CN108303205A - A kind of device for aircraft pressure measurement - Google Patents
A kind of device for aircraft pressure measurement Download PDFInfo
- Publication number
- CN108303205A CN108303205A CN201810082051.1A CN201810082051A CN108303205A CN 108303205 A CN108303205 A CN 108303205A CN 201810082051 A CN201810082051 A CN 201810082051A CN 108303205 A CN108303205 A CN 108303205A
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- China
- Prior art keywords
- aircraft
- pressure sensor
- pressure measurement
- pressure
- circuit module
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Abstract
A kind of device for aircraft pressure measurement, including a pressure sensor, and the circuit module around the battery of pressure sensor setting and with the battery combination circlewise, at least one storage card is detachably connected in the circuit module, the pressure sensor is transmitted and stored at by the battery powered and by its measuring signal in the storage card in the circuit module.The device for aircraft pressure measurement of the present invention is combined into an independently operated structure member by pressure sensor, power supply and for storing the storage card of detection data, without arranging power cord and signal wire in the body for aircraft of taking a flight test, without expending limited electric energy on aircraft, entire independently operated structure member can be bonded on the aircraft components for needing to measure pressure by adhesive-layer at any time.Device using the present invention for aircraft pressure measurement can utilize minimal amount of aircraft of taking a flight test to complete a variety of test missions, can save a large amount of fund and time.
Description
Technical field
It is especially a kind of for during Aircraft Flight Test, examining the present invention relates to a kind of aviation aerodynamics detection device
Survey the convenient pressure measuring unit for bearing pressure size of the structure member of aircraft.
Background technology
It takes a flight test after the airplane design production of one new model, to examine entire aircraft to fly to aerial do respectively from
Whether dynamic property, operability and the safety etc. for the entirety that landing arrive in kind of action again feasible, and with its original design side
Whether case is consistent, to fully show that the overall performance of aircraft, new aircraft will generally pass through tens times even up to a hundred times examinations
Fly to shape.
The aircraft of new model is before the finalization, it will usually and it assembles several airplanes and exclusively carries out and take a flight test, what these were taken a flight test
Aircraft is in assembling process, according to the requirement of test mission, understand before aircraft of taking a flight test finally is completed (such as aircraft is installed
Before covering), pressure sensor is installed in advance on certain structure members, these structure members to detect aircraft were being taken a flight test
The pressure size born in journey.Each pressure sensor can connect the power supply for interior of aircraft of taking a flight test by electric wire, pass through simultaneously
Signal wire connects the signal collection equipment for interior of aircraft of taking a flight test.
Certain usual frame aircraft of taking a flight test often is only used for undertaking the test mission of a part, this is because aircaft configuration is complicated
And narrow space, a large amount of sensor installation are needed to arrange a large amount of power cord and signal wire aboard, be expended on aircraft
Limited electric energy has no idea that all sensors are disposably mounted on the structure member of institute's detection in need up, therefore winged
The aircraft of taking a flight test that multi rack undertakes different test missions is generally required before machine sizing, needs to expend surprising fund.And it is winged to take a flight test
Machine is after installing sensor, being finally completed the structure members such as covering, then these sensors are substantially difficult again just
Row replaces, repairs or even rearranges new sensor, thus a frame undertakes the aircraft of taking a flight test of specific test mission, once it is complete
The gradually failure during taking a flight test at test mission or preassembled pressure sensor, then this takes a flight test aircraft substantially
Processing can only be scrapped, huge fund is wasted.It, must also be again when project of taking a flight test can not be completed due to the failure of sensor
It assembles the new aircraft of taking a flight test of a frame to take a flight test, has delayed the process of taking a flight test significantly, serious unfavorable shadow is brought to the sizing of aircraft
It rings.
Invention content
The technical problem to be solved in the present invention is to provide a kind of devices for aircraft pressure measurement, front institute is reduced or avoided
The problem of mentioning.
Specifically, the present invention provides a kind of device for aircraft pressure measurement, can be with Aircraft Flight Test during, be not necessarily to
Power cord and signal wire are connected, and can be born by the structure member of the convenient connection aircraft of dismountable mode with detecting it
Pressure size.
In order to solve the above technical problems, the present invention proposes a kind of device for aircraft pressure measurement, including a pressure passes
Sensor, the device for aircraft pressure measurement are big for detecting the pressure that the structure member of aircraft is born during Aircraft Flight Test
It is small, wherein the device for aircraft pressure measurement further comprise around the pressure sensor setting battery and with institute
The circuit module of battery combination circlewise is stated, at least one storage card, the pressure are detachably connected in the circuit module
Force snesor is transmitted and stored at by the battery powered and by its measuring signal in the storage card in the circuit module；
The device for aircraft pressure measurement further comprises an adhesive-layer, the pressure sensor and the battery and the electricity
Road module is bonded in by the adhesive-layer on the structure member of the aircraft.
The above-mentioned device for aircraft pressure measurement of the present invention is by pressure sensor, power supply and for storing detection data
Storage card is combined into an independently operated structure member, without arranging power cord and signal wire in the body for aircraft of taking a flight test,
Without expending limited electric energy on aircraft, can entire independently operated structure member be bonded in by needs by adhesive-layer at any time
On the aircraft components for measuring pressure.Device using the present invention for aircraft pressure measurement can utilize minimal amount of aircraft of taking a flight test
A variety of test missions are completed, a large amount of fund and time can be saved.
Description of the drawings
The following drawings are only intended to schematically illustrate and explain the present invention, not delimit the scope of the invention.Wherein,
The overall structure that the device for aircraft pressure measurement of a specific embodiment according to the present invention is shown in Fig. 1 is shown
It is intended to；
The exploded perspective of the device for aircraft pressure measurement of a specific embodiment according to the present invention is shown in Fig. 2
Figure.
Specific implementation mode
For a clearer understanding of the technical characteristics, objects and effects of the present invention, now control illustrates this hair
Bright specific implementation mode.Wherein, identical component uses identical label.
The overall structure that the device for aircraft pressure measurement of a specific embodiment according to the present invention is shown in Fig. 1 is shown
It is intended to, the device 1 for aircraft pressure measurement is big for detecting the pressure that the structure member of aircraft is born during Aircraft Flight Test
It is small, for example, when Aircraft Flight Test, can by the convenient pressure measuring unit 1 by dismountable mode it is convenient be connected to it is winged
On the structure member of machine, such as on the structure members such as aircraft skin surface or bearing beam.
Specifically, in order to overcome the defect of the prior art that background technology part refers to, shown in Fig. 1
The device 1 for aircraft pressure measurement, this is used for the device 1 of aircraft pressure measurement by pressure sensor 100, power supply 200 and for depositing
The storage card 301 of storage detection data is combined into an independently operated structure member, without being arranged in the body for aircraft of taking a flight test
Power cord and signal wire can be incited somebody to action by adhesive-layer 400 entire independently operated at any time without expending limited electric energy on aircraft
Structure member is bonded on the aircraft components for needing to measure pressure, after detection of taking a flight test is completed, it may be convenient to from aircraft components
On remove the present invention the device 1 for aircraft pressure measurement, take out storage card 301 reading detection data.It is using the present invention to be used for
The device 1 of aircraft pressure measurement can not have to specially assemble aircraft gathered data of taking a flight test, and any aircraft commonly assembled can need
It wants to paste the device 1 for aircraft pressure measurement of the present invention when measurement data and be measured on aircaft configuration, even if pressure
Force snesor 100 breaks down, and is also easy to be removed and replaces a new device 1 for aircraft pressure measurement.Obvious, it adopts
With the device 1 for aircraft pressure measurement of the present invention, minimal amount of aircraft of taking a flight test can be utilized to complete a variety of test missions, in addition to spy
Fixed measurement is needed using being laid in advance except the aircraft of taking a flight test of electric wire and signal wire, and a large amount of pressure measurement experiment can be with general
Logical aircraft carries out measurement of taking a flight test, and can save a large amount of fund and time.
Referring to the structure of Fig. 2 devices 1 for aircraft pressure measurement that the present invention will be described in detail, wherein Fig. 2 is shown
The decomposition perspective view of the device for aircraft pressure measurement of a specific embodiment according to the present invention is such as schemed, the use of the present embodiment
In aircraft pressure measurement device 1 include a pressure sensor 100, further include around pressure sensor 100 be arranged battery 200 with
And it is combined into cricoid circuit module 300 with battery 200, at least one storage card is detachably connected in circuit module 300
301, wherein pressure sensor 100 is powered by battery 200 and its measuring signal is transmitted and stored in circuit module 300
In storage card 301.Certainly, in order to which the device 1 that will be entirely used for aircraft pressure measurement be connected to the aircraft components for needing to detect, this hair
The bright device 1 for aircraft pressure measurement further comprises an adhesive-layer 400, pressure sensor 100 and battery 200 and circuit
Module 300 is bonded in by adhesive-layer 400 on the structure member of aircraft.
It will be appreciated by those skilled in the art that pressure sensor 100 of the present invention can be that any one is existing
The pressure sensor that can be used for aerodynamic studies or the flaky structure of experiment, those skilled in the art can will
This pressure sensor package shell for buying acquisition in the market forms structure shown in Fig. 2, the work about pressure sensor
Principle and internal structure are the prior art, are not belonging to protection scope of the present invention, and this is no longer going to repeat them.
In a specific embodiment, as schemed, pressure sensor 100 is in 300 groups of disc-shaped, battery 200 and circuit module
Close formed around pressure sensor 100 disk like annulus, the disk like annulus among it to its outer ledge in thickness it is gradual
Thinning streamline structure.The structure setting of the present embodiment can reduce the protrusion side of pressure sensor 100 by streamline structure
Disturbance of the edge to air-flow influences the accuracy of pressure measurements after avoiding being adhered to as possible on the structure member of aircraft.
Further, in order to reduce disturbance of the structural edge to air-flow, the intermediate maximum gauge of preferably disk like annulus is equal to
The thickness of pressure sensor 100, i.e. the two do not have difference in height, avoid structure protrusion.Certainly, those skilled in the art should manage
Solution, for the test of the internal structure of aircraft, battery 200 and circuit module 300 are only combined into the ring-type of common shape i.e.
Can, it have to be not necessarily combined into disk like annulus, because internal structure is without considering aerodynamic configuration and the interference problem to air-flow.
It should be pointed out that the present invention is combined into cricoid structure using battery 200 and circuit module 300, it can be most under same area
Bigization reduces structural volume, stores and transports convenient for system.
In another specific embodiment, first is provided on battery 200 and 100 mutually matched surface of pressure sensor
Lug electrode 201 is provided with the first recess electrode 101 being clasped with the first lug electrode 201 on pressure sensor 100.
Preferably, the first lug electrode 201 and the first recess electrode 101 are perpendicular to 400 surface of adhesive-layer.
In another specific embodiment, battery 200 with to be provided with second on 300 mutually matched surface of circuit module convex
Edge electrode 202 is provided with the second recess electrode 302 being clasped with the second lug electrode 202 in circuit module 300.It is preferred that
Ground, the second lug electrode 202 and the second recess electrode 302 are perpendicular to 400 surface of adhesive-layer.
In there are one specific embodiment, such as scheme, positive minus two the first flanges electricity is respectively arranged on battery 200
Pole 201 and one positive one minus two the second lug electrodes 202.
It is above-mentioned about in the embodiment of lug electrode and recess electrode, pass through the first lug electrode 201 and the second flange electricity
The setting of 101 and second recess electrode 302 of pole 202 and its corresponding first recess electrode, maximumlly reduces 200 He of battery
The power supply structure of circuit module 300 and pressure sensor 100, while using above-mentioned power supply structure as positioning and connection purposes
Clamping structure avoid structure and misplace the thrashing brought convenient for assembling positioning.That is, as accurate detection
Equipment, therefore, to assure that the accuracy and fastness of assembling, while the electrical connection being ensured that between each structure.Above-mentioned implementation
Flange and groove structure employed in example have been provided simultaneously with the function of power supply and clamping positioning, have simplified structure, improve group
The accuracy and fastness of dress, improve efficiency and have saved cost.In addition, using perpendicular to 400 surface of adhesive-layer flange and
Groove structure, during being conducive to assembling clamping, pressure sensor 100, power supply 200 and circuit module 300 can be independent
Ground presses be adhered on adhesive-layer 400 from top to bottom, avoids the occurrence of the effect of generation power between the structure being mutually clamped, influences to glue
Connect fastness.
In an other specific embodiment, as shown, the bottom that circuit module 300 is mutually bonded with adhesive-layer 400
Portion is provided with the Signal connector 303 stretched out to the bottom of pressure sensor 100, and 100 bottom of pressure sensor is provided with and signal
The signal contact (not shown) that connector 303 is electrically connected.Advantage of this embodiment is that being touched by Signal connector 303 and signal
The connection of head, is omitted contactor, simplifies structure, improve the reliability of equipment.
That is, the device 1 for aircraft pressure measurement of the present invention is when needing use, the step of application method, is：
The power supply of discrete state 200 and circuit module 300 are joined together to form disk like annulus first, then by the dish
Shape annulus is adhered on adhesive-layer 400, pressure sensor 100 is assembled among disk like annulus from top to bottom later, signal connects
First 303 and signal contact connection, at this time entire circuit turn-on start to work, any construction of switch need not be set, it is very square
It is convenient.
It is inserted into storage card 301, applies certain pressure on pressure sensor 100, later removes storage card 301
Data are read, whether the pressure measurement numerical value stored in comparison storage card 301 is consistent with the numerical value of the pressure, if inconsistent
Idle component and again aforementioned installation steps are replaced, finally ensures that the device 1 entirely for aircraft pressure measurement can normal work
Make.
It is finally inserted storage card 301, the entire device 1 for aircraft pressure measurement is adhered to aircaft configuration up.
Test removes the entire device 1 for aircraft pressure measurement after completing from aircraft (by adhesive-layer 400 from aircraft knot
Peeled on structure), it removes the reading of storage card 301 data and entire test process can be completed.
The Signal connector and signal contact structure without switching regulator of above-described embodiment, cooperation is with power supply flange above-mentioned and recessed
Slot structure forms connection and the power supply signal structure of the plug and play of whole system, it is not necessary that additional power supply and signal is arranged
Switch, using the mass property of existing poly-lithium battery, support enough Aircraft Flight Test test commonly required a few houres or
It is several days time of person, simple and reliable for structure, it is easily assembled to, it is easy to operation.
In conclusion the above-mentioned device for aircraft pressure measurement of the present invention is by pressure sensor, power supply and for storing
The storage card of detection data is combined into an independently operated structure member, without arranging power cord in the body for aircraft of taking a flight test
And signal wire can incite somebody to action entire independently operated structure member by adhesive-layer at any time without expending limited electric energy on aircraft
It is bonded on the aircraft components for needing to measure pressure.Device using the present invention for aircraft pressure measurement can utilize minimum
Aircraft of taking a flight test complete a variety of test missions, a large amount of fund and time can be saved.
It will be appreciated by those skilled in the art that although the present invention is described in the way of multiple embodiments,
It is that not each embodiment only contains an independent technical solution.So narration is used for the purpose of for the sake of understanding in specification,
The skilled in the art should refer to the specification as a whole is understood, and by technical solution involved in each embodiment
Regard as and can be combined with each other into the mode of different embodiments to understand protection scope of the present invention.
The foregoing is merely the schematical specific implementation modes of the present invention, are not limited to the scope of the present invention.It is any
Those skilled in the art, do not depart from the design of the present invention and under the premise of principle made by equivalent variations, modification and combination,
The scope of protection of the invention should all be belonged to.
Claims (1)
1. a kind of device for aircraft pressure measurement, including a pressure sensor (100), the device for aircraft pressure measurement
(1) it is used to detect the pressure size that the structure member of aircraft is born during Aircraft Flight Test, which is characterized in that described to be used for aircraft
The device (1) of pressure measurement further comprise around the pressure sensor (100) setting battery (200) and with the battery
(200) it is combined into cricoid circuit module (300), at least one storage is detachably connected in the circuit module (300)
Block (301), the pressure sensor (100) is powered by the battery (200) and is transmitted and stored at its measuring signal described
In the storage card (301) in circuit module (300)；The device (1) for aircraft pressure measurement further comprises that one is glued
Glue-line (400), the pressure sensor (100) and the battery (200) and the circuit module (300) pass through the viscose glue
Layer (400) is bonded on the structure member of the aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810082051.1A CN108303205A (en) | 2015-10-21 | 2015-10-21 | A kind of device for aircraft pressure measurement |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810082051.1A CN108303205A (en) | 2015-10-21 | 2015-10-21 | A kind of device for aircraft pressure measurement |
| CN201510687648.5A CN105300587B (en) | 2015-10-21 | 2015-10-21 | The convenient pressure tester of aircraft |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510687648.5A Division CN105300587B (en) | 2015-10-21 | 2015-10-21 | The convenient pressure tester of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108303205A true CN108303205A (en) | 2018-07-20 |
Family
ID=55198104
Family Applications (9)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810082066.8A Pending CN108225644A (en) | 2015-10-21 | 2015-10-21 | A kind of pressure measuring unit for Aircraft Flight Test |
| CN201810082067.2A Pending CN108240883A (en) | 2015-10-21 | 2015-10-21 | For the convenient pressure measuring unit of aircraft |
| CN201810082049.4A Pending CN108225643A (en) | 2015-10-21 | 2015-10-21 | For the device of aircraft pressure measurement |
| CN201810082052.6A Pending CN108088601A (en) | 2015-10-21 | 2015-10-21 | A kind of convenient pressure measuring unit for aircraft |
| CN201510687648.5A Expired - Fee Related CN105300587B (en) | 2015-10-21 | 2015-10-21 | The convenient pressure tester of aircraft |
| CN201810082077.6A Pending CN108225645A (en) | 2015-10-21 | 2015-10-21 | A kind of aircraft pressure measuring unit |
| CN201810082051.1A Pending CN108303205A (en) | 2015-10-21 | 2015-10-21 | A kind of device for aircraft pressure measurement |
| CN201810082050.7A Pending CN108287036A (en) | 2015-10-21 | 2015-10-21 | Pressure measuring unit for Aircraft Flight Test |
| CN201810082048.XA Pending CN108284969A (en) | 2015-10-21 | 2015-10-21 | Aircraft pressure measuring unit |
Family Applications Before (6)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810082066.8A Pending CN108225644A (en) | 2015-10-21 | 2015-10-21 | A kind of pressure measuring unit for Aircraft Flight Test |
| CN201810082067.2A Pending CN108240883A (en) | 2015-10-21 | 2015-10-21 | For the convenient pressure measuring unit of aircraft |
| CN201810082049.4A Pending CN108225643A (en) | 2015-10-21 | 2015-10-21 | For the device of aircraft pressure measurement |
| CN201810082052.6A Pending CN108088601A (en) | 2015-10-21 | 2015-10-21 | A kind of convenient pressure measuring unit for aircraft |
| CN201510687648.5A Expired - Fee Related CN105300587B (en) | 2015-10-21 | 2015-10-21 | The convenient pressure tester of aircraft |
| CN201810082077.6A Pending CN108225645A (en) | 2015-10-21 | 2015-10-21 | A kind of aircraft pressure measuring unit |
Family Applications After (2)
| 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 |
| CN201810082048.XA Pending CN108284969A (en) | 2015-10-21 | 2015-10-21 | Aircraft pressure measuring unit |
Country Status (1)
| Country | Link |
|---|---|
| CN (9) | CN108225644A (en) |
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- 2015-10-21 CN CN201810082067.2A patent/CN108240883A/en active Pending
- 2015-10-21 CN CN201810082049.4A patent/CN108225643A/en active Pending
- 2015-10-21 CN CN201810082052.6A patent/CN108088601A/en active Pending
- 2015-10-21 CN CN201510687648.5A patent/CN105300587B/en not_active Expired - Fee Related
- 2015-10-21 CN CN201810082077.6A patent/CN108225645A/en active Pending
- 2015-10-21 CN CN201810082051.1A patent/CN108303205A/en active Pending
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| DE10206655A1 (en) * | 2002-02-15 | 2002-10-02 | Phywe Systeme Gmbh | Electrical teaching kit component has housing with magnetic arrangement on external surface, peripheral side wall with 4 mechanical connection regions mutually offset by 90 degrees |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN108225645A (en) | 2018-06-29 |
| CN108240883A (en) | 2018-07-03 |
| CN108287036A (en) | 2018-07-17 |
| CN105300587B (en) | 2018-03-27 |
| CN108088601A (en) | 2018-05-29 |
| CN108284969A (en) | 2018-07-17 |
| CN108225644A (en) | 2018-06-29 |
| CN105300587A (en) | 2016-02-03 |
| CN108225643A (en) | 2018-06-29 |
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Application publication date: 20180720 |