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Passive sound-based missile terminal velocity measurement system and measurement method

A technology of terminal speed and measurement system, applied in the direction of ammunition, ammunition test, weapon accessories, etc., can solve the problem of not being able to carry out all-weather real-time, and achieve the effect of accurate measurement

Active Publication Date: 2014-04-16
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention aims to solve the problem that the method of measuring missile terminal velocity based on vision and radar cannot be carried out in real time all-weather, and provides a missile terminal velocity measurement system and measurement method based on passive sound

Method used

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  • Passive sound-based missile terminal velocity measurement system and measurement method
  • Passive sound-based missile terminal velocity measurement system and measurement method
  • Passive sound-based missile terminal velocity measurement system and measurement method

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specific Embodiment approach 1

[0041] Specific implementation mode one: the following combination Figure 1 to Figure 4 Describe this embodiment, the passive sound-based missile terminal speed measurement system described in this embodiment includes a microphone system 1, a stepper motor 2, an AD acquisition system 3, an FPGA module 4, a DSP module 5, a digital camera 6, a wireless transmission System 7, first FIFO data buffer 8, second FIFO data buffer 9, temperature sensor 10-1, wind speed sensor 10-2, wind direction sensor 10-3 and digital camera interface module 11,

[0042] Digital camera 6 is used for collecting the image signal of tested guided missile in real time, and the grayscale image acquisition control signal output and input end of digital camera 6 is connected to the image acquisition control signal input and output end of FPGA module 4 by digital camera interface module 11,

[0043] The shock wave acquisition control signal input end of the FPGA module 4 is connected to the digital signal o...

specific Embodiment approach 2

[0052] Specific implementation mode two: the following combination Figure 1 to Figure 4 Describe this embodiment, this embodiment is the further explanation to embodiment one, described FPGA module 4 comprises microphone acquisition control module 4-1, digital camera control and data transmission module 4-2, temperature sensor acquisition control module 4-3 , Wind speed sensor acquisition control module 4-4, wind direction sensor acquisition control module 4-5, FIFO chip selection and storage interface module 4-6, DSP communication control module 4-7, shock wave signal adaptive filter processing algorithm module 4-8 , shock wave signal blind separation algorithm module 4-9, controllable beamforming positioning algorithm module 4-10, stepper motor control module 4-11 and SRAM interface module unit 4-12,

[0053] The image acquisition control signal input and output end of FPGA module 4 is the image acquisition control signal input and output end of digital camera control and d...

specific Embodiment approach 3

[0069] Specific implementation mode three: the following combination Figure 1 to Figure 2 Describe this embodiment, this embodiment is a further description of Embodiment 2, the SRAM interface module unit 4-12 includes six SRAM interface modules, the microphone system 1 includes six sound sensor branches, each sound sensor The output signal of the branch is correspondingly transmitted to a SRAM interface module through the AD acquisition system 3 and the microphone acquisition control module 4-1.

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Abstract

The invention discloses a passive sound-based missile terminal velocity measurement system and a passive sound-based missile terminal velocity measurement method, belongs to the technical field of sound signal processing and measurement, and solves the problem that a method for measuring the terminal velocity of a missile based on vision and radar cannot be implemented in real time in all weathers. The measurement system comprises a microphone system, a stepping motor, an analogue-to-digital (AD) acquisition system, a field programmable gate array (FPGA) module, a digital signal processing (DSP) module, a digital camera, a wireless transmission system, a first First-In First-Out (FIFO) data buffer, a second First-In First-Out (FIFO) data buffer, a temperature sensor, a wind velocity sensor, a wind transducer and a digital camera interface module. According to the measurement method, the sensor closest to the azimuth orientation is adjusted by rotating the stepping motor, so that the sensor is parallel to the running direction of the missile; the velocity of the missile when the missile runs closest to a target is measured by using two adjusted sensors; and the accurate velocity of the missile when the missile runs to a target attachment is obtained by delay estimation and velocimetry algorithm in the DSP. The system and the method are applicable to measuring the terminal velocity of the missile.

Description

technical field [0001] The invention relates to a missile terminal speed measurement system and a measurement method based on passive sound, belonging to the technical field of sound signal processing and measurement. Background technique [0002] With the rapid development of military technology in various countries in the world, various new weapon systems have emerged. Among the various methods for evaluating the pros and cons of weapon systems, the measurement of the amount of misses has become one of the hot research topics in various countries. Whether it is the development test of a new weapon system or the combat training of a finalized weapon system equipped with troops, it is necessary to rely on actual combat or shooting to test the performance of the weapon system. The size of the missile is the most important measure in the process of firing the missile, and it is one of the main requirements to judge whether the weapon system meets the design indicators. The k...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F42B35/02
Inventor 叶东路敬祎陈刚郭玉波
Owner HARBIN INST OF TECH