CN204064620U - A kind of satellite fairing vibration and noise reducing simple experimental device - Google Patents
A kind of satellite fairing vibration and noise reducing simple experimental device Download PDFInfo
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- CN204064620U CN204064620U CN201420316354.2U CN201420316354U CN204064620U CN 204064620 U CN204064620 U CN 204064620U CN 201420316354 U CN201420316354 U CN 201420316354U CN 204064620 U CN204064620 U CN 204064620U
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- radome fairing
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Abstract
A kind of satellite fairing vibration and noise reducing simple experimental device, comprise simulation radome fairing, acoustically-driven circuit, power exciting circuit and data acquisition circuit, described acoustically-driven circuit comprises the computer, binary channels Graphic equalizer, power amplifier I, the audio amplifier that connect successively, described power exciting circuit comprises the computer, power amplifier II and the vibrator that connect successively, described data acquisition circuit comprise data acquisition front and be arranged on simulation radome fairing on microphone and acceleration transducer; Described acoustically-driven circuit, power exciting circuit are to the conveying acoustically-driven of simulation radome fairing and power pumping signal, signal is fed back to computer by data acquisition front by the sensor on simulation radome fairing to carry out data analysis and compares, thus obtains simulating the acoustic characteristic of laying acoustical material in radome fairing.This experimental provision equipment investment is few, less demanding to experimental situation, and device security is reliable, simple to operate, repeatable strong, greatly can shorten the production cycle of radome fairing noise reduction process, save human and material resources cost.
Description
Technical field
The utility model relates to a kind of vibration and noise reducing experimental provision, particularly relates to satellite fairing vibration and noise reducing simple experimental device.
Background technology
Satellite is in launch and flight process, outside vibroacoustic environment is extremely severe, the wherein mainly fluctuation pressure of air and the jet noise of rocket engine, in order to protect satellite and other useful load, adopt radome fairing by satellite and other useful load and external environs, can effectively prevent the exact instrument such as satellite by aerodynamic force, Aerodynamic Heating and sound such as to shake at the impact of hostile environment, but the noise reduction measure that current radome fairing is taked is more limited, generally, inside and outside radome fairing, sound pressure level only differs about 10dB, and the effect that satellite quality 40% plays is only used to enable satellite to bear great vibrations in carrier rocket launch and flight process and noise, according to estimation, the cost that one kilogram of object launched by carrier rocket reaches 2 ten thousand to 4 ten thousand dollars, if the sound pressure level in satellite payload cabin therefore can be reduced, the probability of satellite failure can not only be reduced, and the quality of satellite can be reduced, this is for the design of satellite and rocket, manufacture and launch and all there is huge economic implications.
Have with the immediate prior art of present patent application: 1. Acoustic testing of the Cassini spacecraft and Titan IV payload fairing./Part 1, Introduction and test configuration(NASA) 2. transport noise reduction comprehensive test study in seven fuselage compartments (" Research for Structural Strength "), in document 1, the noise testing of radome fairing internal vibration is carried out to god of unusual strength IV payload fairing (inside contains Cassini airship) master mould, relevant vibration and noise reducing experiment has been carried out by laying acoustics blanket inside radome fairing, and propose corresponding rational noise reduction schemes, but the method is only only applicable to the structural designs such as radome fairing, after processing, total need be assembled, total complexity is huge, make there is more special requirement (general reverberation chamber may be unable to hold total) to the reverberation chamber used in test, external drive (sound and vibration) in test also can increase the input of experimental facilities due to the huge of structure, the master pattern of 1:1 too increases the input of acoustical material equally, the research of the acoustic characteristic of the dependency structure adopting the fuselage acoustic experiment platform built voluntarily to carry out in document 2, but what this test unit adopted is real fuselage, be difficult to obtain to general R&D institution, the boundary condition of fuselage and radome fairing in addition, anatomical connectivity form etc. is all different.
Summary of the invention
The technical problems to be solved in the utility model is: in order to the deficiency overcome existing for above-mentioned prior art utilizes the brief test platform built voluntarily, the truly vibration noise environment of complexity of maximum simulation radome fairing, only consider the cylindrical section that vibration noise is more serious, simplify the complexity studied a question, by laying different acoustical materials in cylindrical section inside, study its effect of vibration and noise reduction, for the acoustic treatment of the vibration and noise reducing of master mould provides foundation, also for simulation optimization provides Experimental comparison and checking.
The technical scheme that the utility model is taked is: a kind of satellite fairing vibration and noise reducing simple experimental device, comprise simulation radome fairing, acoustically-driven circuit, power exciting circuit and data acquisition circuit, described simulation radome fairing comprises the cover at cylindrical shell and two ends, described cylindrical shell is rolled by aluminium sheet and forms, described cover adopts plank to make, and is processed with and embeds with cylindrical shell the groove assembled inside cover; Described acoustically-driven circuit comprises the computer, binary channels Graphic equalizer, power amplifier I, the audio amplifier that connect successively, and described power exciting circuit comprises the computer, power amplifier II and the vibrator that connect successively; Described data acquisition circuit comprises data acquisition front and microphone and acceleration transducer, described microphone is arranged on the medial and lateral of simulation radome fairing by support symmetry, the distance of microphone and cylindrical shell is generally 8 ~ 12cm, described acceleration transducer symmetry is arranged on simulation radome fairing and is positioned on the barrel of microphone upper and lower, one end of described data acquisition front is connected with computer by computer USB interface, and microphone and acceleration transducer are connected to data acquisition front respective signal port each via cable; Barrel between the acceleration transducer of described upper and lower part establishes point of excitation A, and described point of excitation A connects the output terminal of vibrator; Described audio amplifier is arranged on simulation 1m place, radome fairing dead ahead.
Its further technical scheme is: described cylindrical shell and cover are rabbeted position and adopted butyl rubber or greasy filth to seal.
Its further technical scheme be: described binary channels Graphic equalizer adopts 2 × 31 sections of binary channels Graphic equalizers, select the lifting of 12dB/6dB wherein and evanescent mode by switch transition, realize sound signal micro-/quick adjustment of coarse adjustment: switch is pressed as 6dB, and switch is upspring as 12db.
Described audio amplifier adopts 2 12 cun, has the full-range cabinet of two divided-frequency, and comprise 12 cun of bass units and 44 titanium high pitchs, its broadband is 50-20KHz, and maximum sound pressure level is 126dB, and 2 audio amplifiers are respectively to tilted 10o ~ 25o.
Owing to adopting technique scheme, a kind of satellite fairing vibration and noise reducing simple experimental device of the utility model has following beneficial effect:
1. the method that the utility model have employed theory calculate, simulation and experiment combines, theory calculate is for simply to test and emulation provides theoretical foundation and reference, experiment is for emulating the checking supplied a model with acoustics treatment effect, emulate as experimental program provides reference, make the simulation optimization of acoustical material and theory calculate become simple, thus substantially reduce the production cycle of radome fairing noise reduction process; (the utility model, by laying the acoustical material of the known acoustical cotton of parameters,acoustic and parameters,acoustic the unknown respectively, being tested by experiment, theory calculate, just just can be obtained its corresponding parameters,acoustic by carrying out contrast to given data); Simultaneously can for providing guidance by the similar acoustic characteristic reducing model of research structure, vibration and noise reducing;
2. the utility model is based on dimensional analysis and the principle of similitude, and only consider the cylindrical section that vibration noise is more serious, that sets up satellite fairing reduces model, just corresponding acoustic analysis can be carried out at the product design initial stage, compare master mould less, like this in the acoustic treatment of carrying out early stage, buying and the use cost of acoustical material can be reduced significantly;
3. a kind of satellite fairing vibration and noise reducing simple experimental device equipment investment of the utility model is few, less demanding to experimental situation, can test in open open air or semianechoic room, device security is reliable, simple to operate, repeatable strong, experiment effect is obvious, saves human and material resources cost.
Be further described below in conjunction with the technical characteristic of drawings and Examples to a kind of satellite fairing vibration and noise reducing simple experimental device of the utility model.
Accompanying drawing explanation
Fig. 1: a kind of satellite fairing vibration and noise reducing simple experimental device theory diagram of the utility model;
Fig. 2: a kind of satellite fairing vibration and noise reducing simple experimental device circuit connection diagram of the utility model;
Fig. 3: simulation radome fairing tube structure schematic diagram:
Fig. 4: simulation radome fairing Cap structure for box-like container schematic diagram.
In figure: 100-computer, 101-binary channels Graphic equalizer, 102-power amplifier I, 103-audio amplifier, 104-power amplifier II, 105-vibrator, 106-data acquisition front, 2-simulation radome fairing, 21-cover, 211-groove, 22-cylindrical shell, 3-microphone, 4-acceleration transducer, D-recess width.
Embodiment
A kind of satellite fairing vibration and noise reducing simple experimental device, comprise simulation radome fairing, acoustically-driven circuit, power exciting circuit and data acquisition circuit, described simulation radome fairing 2 comprises the cover 21 at cylindrical shell 22 and two ends, described cylindrical shell is rolled by aluminium sheet and forms, described cover adopts plank to make, and is processed with the groove 211 embedding with cylindrical shell and assemble inside cover; Described acoustically-driven circuit comprises the computer 100, binary channels Graphic equalizer 101, power amplifier I 102, the audio amplifier 103 that connect successively, and described power exciting circuit comprises the computer 100, power amplifier II 104 and the vibrator 105 that connect successively.
Described data acquisition circuit comprises data acquisition front 106 and microphone 3 and acceleration transducer 4, described microphone is arranged on the medial and lateral of simulation radome fairing by support symmetry, the distance of microphone and cylindrical shell is generally 8 ~ 12cm, described acceleration transducer symmetry is arranged on simulation radome fairing and is positioned on the barrel of microphone upper and lower, one end of described data acquisition front 106 is connected by the data analysis software of computer USB interface with computer 100, and microphone and acceleration transducer are connected to data acquisition front 106 respective signal port each via cable; Barrel between the acceleration transducer of described upper and lower part establishes point of excitation A, and described point of excitation A connects the output terminal of vibrator 105; Described audio amplifier is arranged on simulation 1m place, radome fairing dead ahead.
Described cylindrical shell and cover are rabbeted position and are adopted butyl rubber or greasy filth to seal; Described binary channels Graphic equalizer adopts 2 × 31 sections of binary channels Graphic equalizers, select the lifting of 12dB/6dB wherein and evanescent mode by switch transition, realize sound signal micro-/quick adjustment of coarse adjustment: switch is pressed as 6dB, and switch is upspring as 12db; Described audio amplifier adopts 2 12 cun, has the full-range cabinet of two divided-frequency, and comprise 12 cun of bass units and 44 titanium high pitchs, its broadband is 50-20KHz, and maximum sound pressure level is 126dB, and 2 audio amplifiers are respectively to tilted 10o ~ 25o.
principle of work
1. acoustically-driven sends required sound signal (the signal generation module that sound signal can be carried by computer for analysis software inhouse or audio edited software generate) by computer, then signal is input to 2 × 31 sections of binary channels Graphic equalizers to nurse one's health sound signal, then power amplifier I is input to, sound signal is by amplifying, be input to audio amplifier, driving audio amplifier plays sound, and in order to make sound field reach ideal effect, can be regulated by balanced device;
A the utility model adopts 2 × 31 sections of binary channels Graphic equalizers, lifting and the evanescent mode of 12dB/6dB is wherein selected by switch transition, switch is pressed as 6dB, switch is played as 12db, and check transition status by being furnished with status indicator lamp, thus realize sound signal micro-/quick adjustment of coarse adjustment;
In b the utility model, audio amplifier is according to simulating radome fairing scale model size Selection two 12 cun of audio amplifiers, two audio amplifiers are adjusted to suitable angle (slope inwardly 10o ~ 25o), simulation radome fairing is placed on the just right 1m place of audio amplifier, make to arrive simulation cowling surface sound wave and be plane wave and maximum sound pressure level can reach more than 125dB, in order to not only can white noise be provided, also can reappear radome fairing outfield complex sound field, what the utility model was selected is the full-range cabinet with two divided-frequency.
2. power excitation is equally also send pumping signal by computer, drives vibrator by power amplifier II, and then power be loaded on simulation radome fairing by vibrator, then feeds back to computer data analysis software by acceleration transducer via data acquisition front; In an experiment, according to the live signal of feedback, can regulate driver, to reach acceptable scope.
experimental procedure
1. simulate radome fairing not through any acoustic treatment, only by computer output drive force signal, the live signal that microphone and acceleration transducer record is fed back in computer for analysis software and analyzes, record the structural radiation noise (inherent characteristic of simulation radome fairing) of model;
2. model is not through any acoustic treatment, only by computer output audio signal, fed back in computer for analysis software by the live signal that microphone and acceleration transducer record and analyzes, just know the sound damping of structure;
3. simulate radome fairing not through any acoustic treatment, acoustically-driven and power excitation are added to simulation radome fairing simultaneously, the live signal that microphone and acceleration transducer record is fed back in computer for analysis software and analyzes, the sound vibration characteristic of the structure that can survey;
4., by laying different acoustical materials reducing model inside, studying it is only having acoustically-driven, only strong excitation and is having two kinds of acoustic characteristics encouraging drags simultaneously; (the utility model proposes by simulating certain known model acoustical cotton of radome fairing laid inside acoustic characteristic, after obtaining related measurement data, at the acoustical material of simulation radome fairing laid inside parameters,acoustic the unknown, carry out experiment test, and contrast with acoustical cotton measurement data above, just can obtain the parameters,acoustic of the acoustical material of parameters,acoustic the unknown);
5., by laying variety classes, the acoustical material of various combination, obtaining corresponding data and analyzing, proposing several groups of optimal cases, for the vibration and noise reducing of radome fairing provides guidance.
It is more than one of better embodiment of the present utility model, but the technical solution of the utility model is not limited only to this, in an experiment, the large I of described simulation radome fairing is determined according to actual conditions, thus the specification of audio amplifier and power amplifier is also change thereupon; The number that arranges of microphone and acceleration transducer is also increase and decrease according to actual conditions.
Claims (4)
1. a satellite fairing vibration and noise reducing simple experimental device, it is characterized in that: comprise simulation radome fairing, acoustically-driven circuit, power exciting circuit and data acquisition circuit, described simulation radome fairing (2) comprises the cover (21) at cylindrical shell (22) and two ends, described cylindrical shell is rolled by aluminium sheet and forms, described cover adopts plank to make, and is processed with the groove (211) embedding with cylindrical shell and assemble inside cover;
Described acoustically-driven circuit comprises the computer (100), binary channels Graphic equalizer (101), power amplifier I (102), the audio amplifier (103) that connect successively, and described power exciting circuit comprises the computer (100), power amplifier II (104) and the vibrator (105) that connect successively;
Described data acquisition circuit comprises data acquisition front (106) and microphone (3) and acceleration transducer (4), described microphone is arranged in simulation radome fairing by support symmetry, outside, the distance of microphone and cylindrical shell is generally 8 ~ 12cm, described acceleration transducer symmetry is arranged on simulation radome fairing (2) and is positioned on the barrel of microphone upper and lower, one end of described data acquisition front (106) is connected with computer (100) by computer USB interface, microphone and acceleration transducer are connected to data acquisition front (106) respective signal port each via cable,
Barrel between the acceleration transducer of described upper and lower part establishes point of excitation A, and described point of excitation A connects the output terminal of vibrator (105); Described audio amplifier is arranged on simulation 1m place, radome fairing dead ahead.
2. a kind of satellite fairing vibration and noise reducing simple experimental device according to claim 1, is characterized in that: described cylindrical shell (22) and cover (21) are rabbeted position and adopted butyl rubber or greasy filth to seal.
3. a kind of satellite fairing vibration and noise reducing simple experimental device according to claim 1 and 2, it is characterized in that: described binary channels Graphic equalizer (101) adopts 2 × 31 sections of binary channels Graphic equalizers, select the lifting of 12dB/6dB wherein and evanescent mode by switch transition, realize sound signal micro-/quick adjustment of coarse adjustment: switch is pressed as 6dB, and switch is upspring as 12db.
4. a kind of satellite fairing vibration and noise reducing simple experimental device according to claim 3, it is characterized in that: described audio amplifier adopts 2 12 cun, has the full-range cabinet of two divided-frequency, comprise 12 cun of bass units and 44 titanium high pitchs, its broadband is 50-20KHz, maximum sound pressure level is 126dB, and 2 audio amplifiers are respectively to tilted 10o ~ 25o.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420316354.2U CN204064620U (en) | 2014-06-14 | 2014-06-14 | A kind of satellite fairing vibration and noise reducing simple experimental device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420316354.2U CN204064620U (en) | 2014-06-14 | 2014-06-14 | A kind of satellite fairing vibration and noise reducing simple experimental device |
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| CN204064620U true CN204064620U (en) | 2014-12-31 |
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| CN201420316354.2U Withdrawn - After Issue CN204064620U (en) | 2014-06-14 | 2014-06-14 | A kind of satellite fairing vibration and noise reducing simple experimental device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104019974A (en) * | 2014-06-14 | 2014-09-03 | 广西科技大学 | Simple vibration and noise reducing test device for satellite fairing |
| CN110109974A (en) * | 2019-05-07 | 2019-08-09 | 重庆大学 | A kind of die casting machine creation data intelligent acquiring system based on power information |
-
2014
- 2014-06-14 CN CN201420316354.2U patent/CN204064620U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104019974A (en) * | 2014-06-14 | 2014-09-03 | 广西科技大学 | Simple vibration and noise reducing test device for satellite fairing |
| CN110109974A (en) * | 2019-05-07 | 2019-08-09 | 重庆大学 | A kind of die casting machine creation data intelligent acquiring system based on power information |
| CN110109974B (en) * | 2019-05-07 | 2020-12-29 | 重庆大学 | Die casting machine production data intelligent acquisition system based on power information |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20141231 Effective date of abandoning: 20160601 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |