortened the launch preparation time. Before launch, only the aiming process of the first-stage aircraft in the horizontal state was arranged. Aiming alone, so can't get secondary aircraft aiming angle

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  • Horizontal aiming result compensation method under horizontal state
  • Horizontal aiming result compensation method under horizontal state
  • Horizontal aiming result compensation method under horizontal state

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Embodiment Construction

[0031] In order to illustrate the present invention more clearly, the present invention will be further described below in conjunction with preferred embodiments and accompanying drawings. Similar parts in the figures are denoted by the same reference numerals. It should be understood by those skilled in the art that the content specifically described below is illustrative rather than restrictive, and should not limit the protection scope of the present invention with this.

[0032] like figure 1 As shown, a horizontal aiming result compensation method under the horizontal state is set based on the above-mentioned horizontal aiming structure compensation system in the horizontal state, including the following steps:

[0033] S1. Obtain the horizontal aiming angle α of the first-stage aircraft in the horizontal state through the collimator measurement D ';

[0034] S2. Determine the installation error angle Δζ z ;

[0035] S3, through the installation error Δζ z and the h...

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Abstract

The invention discloses a horizontal aiming result compensation method under a horizontal state. The method comprises the following steps of S1, measuring to obtain a horizontal aiming angle alphaD'ofa first-level aircraft in the horizontal state by using a collimator; S2, determining an installation error angle delta-zetaz; S3, determining a horizontal aiming angle of a second-level aircraft according to the installation error angle delta-zetaz and the horizontal aiming angle alphaD'of the first-level aircraft. The method can calculate the installation error angles of the first-level aircraft and the second-level aircraft in advance by using an inertial measurement unit and quickly determine the horizontal aiming angle of the second-level aircraft on the basis of measuring to obtain thehorizontal aiming angle of the first-level aircraft before the launch.

Description

technical field [0001] The invention relates to the field of compensation for horizontal aiming results, in particular to a compensation method for horizontal aiming results in a horizontal state. Background technique [0002] Both the primary aircraft and the secondary inertial measurement unit (hereinafter referred to as inertial group) of traditional two-stage aircraft are equipped with optical rectangular prisms, and the aiming process is performed before launch, and the aiming angles of the two are sequentially measured by the collimator, and then the first-level Initial baseline for aircraft and secondary aircraft. However, in order to better meet the requirements of actual combat, the improved two-stage aircraft shortened the launch preparation time. Before launch, only the aiming process of the first-stage aircraft in the horizontal state was arranged. Aiming alone, so the aiming angle of the secondary aircraft cannot be obtained. Contents of the invention [000...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00G01C1/00
CPCG01C1/00G01C25/00
Inventor 张乃文夏辉梁彤董霓鄢镕易侯婧
Owner BEIJING INST OF ELECTRONICS SYST ENG
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