Strapdown optical seeker decoupling method considering measurement delay

An optical seeker and strapdown technology, applied in the field of aircraft, can solve problems such as guidance information interference, and achieve the effect of reducing the impact

Active Publication Date: 2020-03-24
HARBIN INST OF TECH
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Problems solved by technology

[0004] The present invention aims to solve the problem that the guidance information interferes greatly under the condition that the time delay of measurement information of the strapdown optical seeker is not the same as that of the aircraft attitude sensor. Seeker decoupling method

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  • Strapdown optical seeker decoupling method considering measurement delay
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  • Strapdown optical seeker decoupling method considering measurement delay

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specific Embodiment approach 1

[0039] Specific implementation mode one: refer to figure 1 This embodiment is specifically described. A strapdown optical seeker decoupling method considering measurement delay described in this embodiment includes the following steps:

[0040] Step 1: Simulate and generate a set of strapdown optical seeker input signals with a pulse width of nanoseconds through the signal generator, and connect the signal output terminal of the signal generator to the signal input terminal of the strapdown optical seeker signal processing board , and then connect the signal output terminal of the signal generator and the signal output terminal of the strapdown optical seeker to the oscilloscope; input the analog input signal into the strapdown optical seeker, and record the signal input in the oscilloscope Moment T dyt_in , collect the output signal of the strapdown optical seeker, and record the signal output time T in the oscilloscope dyt_out , the T dyt_in and T dyt_out Doing the diffe...

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Abstract

The invention discloses a strapdown optical seeker decoupling method considering measurement delay, and relates to the field of aircrafts. The objective of the invention is to solve the problem of large guidance information interference under the condition that strapdown optical seeker measurement information time delay is different from aircraft attitude sensor measurement information time delayat present. The method comprises: measuring the delay time of signal output of the strapdown optical seeker; measuring the output delay time of the angular rate gyroscope through an angular vibrationtest of the angular rate gyroscope; further obtaining the difference between the delay time of the output information of the strapdown optical seeker and the delay time of the output information of the angular rate gyroscope; discretizing the sampling period according to the angular rate gyroscope; determining the beat number adjusted by the attitude angle information resolved by the angular rategyroscope, and solving to obtain the sight angle of the connection line of the aircraft and the target for eliminating the measurement delay by utilizing the information output by the strapdown optical seeker and the attitude angle information resolved by the angular rate gyroscope and adjusted by the time beat number, so as to complete decoupling of the strapdown optical seeker.

Description

technical field [0001] The invention belongs to the field of aircraft, and in particular relates to the measurement of strapdown optical seeker information during aircraft flight. Background technique [0002] During the flight of the aircraft, there is a problem of measurement delay in the measurement information of the strapdown optical seeker; at the same time, there is also a measurement delay in the measurement information of the aircraft attitude sensor. The state of different measurement delays of the two information will increase the interference to the formation of aircraft control commands. , thus affecting the flight trajectory of the aircraft, causing the aircraft to fail to complete the flight mission according to the theoretically set trajectory, and in severe cases, it will cause the failure of the flight test. [0003] In order to reduce the impact of the difference in measurement delay of the two channels of information on the flight trajectory of the aircra...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00
CPCG01C25/005
Inventor 任韦魏英杰夏维学王金强张成举李聪慧
Owner HARBIN INST OF TECH
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