Real-time regression detection system and method for solid rocket propellant burning surface

A solid rocket, real-time detection technology, used in measurement devices, material analysis using sonic/ultrasonic/infrasonic waves, instruments, etc., can solve problems such as large measurement errors and uneven combustion surfaces, to reduce detection errors and improve detection. The effect of precision

Pending Publication Date: 2017-09-08

UNIV OF SHANGHAI FOR SCI & TECH

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Problems solved by technology

Since the effective information used in this method is reflected waves, it is easily ...

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Method used

According to the real-time detection system and method of solid rocket propellant burning surface retreat provided by the present embodiment, since a plurality of emission transducers in the non-destructive testing unit can simultaneously transmit the amplified ultrasonic signal, with each emission transducer Multiple receiving transducers with one-to-one correspondence with each other can simultaneously receive transmission signals passing through the engine casing, so that each group of ultrasonic transducer groups forms a one-send-one-receiving mode, which can not only transmit signals through the engine casing in real time The transmission signal of the propellant can be used to learn the burning surface of the propellant in the shell, and the defect that the detection method in the p...

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Abstract

The present invention provides a solid rocket propellant combustion surface retreat real-time detection system and method, comprising: a signal generating unit for generating an ultrasonic signal as an original pulse signal; a preamplifying unit for amplifying the ultrasonic signal; The non-destructive testing unit is in contact with the casing of the solid rocket motor, and includes multiple sets of ultrasonic transducer groups arranged at certain intervals, each group of ultrasonic transducer groups has a transmitting transducer for emitting amplified ultrasonic signals and a receiving wear The receiving transducer of the transmission signal passing through the shell; the rear amplification unit, which amplifies the transmission signal; the signal conditioning unit, which converts the transmission signal into a digital signal; and the processing control unit, which processes the digital signal to obtain the propellant burning surface The displacement of the propellant and the burning rate of the propellant, and control the operation of the signal generation unit, pre-amplification unit, non-destructive testing unit, post-amplification unit and signal conditioning unit.

Application Domain

Material analysis using sonic/ultrasonic/infrasonic waves

Technology Topic

Burn rateSignal amplification +16

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Experimental program(1)

Example Embodiment

[0021] The specific embodiments of the present invention will be described below with reference to the drawings.

[0022] figure 1 It is a schematic diagram of the structure of the solid rocket propellant burning surface retreat real-time detection system in this embodiment.

[0023] Such as figure 1 As shown, the solid rocket propellant combustion surface retreat real-time detection system 100 adopts a working mode of non-contact measurement with an ultrasonic transducer. It includes a signal generation unit 11, a pre-amplification unit 12, a non-destructive testing unit 13, a post-amplification unit 14, a signal conditioning unit 15, a data acquisition unit 16, and a processing control unit 17.

[0024] The signal generating unit 11 is used to generate an ultrasonic signal as the original pulse signal; the preamplifier unit 12 is used to amplify the ultrasonic signal.

[0025] The non-destructive testing unit 13 is arranged near the solid rocket motor 20 and includes five groups of the same ultrasonic transducer group 131. These ultrasonic transducer groups 131 are arranged at a certain interval up and down near the shell 201 of the rocket engine 20, and are respectively arranged at the five positions A, B, C, D, and E in the combustion direction. Each group includes the set on the right of the shell 201. Transmitting transducer T on the side i And the receiving transducer R provided on the left side of the housing 201 i , The transmitting transducer T in each group i And receiving transducer R i Corresponding one-to-one respectively, forming a transmitting and receiving mode, that is, the transmitting transducer T i Transmit the amplified ultrasonic signal into the housing 201 and receive the transducer R i The transmission signal passing through the housing 201 is received.

[0026] In this embodiment, the propellant is propelled in the housing of the solid rocket motor 20 in the direction indicated by the triangular arrow, that is, propelled from top to bottom.

[0027] Because the ultrasonic attenuation in the air is very strong and the propagation distance is very short, in order to realize the smooth transmission of energy between the transducer and the rocket shell, it is necessary to set up a reasonable coupling method between the two so that the ultrasonic can penetrate effectively The test object achieves the purpose of effective detection. A liquid couplant is added between the measuring section and the probe to remove the air between the probe and the engine housing. This method is highly adaptable, easy to adjust the incident angle, good coupling effect, and the transducer is not easy to wear.

[0028] The post-amplification unit 14 receives the transmission signal and amplifies it; the signal conditioning unit 15 converts the transmission signal into a digital signal; the data acquisition unit 16 is used to record and save the digital signal and the processing result of the processing control unit 17; processing control The unit 17 processes the digital signal recorded by the data acquisition unit 16 to obtain the displacement of the propellant burning surface and the burning rate of the propellant.

[0029] This embodiment also provides a real-time detection method for solid rocket propellant burning surface retreat, such as figure 2 As shown, including the following steps:

[0030] Step 1. The signal generating unit 11 generates an ultrasonic signal as an original pulse signal;

[0031] Step 2: The preamplifier unit 12 amplifies the ultrasonic signal;

[0032] Step 3. Five transmitting transducers T in the NDT unit 13 i Simultaneously transmit the amplified ultrasonic signal, and each transmit transducer T i Multiple receiving transducers in one-to-one correspondence R i Receiving the transmission signal passing through the housing 201;

[0033] Step 4. The post-amplification unit 14 amplifies the transmission signal;

[0034] Step 5. The signal conditioning unit 15 converts the transmission signal into a digital signal;

[0035] Step 6. The data acquisition unit 16 collects the digital signal in real time, obtains five signal data at different positions of the engine, and transmits them to the processing control unit 17;

[0036] Step 7, the processing control unit 17 processes the digital signal to obtain the burning surface position of the propellant and the burning rate of the propellant.

[0037] The processing control unit 17 uses the sound attenuation method to obtain the propellant burning surface position according to the following formula:

[0038]

[0039] Among them, i and j represent the number of the transmitting transducer and the number of the receiving transducer, S Ti,Rj To read from i transmitting transducer to j receiving transducer T i -R j Peak matrix of transmitted wave on the path, V Ti,Rj Is T i -R j The ratio of the attenuated signal amplitude on the path to the background signal amplitude; V T Is the signal threshold.

[0040] If S Ti,Rj =0, which means the engine is at T i -R j Has begun to burn; if S Ti,Rj = 1, it means that the engine is at T i -R j The place did not burn.

[0041] In addition, the processing control unit obtains the average burning rate of the propellant according to the following formula, taking the interval between point A and point B as an example:

[0042]

[0043] Among them, L is the distance between point A and point B on the shell (in meters); △t is the single storage time used in the signal acquisition process (in s); m is when the burning surface moves to point B , The current number of digital signals recorded by the data acquisition unit, that is, the m-1th signal is not burned to point B, and the mth signal is burned to point B; n is when the burning surface moves to point A, the data acquisition unit The current number of recorded digital signals, t A Is the moment when point A burns, t A =n*△t; t B Is the moment when point B burns, t B =m*△t.

[0044] In addition, in ultrasonic testing, the properties of the propellant material and the detection range need to be considered. Enlarging the diameter of the probe can increase the transmission energy of the ultrasound probe. Under the premise of ensuring the normal operation of the probe, increasing the area of the ultrasound probe helps to increase the detection energy.

[0045] The function and effect of the embodiment

[0046] According to the system and method for real-time detection of solid rocket propellant combustion surface retreat provided by this embodiment, since multiple transmitter transducers in the non-destructive testing unit can simultaneously transmit amplified ultrasonic signals, which are separate from each transmitter transducer. One corresponding multiple receiving transducers can simultaneously receive the transmission signals passing through the engine casing, so that each group of ultrasonic transducer groups form a transmission and reception mode, which can not only be based on the transmission signal through the engine casing in real time The combustion surface of the propellant in the shell is learned, and the defect that the detection method in the prior art is easily affected by the unevenness of the combustion surface is overcome, thereby reducing the detection error and improving the detection accuracy.

[0047] In the above embodiment, there are five sets of ultrasonic transducers arranged outside the shell of the solid rocket motor, which are used as the solid rocket propellant fuel surface retreat real-time detection system of the present invention, and are the ultrasonic transducers as a component of the non-destructive testing unit The group is not limited to five groups, and the number of ultrasonic transducer groups can be set according to the actual height of the engine housing.

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Classification and recommendation of technical efficacy words

Reduce detection error
Improve detection accuracy

Real-time regression detection system and method for solid rocket propellant burning surface

AI-Extracted Technical Summary

Problems solved by technology

Method used

Abstract

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Example Embodiment

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Description & Claims & Application Information

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