CN205958182U - Center of gravity of airplane measurement system - Google Patents
Center of gravity of airplane measurement system Download PDFInfo
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- CN205958182U CN205958182U CN201620835146.2U CN201620835146U CN205958182U CN 205958182 U CN205958182 U CN 205958182U CN 201620835146 U CN201620835146 U CN 201620835146U CN 205958182 U CN205958182 U CN 205958182U
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Abstract
The utility model discloses a center of gravity of airplane measurement system, this center of gravity of airplane measurement system include control end module, data acquisition module, reach data receiver module, data acquisition module connects data receiver module, data acquisition module includes a plurality of sensors, each the aircraft wheel pair planar pressure data of aircraft under being in the level or being in two kinds of at least different states of the certain angle of slope are gathered to the sensor, data receiver module connects the control end module is received the pressure data erupt simultaneously and deliver to the control end module, the control end module, including display element and input unit, input unit takes turns the size data of interval and the angle column input of aircraft slope with the aircraft the main control unit, the main control unit is right pressure data, size data and angle column handles and in the last demonstration of display element. The utility model discloses a center of gravity of airplane measurement system is more accurate and convenient to the focus measuring of aircraft.
Description
Technical field
This utility model is particularly to a kind of center of gravity of airplane measuring system.
Background technology
Center of gravity of airplane measurement in the market typically utilizes suspension method, by hanging the intersection point of vertical line twice,
Estimate position of centre of gravity.Or manually measure critical size and distribution of weight, list center of gravity needed for equalising torque formula calculates,
Whole center of gravity calculation and weight measurement are required for manually participating in, and are susceptible to human error, error problem, and weighing process is multiple
Miscellaneous, operation extremely inconvenience.
Utility model content
Main purpose of the present utility model is to provide a kind of center of gravity of airplane measuring system it is intended to ensure center of gravity of airplane measurement
Accurate and convenient.
For achieving the above object, the utility model proposes center of gravity of airplane measuring system, this center of gravity of airplane measuring system includes
Console module, data acquisition module and data reception module；
Described data acquisition module connects described data reception module, and described data acquisition module includes multiple sensors,
Described sensor acquisition aircraft be in level or be in tilt certain angle at least two different conditions under each aircraft wheel
Pressure data to plane；
Described data reception module connects described console module, receives described pressure data and sends to described control end
Module；
Described console module, the display unit connect including main control unit and with described main control unit and input list
Unit, the angle-data of the sized data of aircraft wheel spacing and craft inclination is inputted described main control unit by described input block,
Described main control unit is processed to described pressure data, sized data and angle-data and is shown on described display unit.
Preferably, described data acquisition module also includes first processor and transmitting element, and described sensor connects described
First processor located at aircraft wheel bottom；
Described transmitting element connects described first processor, and described pressure data is sent to described data reception module.
Preferably, described data acquisition module also includes ciphering unit, and described ciphering unit connects described first processor,
Described pressure data is encrypted.
Preferably, described data reception module includes second processing device and multichannel receiving unit, and described multichannel receives
Unit connects described second processing device, receives the described pressure data of the transmission of described transmitting element, and described second processing device is even
Connect described console module.
Preferably, described data reception module also includes USB joint and USB turns serial port chip, and described USB turns serial port chip
Connect described second processing device, described USB joint connects described second processing device, turns serial port chip by USB and be detachably connected
Described console module.
Preferably, described data reception module also includes data check unit, and described data check unit connects described the
Two processors.
Preferably, described console module also includes serial port unit and output unit,
Described serial port unit connects described main control unit, receives the described pressure data that described second processing device sends,
Described output unit connects described main control unit, calculates described pressure data, sized data and angle-data, and in
Result of calculation is shown on described display unit.
Preferably, described console module also includes connecting the select unit of described main control unit.
Preferably, described console module also includes alignment unit, and described alignment unit connects described main control unit.
Preferably, described data acquisition module also includes charhing unit, and described charhing unit connects described first processor.
Technical solutions of the utility model pass through at least two different shapes in level or in horizontal tilt certain angle for the aircraft
Under state, the pressure that data acquisition module is distributed in each aircraft wheel to aircraft carries out real-time pressure data collection, control end mould
Block carries out the process of pressure data, sized data and angle-data again by data reception module, and accurate calculation goes out the weight of aircraft
The heart.The measurement of aircraft and calculate center of gravity process simple, simple operation.
Brief description
In order to be illustrated more clearly that this utility model embodiment or technical scheme of the prior art, below will be to embodiment
Or in description of the prior art the accompanying drawing of required use be briefly described it should be apparent that, drawings in the following description are only
It is some embodiments of the present utility model, for those of ordinary skill in the art, in the premise not paying creative work
Under, other accompanying drawings can also be obtained according to the structure shown in these accompanying drawings.
Fig. 1 is the structural representation of this utility model center of gravity of airplane measuring system one embodiment；
Fig. 2 is that the aircraft of this utility model center of gravity of airplane measuring system is under horizontality, after aircraft nose wheel and aircraft
The principle schematic of the subpoint in aircraft symmetrical profile for the wheel；
Fig. 3 is that the aircraft of this utility model center of gravity of airplane measuring system is under heeling condition, after aircraft nose wheel and aircraft
The principle schematic of the subpoint in aircraft symmetrical profile for the wheel.
Drawing reference numeral explanation：
| Label | Title | Label | Title |
| 10 | Console module | 22 | Sensor |
| 11 | Main control unit | 23 | Transmitting element |
| 12 | Serial port unit | 24 | Ciphering unit |
| 13 | Display unit | 25 | Charhing unit |
| 14 | Output unit | 30 | Data reception module |
| 15 | Select unit | 31 | Second processing device |
| 16 | Input block | 32 | Multichannel receiving unit |
| 17 | Alignment unit | 33 | USB joint |
| 20 | Data acquisition module | 34 | USB turns serial port chip |
| 21 | First processor | 35 | Data check unit |
The realization of this utility model purpose, functional characteristics and advantage will be described further in conjunction with the embodiments referring to the drawings.
Specific embodiment
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is carried out
Clearly and completely describe it is clear that described embodiment is only a part of embodiment of the present utility model, rather than all
Embodiment.Based on the embodiment in this utility model, those of ordinary skill in the art are not making creative work premise
Lower obtained every other embodiment, broadly falls into the scope of this utility model protection.
It is to be appreciated that the directional instruction (such as up, down, left, right, before and after ...) of institute in this utility model embodiment
It is only used for explaining the relative position relation between each part, motion conditions etc. under a certain particular pose (as shown in drawings), such as
When really this particular pose changes, then directionality instruction also correspondingly changes therewith.
In this utility model, unless otherwise clearly defined and limited, term " connection ", " fixation " etc. should do broad sense reason
Solution, for example, " fixation " can be fixedly connected or be detachably connected, or integral；Can be to be mechanically connected, also may be used
To be electrical connection；Can be to be joined directly together it is also possible to be indirectly connected to by intermediary, can be the connection of two element internals
Or the interaction relationship of two elements, limit unless otherwise clear and definite.For the ordinary skill in the art, permissible
Understand concrete meaning in this utility model for the above-mentioned term as the case may be.
In addition, such as relating to the description of " first ", " second " etc. is only used for describing purpose in this utility model, and can not manage
Solve as indicating or implying its relative importance or the implicit quantity indicating indicated technical characteristic.Thus, define " the
One ", the feature of " second " can be expressed or implicitly include at least one this feature.In addition, the skill between each embodiment
Art scheme can be combined with each other, but must be capable of by those of ordinary skill in the art based on, when technical scheme
In conjunction with occurring conflicting or will be understood that the combination of this technical scheme does not exist when cannot realize, also not in this utility model
Within the protection domain requiring.
The utility model proposes a kind of center of gravity of airplane measuring system.
Referring to figs. 1 to Fig. 3, in this utility model one embodiment, this center of gravity of airplane measuring system includes console module
10th, data acquisition module 20 and data reception module 30；
Data acquisition module 20 connects data reception module 30, and data acquisition module 20 includes multiple sensors 22, sensing
Device 22 gather aircraft be in level or be in tilt certain angle at least two different conditions under each aircraft wheel to plane
Pressure data；
Data reception module 30 connects console module 10, receives pressure data and sends to console module 10；
Console module 10, the display unit 13 connect including main control unit 11 and with main control unit 11 and input block
16, the angle-data of the sized data of aircraft wheel spacing and craft inclination is inputted main control unit 11, master control by input block 16
Unit 11 is processed to pressure data, sized data and angle-data and is shown on display unit 13.
Above-mentioned console module 10 can be separately provided, and the process carrying out data message by connecting processor calculates, excellent
Selection of land, console module 10 is arranged in main control computer or terminating machine by computer client, is specifically in mobile phone, computer or class
Like being mounted with console module 10 in equipment, by being collected to data message inputting, and by corresponding program and formula
Precisely and quickly calculate the center of gravity of aircraft.
Specifically, because aircraft is generally at least three aircraft wheels, it is divided into aircraft nose wheel and aircraft trailing wheel, aircraft is integrally tied
Structure employing is symmetrical in length and breadth, and the center of gravity of aircraft is located on the intermediate symmetry section of aircraft, and sensor 22 measures each in real time and flies
The pressure data of wheel, and corresponding on two upright projection points with aircraft trailing wheel for the aircraft nose wheel on symmetrical profile.Due to
Interaction force between two objects, always equal in magnitude, in opposite direction, position is identical, and is respectively acting on this two things
On body, according to this law, the pressure data that aircraft is distributed in each aircraft wheel is measured by sensor 22, that is, measure is real-time
Data, aircraft gross weight is each pressure data sum.
When rigid body is in poised state, projection generation on each axle of rectangular coordinate system for the power and moment on rigid body of acting on
Count and be equal to zero.According to this principle, measure pressure data and aircraft tyre tread parameter.
When with aircraft trailing wheel symmetrical profile upright projection point for zero O, aircraft nose wheel and aircraft trailing wheel are right
The upright projection point line of section is called X-axis, and the plane residing for perpendicular to aircraft balanced state and the straight line of X-axis are Y-axis, set up
Coordinate system is it is assumed that barycentric coodinates are G (a, b).
Aircraft is put down and is lain across under horizontality, measures pressure data by data acquisition module 20.Referring to Fig. 2, specially：
PH+Ph-W=0；
PH × L-W × a=0；
The pressure data that PH therein gathers for aircraft nose wheel；The pressure data that Ph gathers for aircraft trailing wheel；Before L is aircraft
Wheel and the air line distance of aircraft trailing wheel subpoint on the symmetrical plane of aircraft；W is aircraft gross weight, that is, all number pressures gathering
According to sum；A is the X-axis distance of center of gravity range coordinate initial point O.
When aircraft balanced is under two kinds of different conditions, referring to Fig. 3, P ' in Fig. 3HCan be divided into and surveying under two kinds of different conditions
The pressure data of amount, is designated as P respectivelyH1And PH2, can be derived according to above-mentioned formula and trigonometric function
Can arrange and be：
Wherein, a is the X-axis distance of center of gravity range coordinate initial point O；B is the Y-axis distance of center of gravity range coordinate initial point O；PH1For
Horizontality get off the plane front-wheel collection a certain pressure data；PH2For under aircraft nose wheel raised condition, that is, verting certain angle simultaneously
It is in a certain pressure data of poised state；W is aircraft gross weight, that is, all pressure data sums gathering；L be aircraft nose wheel with
The air line distance of aircraft trailing wheel subpoint on the symmetrical plane of aircraft, β1With β2The angle raised for aircraft nose wheel.
Technical solutions of the utility model pass through at least two different shapes in level or in horizontal tilt certain angle for the aircraft
Under state, the pressure that data acquisition module 20 is distributed in each aircraft wheel to aircraft carries out pressure data collection, console module 10
Carry out the process of pressure data, sized data and angle-data again by data reception module 30, accurate calculation goes out the weight of aircraft
The heart.The measurement of aircraft and calculate center of gravity process simple, simple operation.
Preferably, data acquisition module 20 also includes first processor 21 and transmitting element 23, and sensor 22 connects first
Processor 21 located at aircraft wheel bottom；
Transmitting element 23 connects first processor 21, and pressure data is sent to data reception module 30.
Above-mentioned data acquisition module 30 can be pressure transducer or electronic scale etc., preferably uses Wireless data acquisition unit,
Do not restricted by the position of aircraft and size with this, convenient and quick collection aircraft is distributed in each aircraft wheel pressure
Real time data, first processor 21 can adopt micro-chip processor, and data acquisition module 20 can be real respectively by multiple sensors 22
When survey aircraft be distributed in the pressure data of each aircraft wheel, and carry out the monitoring of pressure data, bag by first processor 21
Include the number of times of the collection per minute to pressure data, the exceptional value of data is omitted, temporary, the transmission DATA REASONING of data of data
Scope etc.；Transmitting element 23 can adopt and be wiredly connected to data reception module 30, preferably wireless connection data receiver module
30, make not restricted by the length of connecting line by the pressure data of first processor 21, be fast sent to data acquisition module 20
In.
Further, when data reception module 30 receives to the pressure data in data acquisition module 20, can carry out
Safety management, by unidirectional data transmission, that is, data reception module 30 can only pressure in unidirectional receiving data acquisition module 20
Data it is impossible to driver to the parameter setting in data acquisition module 20 and first processor 21 etc. is modified, to protect
The accurate and reliability of shield pressure data measurement.
Further, data acquisition module 20 also includes ciphering unit 24, and ciphering unit 24 connects first processor 21,
Data message is encrypted.Ciphering unit 24 also can be encrypted to facility information, and facility information may include measured center of gravity
Aircraft number and measurement be distributed in numbering of each sensor of aircraft wheel pressure data etc., the encryption side of ciphering unit 24
Formula can be mutually to be matched etc. with data reception module 30 using interpolation identifying code or data acquisition module 20, especially data
During the pressure data that receiver module 30 first time receiving data acquisition module 20 sends, carry out identifying code checking, by rear, data
Receiver module 30 carries out unidirectional real-time reception pressure data, to ensure the safety of data transfer.
Preferably, data acquisition module 20 also includes charhing unit 25, and charhing unit 25 connects first processor 21.Due to
Data acquisition module 20 includes multiple sensors 22, and each sensor 22 can be separately provided, and by charhing unit 25, can be easy to
Sensor 22 mutually exchanges, and high-efficiency continuous carrying out measures in real time, during measurement pressure data information, without to data acquisition module
Block 20 carries out the operation such as external power supply, convenient to use.
Preferably, data reception module 30 includes second processing device 31 and multichannel receiving unit 32, and multichannel receives single
Unit 32 connection second processing device 31, receives the pressure data that transmitting element 23 sends, second processing device 31 connects console module
10.
Above-mentioned second processing device 31 can adopt micro-chip processor, is convenient for quickly connecing by multichannel receiving unit 32
Receive pressure data, second processing device 31 is quickly processed, be identified, decompress, store including to the pressure data receiving.Optional
Ground, data reception module 30 can be separately provided, and carries out wired or wireless connection with console module 10, can keep in as data base
The pressure data of measurement, console module 10 carries out the reading of information needed to the data in data reception module 30.Data connects
Receiving module 30 can be in also integrative-structure with console module 10, make the pressure data in data reception module 30 more rapidly anti-
Present in console module 10.
Preferably, data reception module 30 also includes USB joint 33 and USB turns serial port chip 34, and USB turns serial port chip 34
Connect second processing device 31, USB joint 33 connects second processing device 31, turns serial port chip 34 by USB and is detachably connected control
End module 10.
Above-mentioned USB turns serial port chip 34 and can adopt the chip such as FT232, PL2303, CH340, and USB turns serial port chip 34 to be made
Be can transmit in console module 10 by USB joint 33 by the pressure data of second processing device 31.Data reception module 30
Can be separately provided, similar to Bluetooth Receiver, be connected with console module 10 plug by USB joint 33, make console module
10 can not limit fixed position, can rapidly receive pressure data whenever and wherever possible by grafting data reception module 30.
Preferably, data reception module 30 also includes data check unit 35, and data check unit 35 connects second processing
Device 31.
Data check unit 35 therein is used for carrying out screening correct data, is identified as required pressure data, and right
Dispense in the larger numerical value of exceptional value or fluctuation ratio, other irrelevant informations can carry out denied access or shielding etc., to ensure to fly
The reliability of machine center of gravity calculation and degree of accuracy.
Further, it is preferable to, console module 10 also includes serial port unit 12, output unit 14,
Serial port unit 12 connects main control unit 11, receives the pressure data that second processing device 31 sends,
Output unit 14 connects main control unit 11, calculates pressure data, sized data and angle-data and in display unit
Result of calculation is shown on 13.
Above-mentioned serial port unit 12 may include multiple USB interface, facilitates the USB joint 33 of data reception module 30 to connect,
External memory storage also can be connected by serial port unit 12, can be used for the aircraft wheel importing aircraft ratio figure and different aircraft type
Between sized data information etc., also can derive console module 10 and calculate the relevant informations such as the concrete data of the center of gravity of airplane.Aobvious
Show that unit 13 can adopt touch screen displays or input through keyboard, size between the aircraft wheel of measurement can be directly inputted by display unit 13
Related data, or sized data of relevant difference aircrafts of preserving of the data base within console module 10 of conducting interviews etc.,
Pass through output unit 14 again, carry out the accurate calculation of related data information.
Preferably, console module 10 also includes connecting the select unit 15 of main control unit 11.
Select unit 15, input block 16 and output unit 14 may be disposed in display unit 13, and with main control unit 11
Connect, by display unit 13 in order to operate.Input block 16 therein connects main control unit 11, can be used for inputting aircraft wheel
Sized data and aircraft are in ratio figure.Select unit 15 connects main control unit 11, for selecting different pressure datas, can have
Body selects the pressure data of sensor 22 measurement when each aircraft wheel pressure of pre-test, because sensor 22 is multiple, and can
Separate, specifically it is allocated in calculation procedure by the pressure data that select unit 15 can make the measurement of each sensor 22, and
Corresponding to aircraft nose wheel and two corresponding on symmetrical profile subpoints of aircraft trailing wheel.
Further, it is preferable to, console module 10 also includes alignment unit 17, and alignment unit 17 connects main control unit
11.Alignment unit 17, to carrying out calibration accuracy to pressure data and result of calculation, can be accurate to one decimal place, make measurement
Center of gravity of airplane position data more accurate.
The foregoing is only preferred embodiment of the present utility model, not thereby limit the scope of the claims of the present utility model,
Every equivalent structure under utility model of the present utility model is conceived, made using this utility model description and accompanying drawing content
Conversion, or directly/be indirectly used in other related technical fields and be included in scope of patent protection of the present utility model.
Claims (10)
1. a kind of center of gravity of airplane measuring system is it is characterised in that include console module, data acquisition module and data receiver
Module；
Described data acquisition module connects described data reception module, and described data acquisition module includes multiple sensors, described
Sensor acquisition aircraft be in level or be in certain angle at least two different conditions under each aircraft wheel to flat
The pressure data in face；
Described data reception module connects described console module, receives described pressure data and sends to described control end mould
Block；
Described console module, the display unit connect including main control unit and with described main control unit and input block, institute
State input block and the angle-data of the sized data of aircraft wheel spacing and craft inclination is inputted described main control unit, described master
Control unit is processed to described pressure data, sized data and angle-data and is shown on described display unit.
2. center of gravity of airplane measuring system as claimed in claim 1 is it is characterised in that described data acquisition module also includes first
Processor and transmitting element, described sensor connects described first processor and located at aircraft wheel bottom；
Described transmitting element connects described first processor, and described pressure data is sent to described data reception module.
3. center of gravity of airplane measuring system as claimed in claim 2 is it is characterised in that described data acquisition module also includes encrypting
Unit, described ciphering unit connects described first processor, and described pressure data is encrypted.
4. center of gravity of airplane measuring system as claimed in claim 2 is it is characterised in that described data reception module is included at second
Reason device and multichannel receiving unit, described multichannel receiving unit connects described second processing device, receives described transmitting element and sends out
The described pressure data sending, described second processing device connects described console module.
5. center of gravity of airplane measuring system as claimed in claim 4 is it is characterised in that described data reception module also includes USB
Joint and USB turn serial port chip, and described USB turns serial port chip and connects described second processing device, and described USB joint connects described the
Two processors, turn serial port chip by USB and are detachably connected described console module.
6. center of gravity of airplane measuring system as claimed in claim 4 is it is characterised in that described data reception module also includes data
Verification unit, described data check unit connects described second processing device.
7. center of gravity of airplane measuring system as claimed in claim 4 is it is characterised in that described console module also includes serial ports list
Unit, output unit,
Described serial port unit connects described main control unit, receives the described pressure data that described second processing device sends,
Described output unit connects described main control unit, calculates described pressure data, sized data and angle-data, and in described
Result of calculation is shown on display unit.
8. center of gravity of airplane measuring system as claimed in claim 7 is it is characterised in that described console module also includes connecting institute
State the select unit of main control unit.
9. center of gravity of airplane measuring system as claimed in claim 7 is it is characterised in that described console module also includes calibration list
Unit, described alignment unit connects described main control unit.
10. center of gravity of airplane measuring system as claimed in claim 2 is it is characterised in that described data acquisition module also includes filling
Electric unit, described charhing unit connects described first processor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620835146.2U CN205958182U (en) | 2016-08-03 | 2016-08-03 | Center of gravity of airplane measurement system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620835146.2U CN205958182U (en) | 2016-08-03 | 2016-08-03 | Center of gravity of airplane measurement system |
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| CN205958182U true CN205958182U (en) | 2017-02-15 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107128497A (en) * | 2017-04-19 | 2017-09-05 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Aircraft Air is by oil system |
| CN107545804A (en) * | 2017-09-08 | 2018-01-05 | 中国飞行试验研究院 | A kind of center of gravity of airplane indicating means |
| CN107741300A (en) * | 2017-09-08 | 2018-02-27 | 中国飞行试验研究院 | A kind of center of gravity of airplane instruction device |
| CN112158357A (en) * | 2020-08-28 | 2021-01-01 | 成都飞机工业（集团）有限责任公司 | Device and method for measuring deviation between thrust line and gravity center of unmanned aerial vehicle booster rocket |
-
2016
- 2016-08-03 CN CN201620835146.2U patent/CN205958182U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107128497A (en) * | 2017-04-19 | 2017-09-05 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Aircraft Air is by oil system |
| CN107545804A (en) * | 2017-09-08 | 2018-01-05 | 中国飞行试验研究院 | A kind of center of gravity of airplane indicating means |
| CN107741300A (en) * | 2017-09-08 | 2018-02-27 | 中国飞行试验研究院 | A kind of center of gravity of airplane instruction device |
| CN107741300B (en) * | 2017-09-08 | 2019-06-28 | 中国飞行试验研究院 | A kind of center of gravity of airplane instruction device |
| CN107545804B (en) * | 2017-09-08 | 2019-10-18 | 中国飞行试验研究院 | A kind of center of gravity of airplane indicating means |
| CN112158357A (en) * | 2020-08-28 | 2021-01-01 | 成都飞机工业（集团）有限责任公司 | Device and method for measuring deviation between thrust line and gravity center of unmanned aerial vehicle booster rocket |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170215 Termination date: 20200803 |