CN105300587A - Convenient pressure gauge of airplane - Google Patents
Convenient pressure gauge of airplane Download PDFInfo
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- CN105300587A CN105300587A CN201510687648.5A CN201510687648A CN105300587A CN 105300587 A CN105300587 A CN 105300587A CN 201510687648 A CN201510687648 A CN 201510687648A CN 105300587 A CN105300587 A CN 105300587A
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Abstract
The invention relates to a convenient pressure gauge of an airplane. The pressure gauge comprises a pressure sensor, a battery surrounding the pressure sensor and a circuit module, the circuit module and the battery are combined to form an annular unit, the circuit module is detachably connected with at least one memory card, the battery supplies to the pressure sensor, and the pressure sensor transmits measuring signals to the memory card and stores the measuring signals in the memory card. According to the convenient pressure gauge of the airplane, the pressure sensor, the power supply and the memory card for storing detection data are combined to form a structural part which operates independently, it is not required to lay power lines and signals lines in an trial airplane body, limited electric energy of the airplane is not consumed, and the structural part which operates independently can be pasted to an airplane part whose pressure needs to be measured at any time. The convenient pressure gauge of the airplane can be used to complete different trial flight tasks with minimal trial airplanes, and can save a lot of money and time.
Description
Technical field
The present invention relates to a kind of aviation aerodynamics checkout equipment, especially a kind of being used for, in Aircraft Flight Test process, detects the convenient pressure tester of bearing pressure size of the structure member of aircraft.
Background technology
Need to take a flight test after the airplane design production of a new model, with check whole aircraft from fly to whether do various action in the air feasible to the dynamic property of entirety of landing, operability and security etc. again, and whether conform to its initial design, thus fully show the overall performance of aircraft, new aircraft generally will through tens secondary taking a flight test and could shape even up to a hundred.
The aircraft of new model before the finalization; usually can assemble some airplanes to take a flight test specially; these aircrafts of taking a flight test are in assembling process; according to the requirement of test mission; can before aircraft of taking a flight test finally have been assembled (before such as aircraft skin being installed); setting pressure sensor in advance on some structure member, the pressure size of bearing in the process of taking a flight test with these structure members detecting aircraft.Each pressure transducer can connect the power supply of interior of aircraft of taking a flight test by electric wire, connected the signal collection equipment of interior of aircraft of taking a flight test by signal wire simultaneously.
Usually certain frame aircraft of taking a flight test often can only be used for bearing the test mission of a part, this is because aircaft configuration is complicated and narrow space, a large amount of sensors is installed to be needed to arrange a large amount of power leads and signal wire aboard, expend electric energy limited on aircraft, have no idea disposable all sensors is arranged on all need detect structure member get on, therefore often need multi rack to bear the aircraft of taking a flight test of different test mission before aircraft sizing, need to expend surprising fund.And take a flight test aircraft after installing sensor, finally having been assembled by the structure members such as covering, then these sensors are replaced with regard to being substantially difficult to row again, being keeped in repair and even rearrange new sensor, thus the aircraft of taking a flight test of specific test mission born by a frame, once complete test mission, or preassembled pressure transducer lost efficacy gradually in the process of taking a flight test, then this aircraft of taking a flight test substantially can only be scrapped and process, and wastes huge fund.Project of taking a flight test due to the inefficacy of sensor cannot complete time, the aircraft of taking a flight test that also must re-assembly a frame new is taken a flight test, and has greatly delayed process of taking a flight test, has brought serious adverse influence to the sizing of aircraft.
Summary of the invention
The technical problem to be solved in the present invention is to provide the convenient pressure tester of a kind of aircraft, to reduce or to avoid problem noted earlier.
Specifically, the invention provides the convenient pressure tester of a kind of aircraft, it can in Aircraft Flight Test process, without the need to connecting power line and signal wire, and the pressure size can born to detect it by the structure member of the convenient connection aircraft of dismountable mode.
For solving the problems of the technologies described above, the present invention proposes the convenient pressure tester of a kind of aircraft, comprise a pressure transducer, the pressure size that the structure member that the convenient pressure tester of described aircraft is used for detecting aircraft in Aircraft Flight Test process bears, wherein, the convenient pressure tester of described aircraft comprise further the battery that arranges around described pressure transducer and with described battery combination circuit module circlewise, at least one storage card is removably connected with in described circuit module, described pressure transducer is by described powered battery and transmitted by its measuring-signal and be stored in the described storage card in described circuit module.
Preferably, the convenient pressure tester of described aircraft comprises an adhesive-layer further, and described pressure transducer and described battery and described circuit module are bonded on the structure member of described aircraft by described adhesive-layer.
Preferably, described pressure transducer is disc-shaped, and described battery and described circuit module are combined to form the disk like annulus around described pressure transducer, and described disk like annulus is thickness streamline structure thinning gradually from its centre to its outer ledge.
Preferably, the middle maximum gauge of described disk like annulus equals the thickness of described pressure transducer.
Preferably, the surface that described battery and described pressure transducer cooperatively interact is provided with the first lug electrode, described pressure transducer is provided with the first recess electrode be clasped with described first lug electrode.
Preferably, described first lug electrode and described first recess electrode are perpendicular to described adhesive-layer surface.
Preferably, the surface that described battery and described circuit module cooperatively interact is provided with the second lug electrode, described circuit module is provided with the second recess electrode be clasped with described second lug electrode.
Preferably, described second lug electrode and described second recess electrode are perpendicular to described adhesive-layer surface.
Preferably, described battery is respectively arranged with positive negative two described first lug electrodes and positive negative two described second lug electrodes.
Preferably, the described circuit module bottom mutually bonding with described adhesive-layer is provided with the Signal connector that the bottom to described pressure transducer is stretched out, and is provided with the signal contact be electrically connected with described Signal connector bottom described pressure transducer.
The convenient pressure tester of above-mentioned aircraft of the present invention is by pressure transducer, power supply and be used for storing the structure member that the storage card detecting data is combined into an independent operating, without the need to arranging power lead and signal wire in the body of aircraft of taking a flight test, without the need to expending electric energy limited on aircraft, can the structure member of whole independent operating be bonded on the aircraft components that needs to measure pressure by adhesive-layer at any time.Adopt the convenient pressure tester of aircraft of the present invention, minimum aircraft of taking a flight test can be utilized to complete multiple test mission, a large amount of funds and time can be saved.
Accompanying drawing explanation
The following drawings is only intended to schematically illustrate the present invention and explain, not delimit the scope of the invention.Wherein,
Fig. 1 display be the general structure schematic diagram of the convenient pressure tester of aircraft according to a specific embodiment of the present invention;
Fig. 2 display be the decomposition diagram of the convenient pressure tester of aircraft according to a specific embodiment of the present invention.
Embodiment
In order to there be understanding clearly to technical characteristic of the present invention, object and effect, now contrast accompanying drawing and the specific embodiment of the present invention is described.Wherein, identical parts adopt identical label.
Fig. 1 display be the general structure schematic diagram of the convenient pressure tester of aircraft according to a specific embodiment of the present invention, the pressure size that the convenient pressure tester 1 of described aircraft is born for the structure member detecting aircraft in Aircraft Flight Test process, such as, when Aircraft Flight Test, can described convenient pressure tester 1 be connected on the structure member of aircraft by dismountable mode is convenient, such as, on the structure member such as aircraft skin surface or bearing beam.
Specifically, in order to overcome the defect of the prior art that background technology part is mentioned, the invention provides the convenient pressure tester 1 of aircraft shown in Fig. 1, the convenient pressure tester 1 of this aircraft is by pressure transducer 100, power supply 200 and the storage card 301 for storing detection data are combined into the structure member of an independent operating, without the need to arranging power lead and signal wire in the body of aircraft of taking a flight test, without the need to expending electric energy limited on aircraft, can the structure member of whole independent operating be bonded on the aircraft components that needs to measure pressure by adhesive-layer 400 at any time, after detection of taking a flight test completes, the convenient pressure tester 1 of aircraft of the present invention can be pulled down easily from aircraft components, take out storage card 301 and read detection data.Adopt the convenient pressure tester 1 of aircraft of the present invention, aircraft image data of taking a flight test can be assembled specially, convenient for aircraft of the present invention pressure tester 1 all can paste on aircaft configuration when needs measurement data by the aircraft of any common assembling to be measured, even if pressure transducer 100 breaks down, be also easy to be removed the convenient pressure tester 1 of the new aircraft of replacing one.Obvious, adopt the convenient pressure tester 1 of aircraft of the present invention, minimum aircraft of taking a flight test can be utilized to complete multiple test mission, employing is needed to lay except the aircraft of taking a flight test of electric wire and signal wire in advance except specifically measuring, a large amount of pressure measurement experiments can carry out with conventional airplane measurement of taking a flight test, and can save a large amount of funds and time.
The structure of the convenient pressure tester 1 of aircraft of the present invention is described in detail referring to Fig. 2, wherein, Fig. 2 display be the decomposition diagram of the convenient pressure tester of aircraft according to a specific embodiment of the present invention, as figure, the convenient pressure tester 1 of aircraft of the present embodiment comprises a pressure transducer 100, also comprise around pressure transducer 100 arrange battery 200 and be combined into the circuit module 300 of ring-type with battery 200, at least one storage card 301 is removably connected with in circuit module 300, wherein, pressure transducer 100 is powered by battery 200 and is transmitted by its measuring-signal and be stored in the storage card 301 in circuit module 300.Certainly, in order to convenient for whole aircraft pressure tester 1 being connected on the aircraft components of needs detection, the convenient pressure tester 1 of aircraft of the present invention comprises an adhesive-layer 400 further, and pressure transducer 100 and battery 200 and circuit module 300 are bonded on the structure member of aircraft by adhesive-layer 400.
Those skilled in the art are to be understood that; pressure transducer 100 of the present invention can be any one existing pressure transducer in flaky texture that can be used for aerodynamic studies or experiment; this pressure sensor package shell market being bought acquisition can be formed the structure shown in Fig. 2 by those skilled in the art; prior art is about the principle of work of pressure transducer and internal structure; do not belong to protection scope of the present invention, this is no longer going to repeat them.
In a specific embodiment, as figure, pressure transducer 100 is in disc-shaped, and battery 200 and circuit module 300 are combined to form the disk like annulus around pressure transducer 100, and described disk like annulus is thickness streamline structure thinning gradually from its centre to its outer ledge.The vibrational power flow of the present embodiment reduces the projecting edge of pressure transducer 100 to the disturbance of air-flow by streamline structure, affects the accuracy of pressure measurements after on the structure member as far as possible avoiding bonding to aircraft.
Further, in order to reduce the disturbance of structural edge to air-flow, the middle maximum gauge of preferred disk like annulus equals the thickness of pressure transducer 100, and namely the two does not have difference in height, avoids structure and gives prominence to.Certainly, it will be appreciated by those skilled in the art that battery 200 and circuit module 300 are only combined into the ring-type of common shape for the inner structure test of aircraft, not necessarily have to be combined into disk like annulus, because inner structure is without the need to considering aerodynamic configuration and the interference problem to air-flow.It is pointed out that the present invention adopts battery 200 and circuit module 300 to be combined into the structure of ring-type, can maximize minimizing structural volume under same area, the system of being convenient to is deposited and is transported.
In another specific embodiment, the surface that battery 200 and pressure transducer 100 cooperatively interact is provided with the first lug electrode 201, pressure transducer 100 is provided with the first recess electrode 101 be clasped with the first lug electrode 201.Preferably, the first lug electrode 201 and the first recess electrode 101 are perpendicular to adhesive-layer 400 surface.
In another specific embodiment, the surface that battery 200 and circuit module 300 cooperatively interact is provided with the second lug electrode 202, circuit module 300 is provided with the second recess electrode 302 be clasped with the second lug electrode 202.Preferably, the second lug electrode 202 and the second recess electrode 302 are perpendicular to adhesive-layer 400 surface.
Also having in a specific embodiment, as figure, battery 200 is respectively arranged with positive negative two first lug electrodes 201 and positive negative two second lug electrodes 202.
Above-mentioned about in the embodiment of lug electrode and recess electrode, by the first lug electrode 201 and the first recess electrode 101 of the second lug electrode 202 and correspondence thereof and the setting of the second recess electrode 302, the maximized electric power-feeding structure decreasing battery 200 and circuit module 300 and pressure transducer 100, utilize above-mentioned electric power-feeding structure as location and the interface arrangment being connected purposes simultaneously, be convenient to assembling location, avoid structure and to misplace the thrashing brought.That is, as the checkout equipment of precision, need accuracy and the fastness of guaranteeing assembling, also will guarantee the electrical connection between each structure simultaneously.The flange adopted in above-described embodiment and groove structure, possessed the function of power supply and clamping location simultaneously, simplified the structure, improve accuracy and the fastness of assembling, improve efficiency and saved cost.In addition, adopt the flange perpendicular to adhesive-layer 400 surface and groove structure, be conducive in assembling clamping process, pressure transducer 100, power supply 200 and circuit module 300 all can press from top to bottom independently and bond on adhesive-layer 400, produce the effect of power between the structure avoiding occurring mutual clamping, affect bonding fastness.
In other specific embodiment, as shown in the figure, circuit module 300 bottom mutually bonding with adhesive-layer 400 is provided with the Signal connector 303 that the bottom to pressure transducer 100 is stretched out, and is provided with the signal contact (not shown) be electrically connected with Signal connector 303 bottom pressure transducer 100.The advantage of the present embodiment is, by the connection of Signal connector 303 and signal contact, eliminates contactor, simplifies the structure, improve the reliability of equipment.
That is, the convenient pressure tester 1 of aircraft of the present invention is when needs use, and the step of its using method is:
First the power supply 200 of released state and circuit module 300 are joined together to form disk like annulus, then this disk like annulus is bonded on adhesive-layer 400, from top to bottom pressure transducer 100 is assembled in the middle of disk like annulus afterwards, the connection of Signal connector 303 and signal contact, now whole circuit turn-on is started working, do not need to arrange any construction of switch, very convenient convenient.
Then storage card 301 is inserted, pressure transducer 100 applies certain pressure, afterwards storage card 301 is taken off reading data, whether the pressure survey numerical value stored in comparison storage card 301 is consistent with the numerical value of this pressure, if inconsistent, change idle parts and aforementioned installation steps again, finally guarantee that the convenient pressure tester 1 of whole aircraft can normally work.
Finally insert storage card 301, convenient for whole aircraft pressure tester 1 is bonded to aircaft configuration and gets on.
After having tested, convenient for whole aircraft pressure tester 1 is taken off (being peeled from aircaft configuration by adhesive-layer 400) from aircraft, take off storage card 301 and read data and can complete whole test process.
The Signal connector without switching regulator of above-described embodiment and signal contact structure, coordinate with aforesaid power supply flange and groove structure, define connection and the power supply signal structure of the plug and play of whole system, without the need to arranging extra power supply and signaling switch, utilize the mass property of existing poly-lithium battery, enough support several hours or several days time that Aircraft Flight Test experiment is usually required, simple and reliable for structure, be easy to assembling, convenient operation.
In sum, the convenient pressure tester of above-mentioned aircraft of the present invention is by pressure transducer, power supply and be used for storing the structure member that the storage card detecting data is combined into an independent operating, without the need to arranging power lead and signal wire in the body of aircraft of taking a flight test, without the need to expending electric energy limited on aircraft, can the structure member of whole independent operating be bonded on the aircraft components that needs to measure pressure by adhesive-layer at any time.Adopt the convenient pressure tester of aircraft of the present invention, minimum aircraft of taking a flight test can be utilized to complete multiple test mission, a large amount of funds and time can be saved.
Although it will be appreciated by those skilled in the art that the present invention is described according to the mode of multiple embodiment, not each embodiment only comprises an independently technical scheme.So describe in instructions be only used to clear for the purpose of; instructions should integrally be understood by those skilled in the art, and regards technical scheme involved in each embodiment as the mode that mutually can be combined into different embodiment to understand protection scope of the present invention.
The foregoing is only the schematic embodiment of the present invention, and be not used to limit scope of the present invention.Any those skilled in the art, the equivalent variations done under the prerequisite not departing from design of the present invention and principle, amendment and combination, all should belong to the scope of protection of the invention.
Claims (10)
1. the convenient pressure tester of aircraft, comprise a pressure transducer (100), the pressure size that the convenient pressure tester of described aircraft (1) is born for the structure member detecting aircraft in Aircraft Flight Test process, it is characterized in that, the convenient pressure tester of described aircraft (1) comprises the battery (200) that arranges around described pressure transducer (100) further and is combined into the circuit module (300) of ring-type with described battery (200), at least one storage card (301) is removably connected with in described circuit module (300), described pressure transducer (100) is powered by described battery (200) and is transmitted by its measuring-signal and be stored in the described storage card (301) in described circuit module (300).
2. the convenient pressure tester of aircraft as claimed in claim 1, it is characterized in that, the convenient pressure tester of described aircraft (1) comprises an adhesive-layer (400) further, and described pressure transducer (100) and described battery (200) and described circuit module (300) are bonded on the structure member of described aircraft by described adhesive-layer (400).
3. the convenient pressure tester of aircraft as claimed in claim 1, it is characterized in that, described pressure transducer (100) is in disc-shaped, described battery (200) and described circuit module (300) are combined to form the disk like annulus around described pressure transducer (100), and described disk like annulus is thickness streamline structure thinning gradually from its centre to its outer ledge.
4. the convenient pressure tester of aircraft as claimed in claim 3, it is characterized in that, the middle maximum gauge of described disk like annulus equals the thickness of described pressure transducer (100).
5. the convenient pressure tester of the aircraft as described in one of claim 1-3, it is characterized in that, the surface that described battery (200) and described pressure transducer (100) cooperatively interact is provided with the first lug electrode (201), described pressure transducer (100) is provided with the first recess electrode (101) be clasped with described first lug electrode (201).
6. the convenient pressure tester of aircraft as claimed in claim 5, is characterized in that, described first lug electrode (201) and described first recess electrode (101) are perpendicular to described adhesive-layer (400) surface.
7. the convenient pressure tester of aircraft as claimed in claim 5, it is characterized in that, the surface that described battery (200) and described circuit module (300) cooperatively interact is provided with the second lug electrode (202), described circuit module (300) is provided with the second recess electrode (302) be clasped with described second lug electrode (202).
8. the convenient pressure tester of aircraft as claimed in claim 7, is characterized in that, described second lug electrode (202) and described second recess electrode (302) are perpendicular to described adhesive-layer (400) surface.
9. the convenient pressure tester of the aircraft as described in one of claim 5-8, it is characterized in that, described battery (200) is respectively arranged with positive negative two described first lug electrodes (201) and positive negative two described second lug electrodes (202).
10. the convenient pressure tester of aircraft as claimed in claim 5, it is characterized in that, described circuit module (300) bottom mutually bonding with described adhesive-layer (400) is provided with the Signal connector (303) that the bottom to described pressure transducer (100) is stretched out, and described pressure transducer (100) bottom is provided with the signal contact be electrically connected with described Signal connector (303).
Priority Applications (9)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810082066.8A CN108225644A (en) | 2015-10-21 | 2015-10-21 | A kind of pressure measuring unit for Aircraft Flight Test |
| CN201810082052.6A CN108088601A (en) | 2015-10-21 | 2015-10-21 | A kind of convenient pressure measuring unit for aircraft |
| CN201510687648.5A CN105300587B (en) | 2015-10-21 | 2015-10-21 | The convenient pressure tester of aircraft |
| CN201810082050.7A CN108287036A (en) | 2015-10-21 | 2015-10-21 | Pressure measuring unit for Aircraft Flight Test |
| CN201810082051.1A CN108303205A (en) | 2015-10-21 | 2015-10-21 | A kind of device for aircraft pressure measurement |
| CN201810082049.4A CN108225643A (en) | 2015-10-21 | 2015-10-21 | For the device of aircraft pressure measurement |
| CN201810082067.2A CN108240883A (en) | 2015-10-21 | 2015-10-21 | For the convenient pressure measuring unit of aircraft |
| CN201810082077.6A CN108225645A (en) | 2015-10-21 | 2015-10-21 | A kind of aircraft pressure measuring unit |
| CN201810082048.XA CN108284969A (en) | 2015-10-21 | 2015-10-21 | Aircraft pressure measuring unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510687648.5A CN105300587B (en) | 2015-10-21 | 2015-10-21 | The convenient pressure tester of aircraft |
Related Child Applications (8)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810082049.4A Division CN108225643A (en) | 2015-10-21 | 2015-10-21 | For the device of aircraft pressure measurement |
| CN201810082051.1A Division CN108303205A (en) | 2015-10-21 | 2015-10-21 | A kind of device for aircraft pressure measurement |
| CN201810082077.6A Division CN108225645A (en) | 2015-10-21 | 2015-10-21 | A kind of aircraft pressure measuring unit |
| CN201810082050.7A Division CN108287036A (en) | 2015-10-21 | 2015-10-21 | Pressure measuring unit for Aircraft Flight Test |
| CN201810082048.XA Division CN108284969A (en) | 2015-10-21 | 2015-10-21 | Aircraft pressure measuring unit |
| CN201810082067.2A Division CN108240883A (en) | 2015-10-21 | 2015-10-21 | For the convenient pressure measuring unit of aircraft |
| CN201810082052.6A Division CN108088601A (en) | 2015-10-21 | 2015-10-21 | A kind of convenient pressure measuring unit for aircraft |
| CN201810082066.8A Division CN108225644A (en) | 2015-10-21 | 2015-10-21 | A kind of pressure measuring unit for Aircraft Flight Test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105300587A true CN105300587A (en) | 2016-02-03 |
| CN105300587B CN105300587B (en) | 2018-03-27 |
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Family Applications (9)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810082050.7A Pending CN108287036A (en) | 2015-10-21 | 2015-10-21 | Pressure measuring unit for Aircraft Flight Test |
| CN201810082066.8A Pending CN108225644A (en) | 2015-10-21 | 2015-10-21 | A kind of pressure measuring unit for Aircraft Flight Test |
| CN201810082048.XA Pending CN108284969A (en) | 2015-10-21 | 2015-10-21 | Aircraft pressure measuring unit |
| CN201810082067.2A Pending CN108240883A (en) | 2015-10-21 | 2015-10-21 | For the convenient pressure measuring unit of aircraft |
| CN201810082077.6A Pending CN108225645A (en) | 2015-10-21 | 2015-10-21 | A kind of aircraft pressure measuring unit |
| CN201510687648.5A Expired - Fee Related CN105300587B (en) | 2015-10-21 | 2015-10-21 | The convenient pressure tester of aircraft |
| CN201810082052.6A Pending CN108088601A (en) | 2015-10-21 | 2015-10-21 | A kind of convenient pressure measuring unit for aircraft |
| CN201810082051.1A Pending CN108303205A (en) | 2015-10-21 | 2015-10-21 | A kind of device for aircraft pressure measurement |
| CN201810082049.4A Pending CN108225643A (en) | 2015-10-21 | 2015-10-21 | For the device of aircraft pressure measurement |
Family Applications Before (5)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810082050.7A Pending CN108287036A (en) | 2015-10-21 | 2015-10-21 | Pressure measuring unit for Aircraft Flight Test |
| CN201810082066.8A Pending CN108225644A (en) | 2015-10-21 | 2015-10-21 | A kind of pressure measuring unit for Aircraft Flight Test |
| CN201810082048.XA Pending CN108284969A (en) | 2015-10-21 | 2015-10-21 | Aircraft pressure measuring unit |
| CN201810082067.2A Pending CN108240883A (en) | 2015-10-21 | 2015-10-21 | For the convenient pressure measuring unit of aircraft |
| CN201810082077.6A Pending CN108225645A (en) | 2015-10-21 | 2015-10-21 | A kind of aircraft pressure measuring unit |
Family Applications After (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810082052.6A Pending CN108088601A (en) | 2015-10-21 | 2015-10-21 | A kind of convenient pressure measuring unit for aircraft |
| CN201810082051.1A Pending CN108303205A (en) | 2015-10-21 | 2015-10-21 | A kind of device for aircraft pressure measurement |
| CN201810082049.4A Pending CN108225643A (en) | 2015-10-21 | 2015-10-21 | For the device of aircraft pressure measurement |
Country Status (1)
| Country | Link |
|---|---|
| CN (9) | CN108287036A (en) |
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- 2015-10-21 CN CN201810082048.XA patent/CN108284969A/en active Pending
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| US20060022082A1 (en) * | 2004-02-27 | 2006-02-02 | Murg Larry J | Static port skin applique apparatus and method |
| CN102473276A (en) * | 2009-08-31 | 2012-05-23 | 雅培糖尿病护理公司 | Medical devices and methods |
| US20120298801A1 (en) * | 2011-05-26 | 2012-11-29 | Bae Systems Plc | Aircraft wing and sensor |
| CN102866201A (en) * | 2012-09-13 | 2013-01-09 | 南京航空航天大学 | Aircraft skin health monitoring robot and control system for same |
| CN103640713A (en) * | 2013-12-17 | 2014-03-19 | 中国人民解放军空军装备研究院航空装备研究所 | Monitoring system of aircraft structure fatigue part |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108287036A (en) | 2018-07-17 |
| CN108225645A (en) | 2018-06-29 |
| CN108225643A (en) | 2018-06-29 |
| CN108284969A (en) | 2018-07-17 |
| CN108303205A (en) | 2018-07-20 |
| CN108088601A (en) | 2018-05-29 |
| CN105300587B (en) | 2018-03-27 |
| CN108240883A (en) | 2018-07-03 |
| CN108225644A (en) | 2018-06-29 |
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