CN202693125U - Air crash prediction device - Google Patents
Air crash prediction device Download PDFInfo
- Publication number
- CN202693125U CN202693125U CN 201220365091 CN201220365091U CN202693125U CN 202693125 U CN202693125 U CN 202693125U CN 201220365091 CN201220365091 CN 201220365091 CN 201220365091 U CN201220365091 U CN 201220365091U CN 202693125 U CN202693125 U CN 202693125U
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- wave
- crash prediction
- infrasonic
- prediction unit
- infrasonic wave
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Abstract
The utility model discloses an air crash prediction device. The air crash prediction device comprises a sub-sonic generating device, a sub-sonic noise sensor, a sensitive element, a voice alarm device, a sub-sonic comparing instrument, an automatic seeking device and a monitor. the air crash prediction device disclosed by the utility model has the advantages that the volume is small, the cost is lower, the air crash prediction device can be used by being directly arranged on a vehicle, the noise of a flying machine can be detected in time, and thus unnecessary disaster can be prevented from happening.
Description
Technical field
The utility model relates to the device of predicting Flight Vehicle Structure, belongs to the electronic communication technology field.
Background technology
Various aviation aircrafts are along with the increase of flight time, rate of wear increases in the use procedure, the flight-line maintenance number of times increases, its wing seam crossing fatigue strength increases, and noise is dynamic than namely applicable situation is under day, and the reminiscence ability reduces, its ratio of gear produces noise and increases, still can reach the continuity flight time by not only increasing maintenance if reach 70 decibels-80 decibels, when aviation aircraft ratio of gear noise reaches 90 decibels, can produce beyond thought airplane crash.
In order to remove a hidden danger, some airplane crash failure detectors appear in prior art, but its principle is complicated, and are bulky and cost is higher.
Thereby, a kind of volume being proposed little, the airplane crash prediction unit that cost is low then becomes the problem that the utility model faces.
The utility model content
The utility model exists principle complicated in order to solve existing airplane crash prediction unit, and bulky and problem that cost is higher provides a kind of novel airplane crash prediction unit, and it adopts following technical scheme to be achieved:
A kind of airplane crash prediction unit, it is characterized in that: comprise the Subsonic wave generator that links to each other successively, infrasonic wave noise induction device, sensitive element, phonetic alarm device, infrasonic wave comparison instrument and self-homing device, watch-dog, described Subsonic wave generator sends sine wave signal to described infrasonic wave noise induction device, described infrasonic wave noise induction device produces infrasonic wave, infrasonic wave and noise signal enter quiet contrast receiving trap and infrasonic wave comparison instrument and compare and control phonetic alarm device and report to the police by Sensitive Apparatus stack is laggard, self-homing device is sent to the watch-dog demonstration after receiving signal, and feeds back to Subsonic wave generator.
Be connected a quiet plate of shelving between the aforesaid airplane crash prediction unit, described infrasonic wave noise induction device and sensitive element.
Aforesaid airplane crash prediction unit connects a working station indicator in the feed circuit of described infrasonic wave noise induction device.
Aforesaid airplane crash prediction unit, described Subsonic wave generator comprises pulse generating means and bar magnet.
Aforesaid airplane crash prediction unit, described infrasonic sound noise induction device comprises frequency conversion sound conducting apparatus and synchro pick-up.
Compared with prior art, advantage of the present utility model and good effect are: the utility model airplane crash prediction unit volume is small and exquisite, and cost is lower, can be directly installed on vehicle-mounted upper use, and timely sense aircraft noise, thereby avoids unnecessary disaster to occur.
After reading by reference to the accompanying drawings the detailed description of the utility model embodiment, other characteristics of the present utility model and advantage will become clearer.
Description of drawings
Fig. 1 is the airplane crash generator functional-block diagram that the utility model proposes;
Fig. 2 is the part-structure schematic diagram among Fig. 1;
Fig. 3 is the cut-open view of Fig. 2;
Fig. 4 is another embodiment cut-open view of Fig. 2.
Embodiment
Below in conjunction with accompanying drawing embodiment of the present utility model is described in more detail.
Embodiment one, comprises Subsonic wave generator, infrasonic wave noise induction device, sensitive element, phonetic alarm device, infrasonic wave comparison instrument and self-homing device, the watch-dog that links to each other successively with reference to figure 1-3 the utility model.
Wherein said Subsonic wave generator comprises pulse generating means and bar magnet, and described infrasonic sound noise induction device comprises frequency conversion sound conducting apparatus and synchro pick-up.
The principle of work of the present embodiment is as follows: behind the plugged, pulse generating means produces quiet vibration, and send sine wave, this sine wave is sent to the frequency conversion sound conducting apparatus, then pass through synchro pick-up synchronously and behind the sonar equipment of frequency conversion sound conducting apparatus, the generation infrasonic wave is launched, infrasonic wave and noise signal superpose by Sensitive Apparatus, strengthen that signal is laggard to enter quiet contrast receiving trap, described quiet compare device is time-delay point contact magnetic field and contrast circuit composite set, has the static sound absorption, three groups of different sine wave signals of output after described signal filters by this device, and then enter the infrasonic wave comparison instrument, this infrasonic wave comparison instrument are worth respectively the sine wave signal noise with the noise decibel value that sets and compare, when surpassing the warning decibel, start phonetic alarm device and send warning.The ground self-homing device is sent to the watch-dog demonstration after receiving signal.In order to strengthen the pilot signal of watch-dog, between watch-dog and Subsonic wave generator, be connected with sensitive element.
Get the signal radiation in order to reduce the tester, be connected a quiet plate of shelving between described infrasonic wave noise device and the light activated element.
For display system normal operation, the present embodiment working station indicator of in above-mentioned feed circuit, connecting, when system works, pilot lamp is bright, and when system quit work, pilot lamp went out.
Fig. 2 is frequency conversion sound conducting apparatus structural representation, Fig. 3 is the cut-open view of Fig. 2, frequency conversion sound conducting apparatus and synchro pick-up, initial 10 ° of inclination angles of acoustic pickup unsupported width, expand 20 centimetres of reed alignment sensors, 40 centimetres of reed expansion sensors, 60 centimetres of reeds increase a times sensor, 80 centimetres of reeds increase a times sensor for several times, and octadentate (six directions perhaps is referring to shown in Figure 4) is along a cover cylindrical in 90 centimetres of convergence expansion sectional views, forged by red copper, the positioning reed welds upper forms through fining-off, and high frequency receptacle and asynchronous sensor need design in the other direction, quiet pulse oscillator is coated with ceramic layer by pottery and the assembling of vibration sense device on the reed.
Certainly; above-mentioned explanation is not to be to restriction of the present utility model; the utility model also is not limited in above-mentioned giving an example, and the variation that those skilled in the art make in essential scope of the present utility model, remodeling, interpolation or replacement also should belong to protection domain of the present utility model.
Claims (5)
1. airplane crash prediction unit, it is characterized in that: comprise the Subsonic wave generator that links to each other successively, infrasonic wave noise induction device, sensitive element, phonetic alarm device, infrasonic wave comparison instrument and self-homing device, watch-dog, described Subsonic wave generator sends sine wave signal to described infrasonic wave noise induction device, described infrasonic wave noise induction device produces infrasonic wave, infrasonic wave and noise signal enter quiet contrast receiving trap and infrasonic wave comparison instrument and compare and control phonetic alarm device and report to the police by Sensitive Apparatus stack is laggard, self-homing device is sent to the watch-dog demonstration after receiving signal, and feeds back to Subsonic wave generator.
2. airplane crash prediction unit according to claim 1 is characterized in that: be connected a quiet plate of shelving between described infrasonic wave noise induction device and the sensitive element.
3. airplane crash prediction unit according to claim 2 is characterized in that: connect a working station indicator in the feed circuit of described infrasonic wave noise induction device.
4. airplane crash prediction unit according to claim 3, it is characterized in that: described Subsonic wave generator comprises pulse generating means and bar magnet.
5. airplane crash prediction unit according to claim 4, it is characterized in that: described infrasonic sound noise induction device comprises frequency conversion sound conducting apparatus and synchro pick-up.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220365091 CN202693125U (en) | 2012-07-26 | 2012-07-26 | Air crash prediction device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220365091 CN202693125U (en) | 2012-07-26 | 2012-07-26 | Air crash prediction device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202693125U true CN202693125U (en) | 2013-01-23 |
Family
ID=47548729
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220365091 Expired - Fee Related CN202693125U (en) | 2012-07-26 | 2012-07-26 | Air crash prediction device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202693125U (en) |
-
2012
- 2012-07-26 CN CN 201220365091 patent/CN202693125U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130123 Termination date: 20140726 |
|
| EXPY | Termination of patent right or utility model |