CN103278229A - Helicopter weighing measurer and helicopter gravity core measuring method - Google Patents
Helicopter weighing measurer and helicopter gravity core measuring method Download PDFInfo
- Publication number
- CN103278229A CN103278229A CN2013101876422A CN201310187642A CN103278229A CN 103278229 A CN103278229 A CN 103278229A CN 2013101876422 A CN2013101876422 A CN 2013101876422A CN 201310187642 A CN201310187642 A CN 201310187642A CN 103278229 A CN103278229 A CN 103278229A
- Authority
- CN
- China
- Prior art keywords
- helicopter
- pressure type
- weighing measurement
- measurement device
- type sensor
- Prior art date
- 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.)
- Granted
Links
Images
Abstract
The invention relates to a helicopter weighing measurer and a helicopter gravity core measuring method. The helicopter weighing measurer comprises a shell and four spoke press-type sensors which are arranged in the shell, wherein a bearing column of each spoke press-type sensor is used for sensing the deformation of the stressed shell, the four spoke press-type sensors are connected with one another in parallel to form a force sensing assembly; the input end of the force sensing assembly is connected with a voltage stabilizing circuit, and the output end of the force sensing assembly is connected with a current amplifier; and an output impedance adjusting resistor is bridged between a first signal output end and a second signal output end of each spoke press-type sensor, and the first signal output end and the second signal output end of each spoke press-type sensor are respectively connected with an isolation resistor. The four spoke press-type sensors are connected in parallel, so that the measuring precision is improved.
Description
Technical field
The present invention relates to helicopter weighing measurement device and helicopter center of gravity measurement method.
Background technology
Present China most of helicopter manufacturer, system shop and use department of army still continue to use mechanical platform scale and add weight and the centre of gravity place that artificial Calculation Method obtains helicopter.The original backwardness of the method, and waste time and energy, measuring accuracy is subjected to human factor to influence big and is difficult to guarantee.Especially in the safeguard work of airport, the method takies more personnel, and Measuring Time is longer, and precision can't ensure.
Summary of the invention
The objective of the invention is to propose a kind of helicopter weighing measurement device, it can solve, and measuring accuracy is hanged down and the problem of inefficiency.
In order to achieve the above object, the technical solution adopted in the present invention is as follows:
Helicopter weighing measurement device, four spoke pressure type sensors that it comprises a housing and is positioned at described housing, the pressure-bearing post of spoke pressure type sensor is used for the induction housing because of the stressed deformation quantity that produces, and described four spoke pressure type sensors are connected in parallel, and form the power inductive component; The input end of power inductive component is connected with a mu balanced circuit, and the output terminal of power inductive component is connected with a current amplifier; Cross-over connection has an output impedance to adjust resistance between first signal output part of each spoke pressure type sensor and the secondary signal output terminal, and first signal output part of each spoke pressure type sensor and secondary signal output terminal all are connected with an isolation resistance.
Preferably, for the ease of the rolling of wheel, described housing is connected and composed by cover plate, base plate, left swash plate, right swash plate, protecgulum and bonnet, and is formed with the ccontaining cavity for ccontaining spoke pressure type sensor; Cover plate and base plate are writing board shape, the bottom surface of left side swash plate and the bottom surface of right swash plate are the plane, the end face of left side swash plate and the end face of right swash plate are an inclined-plane, the bottom surface of left side swash plate and the bottom surface of right swash plate all flush with the bottom surface of base plate, the top on described inclined-plane flushes with the end face of cover plate, and protecgulum or bonnet are provided with the electric connection terminal group; Fit in the pressure-bearing post of spoke pressure type sensor and the bottom surface of cover plate, the bottom of spoke pressure type sensor is fixed on the base plate, and the input end of the output terminal of current amplifier, the power end of current amplifier and mu balanced circuit all is connected with the electric connection terminal group.Further, because the wheel tyre surface is wideer, four spoke pressure type sensors are cross shape and distribute.The helicopter weighing measurement device of this structure is called dull and stereotyped helicopter weighing measurement device.
Preferably, in order accurately to measure centre of gravity place, described housing is connected and composed by cover plate, base plate and annular leg, and is formed with the ccontaining cavity for ccontaining spoke pressure type sensor; Cover plate and base plate are writing board shape, and the end face of cover plate extends upward one and be used for the projection chimeric with the strong point groove of the fuselage of helicopter, and annular leg is provided with the electric connection terminal group; Fit in the pressure-bearing post of spoke pressure type sensor and the bottom surface of cover plate, the bottom of spoke pressure type sensor is fixed on the base plate, and the input end of the output terminal of current amplifier, the power end of current amplifier and mu balanced circuit all is connected with the electric connection terminal group.Further preferred, in order to adjust helicopter at horizontal level, the bottom surface of base plate also is bolted with one for the threaded rod of regulating the helicopter horizontal level.The helicopter weighing measurement device of this structure is called cylindricality helicopter weighing measurement device.
The invention allows for a kind of helicopter center of gravity measurement method, it may further comprise the steps:
The electric connection terminal group of three aforesaid dull and stereotyped helicopter weighing measurement devices is connected with a single-chip microcomputer, and described single-chip microcomputer also connects a display screen;
Three wheels of helicopter are placed respectively on the cover plate of three helicopter weighing measurement devices, and a wheel is corresponding with a helicopter weighing measurement device;
Utilize described single-chip microcomputer to gather the signal of helicopter weighing measurement device output, and obtain weight and the centre-of-gravity range of helicopter according to the calculated signals that collects, and weight and the centre-of-gravity range of helicopter shown on described display screen.
The invention allows for another kind of helicopter center of gravity measurement method, it may further comprise the steps:
The electric connection terminal group of four aforesaid cylindricality helicopter weighing measurement devices is connected with a single-chip microcomputer, and described single-chip microcomputer also connects a display screen;
Four strong point grooves of the fuselage of helicopter are chimeric with the projection of the cover plate of four helicopter weighing measurement devices respectively, and a strong point groove is corresponding with a helicopter weighing measurement device;
Utilize described single-chip microcomputer to gather the signal of helicopter weighing measurement device output, and obtain weight and the centre of gravity place of helicopter according to the calculated signals that collects, and weight and the centre of gravity place of helicopter shown on described display screen.
The present invention has following beneficial effect:
1, four spoke pressure type sensors is connected in parallel, has improved measuring accuracy.
2, dull and stereotyped helicopter weighing measurement device adopts the wheel supporting way, has solved the problem of quick measurement weight and centre-of-gravity range.
3, cylindricality helicopter weighing measurement device adopts lifting jack to support aircraft strong point mode, has solved the problem of accurate measurement weight and centre of gravity place;
4, adopt the single-chip microcomputer detection technique to replace mechanical platform scale and artificial calculating, reduced manually, improved efficient, can accurately measure centre of gravity place.
Description of drawings
Fig. 1 is the cross-sectional view of the helicopter weighing measurement device of the embodiment of the invention one;
Fig. 2 is the electrical block diagram of power inductive component of the helicopter weighing measurement device of the embodiment of the invention one;
Fig. 3 is the distribution schematic diagram of spoke pressure type sensor of the helicopter weighing measurement device of the embodiment of the invention one;
Fig. 4 is the cross-sectional view of the helicopter weighing measurement device of the embodiment of the invention two;
Fig. 5 is the distribution schematic diagram of spoke pressure type sensor of the helicopter weighing measurement device of the embodiment of the invention two;
Fig. 6 is for being the application synoptic diagram of the helicopter weighing measurement device of the embodiment of the invention two.
Embodiment
Below, by reference to the accompanying drawings and embodiment, the present invention is described further.
Embodiment one
As shown in Figure 1 to Figure 3, helicopter weighing measurement device, four spoke pressure type sensors 5 that it comprises a housing and is positioned at described housing.Need to prove that the spoke pressure type sensor 5 of present embodiment is known technology, is 200820030228.5 the disclosed radial sensor of Chinese utility model patent as application number.Spoke pressure type sensor is the function translator spare that non electrical quantity (pressure) is converted to electric weight (electric current).The spoke pressure type principle of sensors of resistance-strain type: elastic body (flexible member, sensitive beam) produces elastic deformation under external force, make the resistance strain gage (conversion element) that sticks on his surface also in company with producing distortion, after the resistance strain gage distortion, its resistance will change (increase or reduce), through corresponding amplifying circuit this resistance variations is converted to electric signal (voltage or electric current) again, thereby has finished the process that external force is transformed to electric signal.The precision of spoke pressure type sensor directly influences the precision of weighing.
The pressure-bearing post of spoke pressure type sensor 5 is used for the induction housing because of the stressed deformation quantity that produces, and described four spoke pressure type sensors 5 are connected in parallel, thereby forms the power inductive component.
Concrete, as shown in Figure 2, the input end of power inductive component is connected with a mu balanced circuit, and the output terminal of power inductive component is connected with a current amplifier; Cross-over connection has an output impedance to adjust resistance between first signal output part of each spoke pressure type sensor 5 and the secondary signal output terminal, and first signal output part of each spoke pressure type sensor 5 and secondary signal output terminal all are connected with an isolation resistance.During use, the outside can adopt the 24V power supply that mu balanced circuit and current amplifier are powered.
From the above, core of the present invention is connected in parallel four spoke pressure type sensors 5 exactly, by the standard signal of the exportable 4-20mA of current amplifier.
The condition of spoke pressure type sensor parallel running is: S1/R1=S2/R2=...=Sn/Rn(S is spoke pressure type transducer sensitivity, and R is the output impedance of spoke pressure type sensor)
Characteristics during four spoke pressure type sensor parallel runnings are as follows:
Suppose a certain load W, with the full scale be F, sensitivity be S, for bridge voltage be U a spoke pressure type sensor measurement it, be output as U1, then: U1=WSU/F.
If four spoke pressure type sensor parallel runnings are measured above same load W, in the ideal case, then can select full scale for use is the spoke pressure type sensor of (1/4) F, the sensitivity of supposing them also is S, also is U for bridge voltage, and then total output Un is: Un=U1
The arm resistance of supposing these four spoke pressure type sensors is R, and the output impedance after the parallel connection is Rn, then Rn=R/4.
The sensitivity S of spoke pressure type sensor and output impedance R can not be in full accord in actual manufacture process.So current amplifier input end add isolation resistance and output impedance and adjust resistance and make it satisfy the condition of work of spoke pressure type sensor parallel connection.Thereby reach balanced purpose of amplifying output.
As shown in figures 1 and 3, housing is connected and composed by cover plate 1, base plate 2, left swash plate 3, right swash plate 4, protecgulum (figure does not look) and bonnet (figure does not look), and is formed with the ccontaining cavity (figure does not mark) for ccontaining spoke pressure type sensor 5.Cover plate 1 and base plate 2 are writing board shape, the bottom surface of left side swash plate 3 and the bottom surface of right swash plate 4 are the plane, the end face of left side swash plate 3 and the end face of right swash plate 4 are an inclined-plane, the bottom surface of left side swash plate 3 and the bottom surface of right swash plate 4 all flush with the bottom surface of base plate 2, the top on described inclined-plane flushes with the end face of cover plate 1, and protecgulum or bonnet are provided with the electric connection terminal group.
Fit in the pressure-bearing post of spoke pressure type sensor 5 and the bottom surface of cover plate 1, the bottom of spoke pressure type sensor 5 is fixed on the base plate 2, and the input end of the output terminal of current amplifier, the power end of current amplifier and mu balanced circuit all is connected with the electric connection terminal group.Because the wheel tyre surface is wideer, four spoke pressure type sensors 5 are cross shape and distribute.The helicopter weighing measurement device of this structure is called dull and stereotyped helicopter weighing measurement device.
Wheel rolls on left swash plate 3 and right swash plate 4 for convenience, adopts ultra-thin spoke pressure type sensor, can effectively reduce the thickness (less than 30mm) of dull and stereotyped helicopter weighing measurement device.Be weight reduction, can adopt high-strength aluminum alloy material to make.
The measuring method of present embodiment is as follows:
Three electric connection terminal groups as the described dull and stereotyped helicopter weighing measurement device of present embodiment are connected with a single-chip microcomputer, and described single-chip microcomputer also connects a display screen;
Three wheels of helicopter are placed respectively on the cover plate 1 of three dull and stereotyped helicopter weighing measurement devices, and a wheel is corresponding with a dull and stereotyped helicopter weighing measurement device;
Utilize described single-chip microcomputer to gather the signal of dull and stereotyped helicopter weighing measurement device output, and obtain weight and the centre-of-gravity range of helicopter according to the calculated signals that collects, and weight and the centre-of-gravity range of helicopter shown on described display screen.
The dull and stereotyped helicopter weighing measurement device of present embodiment is used for rapid weighing and center of gravity estimation, and the open-air goods of suitable helicopter loads or installs additional temporarily, reequips.
Embodiment two
As shown in Figure 4 and Figure 5, present embodiment is that with the difference of embodiment one shell structure is different.Concrete, the housing of present embodiment is connected and composed by cover plate 6, base plate 7 and annular leg 8, and is formed with the ccontaining cavity for ccontaining spoke pressure type sensor 5.Cover plate 6 and base plate 7 are writing board shape, and the end face of cover plate 6 extends upward one and be used for the projection 61 chimeric with the strong point groove of the fuselage of helicopter, and general described projection 61 is rounded.Annular leg 8 is provided with the electric connection terminal group.
Fit in the pressure-bearing post of spoke pressure type sensor 5 and the bottom surface of cover plate 6, the bottom of spoke pressure type sensor 5 is fixed on the base plate 7, and the input end of the output terminal of current amplifier, the power end of current amplifier and mu balanced circuit all is connected with the electric connection terminal group.Four spoke pressure type sensors 5 are cross shape and distribute.The bottom surface of base plate 7 also is bolted with one for the threaded rod 9 of regulating the helicopter horizontal level, and it can be as lifting jack.The helicopter weighing measurement device of this structure is called cylindricality helicopter weighing measurement device.
The measuring method of present embodiment is as follows:
Four electric connection terminal groups as the described cylindricality helicopter of present embodiment weighing measurement device are connected with a single-chip microcomputer, and described single-chip microcomputer also connects a display screen;
As shown in Figure 6, four strong point grooves (F1, F2, F3, F4) of the fuselage of helicopter are chimeric with the projection of the cover plate of four cylindricality helicopter weighing measurement devices respectively, and a strong point groove is corresponding with a cylindricality helicopter weighing measurement device;
Utilize described single-chip microcomputer to gather the signal of cylindricality helicopter weighing measurement device output, and obtain weight and the centre of gravity place of helicopter according to the calculated signals that collects, and weight and the centre of gravity place of helicopter shown on described display screen.
Wherein, single-chip microcomputer is as follows according to the principle that the calculated signals that collects obtains the weight of helicopter and centre of gravity place:
L
1, L
2Be respectively forward and backward measurement point apart from the distance of reference field, L is that the rotor center line is apart from the distance of reference field; F
1, F
2, F
3, F
4Weight for four measuring point that sensor is surveyed.
G=F
1＋F
2＋F
3＋F
4
（F
1＋F
2）×L
1+（F
3＋F
4）×L
2=G×（L－X）
In the formula, G is weight, and X is distance of centre of gravity rotor distance between center line.
As long as know parameter L
1, L
2And behind the L, by the weight of cylindricality helicopter weighing measurement four measuring point that device is surveyed, just can calculate weight and the centre of gravity place of any type.
The cylindricality helicopter weighing measurement device of present embodiment is used for the accurate measurement of center of gravity and weighs, and suitable helicopter internal field, maintenance depot or manufacturer carry out helicopter and install additional, reequip.
In addition, the single-chip microcomputer of the various embodiments described above, display screen and relevant wire rod can be integrated in the door glove box, are convenient for carrying.Single-chip microcomputer and display screen can be made into integration module.
For a person skilled in the art, can make other various corresponding changes and distortion according to technical scheme described above and design, and these all changes and distortion should belong within the protection domain of claim of the present invention all.
Claims (8)
1. helicopter weighing measurement device, it is characterized in that, comprise a housing and four spoke pressure type sensors that are positioned at described housing, the pressure-bearing post of spoke pressure type sensor is used for the induction housing because of the stressed deformation quantity that produces, described four spoke pressure type sensors are connected in parallel, and form the power inductive component; The input end of power inductive component is connected with a mu balanced circuit, and the output terminal of power inductive component is connected with a current amplifier; Cross-over connection has an output impedance to adjust resistance between first signal output part of each spoke pressure type sensor and the secondary signal output terminal, and first signal output part of each spoke pressure type sensor and secondary signal output terminal all are connected with an isolation resistance.
2. helicopter weighing measurement device as claimed in claim 1 is characterized in that, described housing is connected and composed by cover plate, base plate, left swash plate, right swash plate, protecgulum and bonnet, and is formed with the ccontaining cavity for ccontaining spoke pressure type sensor; Cover plate and base plate are writing board shape, the bottom surface of left side swash plate and the bottom surface of right swash plate are the plane, the end face of left side swash plate and the end face of right swash plate are an inclined-plane, the bottom surface of left side swash plate and the bottom surface of right swash plate all flush with the bottom surface of base plate, the top on described inclined-plane flushes with the end face of cover plate, and protecgulum or bonnet are provided with the electric connection terminal group; Fit in the pressure-bearing post of spoke pressure type sensor and the bottom surface of cover plate, the bottom of spoke pressure type sensor is fixed on the base plate, and the input end of the output terminal of current amplifier, the power end of current amplifier and mu balanced circuit all is connected with the electric connection terminal group.
3. helicopter weighing measurement device as claimed in claim 2 is characterized in that, four spoke pressure type sensors are cross shape and distribute.
4. helicopter weighing measurement device as claimed in claim 1 is characterized in that, described housing is connected and composed by cover plate, base plate and annular leg, and is formed with the ccontaining cavity for ccontaining spoke pressure type sensor; Cover plate and base plate are writing board shape, and the end face of cover plate extends upward one and be used for the projection chimeric with the strong point groove of the fuselage of helicopter, and annular leg is provided with the electric connection terminal group; Fit in the pressure-bearing post of spoke pressure type sensor and the bottom surface of cover plate, the bottom of spoke pressure type sensor is fixed on the base plate, and the input end of the output terminal of current amplifier, the power end of current amplifier and mu balanced circuit all is connected with the electric connection terminal group.
5. helicopter weighing measurement device as claimed in claim 4 is characterized in that, four spoke pressure type sensors are cross shape and distribute.
6. helicopter weighing measurement device as claimed in claim 4 is characterized in that, the bottom surface of base plate also is bolted with one for the threaded rod of regulating the helicopter horizontal level.
7. helicopter center of gravity measurement method is characterized in that, may further comprise the steps:
Three electric connection terminal groups as claim 2 or 3 described helicopter weighing measurement devices are connected with a single-chip microcomputer, and described single-chip microcomputer also connects a display screen;
Three wheels of helicopter are placed respectively on the cover plate of three helicopter weighing measurement devices, and a wheel is corresponding with a helicopter weighing measurement device;
Utilize described single-chip microcomputer to gather the signal of helicopter weighing measurement device output, and obtain weight and the centre-of-gravity range of helicopter according to the calculated signals that collects, and weight and the centre-of-gravity range of helicopter shown on described display screen.
8. helicopter center of gravity measurement method is characterized in that, may further comprise the steps:
Four electric connection terminal groups as claim 4 or 5 or 6 described helicopter weighing measurement devices are connected with a single-chip microcomputer, and described single-chip microcomputer also connects a display screen;
Four strong point grooves of the fuselage of helicopter are chimeric with the projection of the cover plate of four helicopter weighing measurement devices respectively, and a strong point groove is corresponding with a helicopter weighing measurement device;
Utilize described single-chip microcomputer to gather the signal of helicopter weighing measurement device output, and obtain weight and the centre of gravity place of helicopter according to the calculated signals that collects, and weight and the centre of gravity place of helicopter shown on described display screen.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310187642.2A CN103278229B (en) | 2013-05-20 | 2013-05-20 | Helicopter weighing measurement device and helicopter center of gravity measurement method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310187642.2A CN103278229B (en) | 2013-05-20 | 2013-05-20 | Helicopter weighing measurement device and helicopter center of gravity measurement method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103278229A true CN103278229A (en) | 2013-09-04 |
| CN103278229B CN103278229B (en) | 2015-10-28 |
Family
ID=49060815
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310187642.2A Expired - Fee Related CN103278229B (en) | 2013-05-20 | 2013-05-20 | Helicopter weighing measurement device and helicopter center of gravity measurement method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103278229B (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104390687A (en) * | 2014-11-26 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Intelligent tester for weight and center of gravity of aircraft |
| CN104864906A (en) * | 2015-03-24 | 2015-08-26 | 深圳海油工程水下技术有限公司 | Offshore oil and gas subsea equipment weight measurement and center of gravity detection method |
| CN105444855A (en) * | 2015-11-28 | 2016-03-30 | 沈阳飞机工业（集团）有限公司 | Airplane weight gravity center measurement and adjustment device |
| CN106044566A (en) * | 2016-07-14 | 2016-10-26 | 中国华能集团清洁能源技术研究院有限公司 | Method for determining gravity center of article to be measured |
| CN106525211A (en) * | 2015-09-14 | 2017-03-22 | 波音公司 | Vehicle Occupant Sensor System and Method |
| CN108209873A (en) * | 2017-12-29 | 2018-06-29 | 深圳市宝康隆科技有限公司 | A kind of intelligence turntable |
| CN108489439A (en) * | 2018-07-05 | 2018-09-04 | 大连理工大学 | A kind of device and method of the tracking suspension structure center of rotation based on dynamic measurement centrifugal force |
| CN109323741A (en) * | 2018-11-01 | 2019-02-12 | 江苏省特种设备安全监督检验研究院 | The wheel load test method of crane |
| CN109632062A (en) * | 2018-12-29 | 2019-04-16 | 成都纵横大鹏无人机科技有限公司 | Weight and gravity center measurement device and measurement method |
| CN109855712A (en) * | 2019-01-09 | 2019-06-07 | 山东太古飞机工程有限公司 | Auxiliary mould during a kind of spacing in aircraft weighting technique is fixed |
| WO2022127143A1 (en) * | 2020-12-14 | 2022-06-23 | 海南聚能科技创新研究院有限公司 | Nitric oxide concentration measurement apparatus and nitric oxide concentration measurement instrument |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3638477A (en) * | 1969-02-13 | 1972-02-01 | Bevauge Ag | Device for determining the center of gravity and/or the weight of airplanes |
| CN2041810U (en) * | 1988-12-09 | 1989-07-26 | 关刃 | Portable electric scale |
| GB2268138A (en) * | 1981-06-20 | 1994-01-05 | Rolls Royce | Multi-engined VTOL aircraft |
| CN2713448Y (en) * | 2004-03-04 | 2005-07-27 | 甘肃省科学院传感技术研究所 | Weight and gravity center measurement device for plane |
| CN202562615U (en) * | 2012-03-21 | 2012-11-28 | 利辛县衡器电子有限责任公司 | Multipurpose analog terminal box |
-
2013
- 2013-05-20 CN CN201310187642.2A patent/CN103278229B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3638477A (en) * | 1969-02-13 | 1972-02-01 | Bevauge Ag | Device for determining the center of gravity and/or the weight of airplanes |
| GB2268138A (en) * | 1981-06-20 | 1994-01-05 | Rolls Royce | Multi-engined VTOL aircraft |
| CN2041810U (en) * | 1988-12-09 | 1989-07-26 | 关刃 | Portable electric scale |
| CN2713448Y (en) * | 2004-03-04 | 2005-07-27 | 甘肃省科学院传感技术研究所 | Weight and gravity center measurement device for plane |
| CN202562615U (en) * | 2012-03-21 | 2012-11-28 | 利辛县衡器电子有限责任公司 | Multipurpose analog terminal box |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104390687A (en) * | 2014-11-26 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Intelligent tester for weight and center of gravity of aircraft |
| CN104864906A (en) * | 2015-03-24 | 2015-08-26 | 深圳海油工程水下技术有限公司 | Offshore oil and gas subsea equipment weight measurement and center of gravity detection method |
| CN106525211A (en) * | 2015-09-14 | 2017-03-22 | 波音公司 | Vehicle Occupant Sensor System and Method |
| CN105444855A (en) * | 2015-11-28 | 2016-03-30 | 沈阳飞机工业（集团）有限公司 | Airplane weight gravity center measurement and adjustment device |
| CN106044566A (en) * | 2016-07-14 | 2016-10-26 | 中国华能集团清洁能源技术研究院有限公司 | Method for determining gravity center of article to be measured |
| CN108209873A (en) * | 2017-12-29 | 2018-06-29 | 深圳市宝康隆科技有限公司 | A kind of intelligence turntable |
| CN108489439A (en) * | 2018-07-05 | 2018-09-04 | 大连理工大学 | A kind of device and method of the tracking suspension structure center of rotation based on dynamic measurement centrifugal force |
| CN109323741A (en) * | 2018-11-01 | 2019-02-12 | 江苏省特种设备安全监督检验研究院 | The wheel load test method of crane |
| CN109632062A (en) * | 2018-12-29 | 2019-04-16 | 成都纵横大鹏无人机科技有限公司 | Weight and gravity center measurement device and measurement method |
| CN109632062B (en) * | 2018-12-29 | 2020-09-22 | 成都纵横大鹏无人机科技有限公司 | Weight and gravity center measuring device and measuring method |
| CN109855712A (en) * | 2019-01-09 | 2019-06-07 | 山东太古飞机工程有限公司 | Auxiliary mould during a kind of spacing in aircraft weighting technique is fixed |
| CN109855712B (en) * | 2019-01-09 | 2023-09-01 | 山东太古飞机工程有限公司 | Distance centering auxiliary tool for airplane weighing process |
| WO2022127143A1 (en) * | 2020-12-14 | 2022-06-23 | 海南聚能科技创新研究院有限公司 | Nitric oxide concentration measurement apparatus and nitric oxide concentration measurement instrument |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103278229B (en) | 2015-10-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103278229B (en) | Helicopter weighing measurement device and helicopter center of gravity measurement method | |
| CN102169040B (en) | Device for measuring quality center of mass by composite range sensor in cross-measuring range | |
| CN105910755B (en) | Calibration device suitable for small thrust measurement system electromagnetism power application ware | |
| CN201653607U (en) | Axial force measuring sensor | |
| CN105136391B (en) | A kind of method and system of survey aircraft in ground stress point distance | |
| CN105043518A (en) | Dynamic-static double-output rail weighbridge | |
| CN201707261U (en) | Combined multifunctional flat plate load-bearing tester | |
| CN105628280A (en) | Integrated transmission device strain gage force measurement supporting seat for armored vehicle | |
| CN202869717U (en) | Absolute stress detection apparatus for prestressed concrete bridge | |
| CN204405174U (en) | A kind of proving installation of LOAD CELLS | |
| CN105674956A (en) | Tower body gradient measurement system for wind turbine generator set | |
| CN202547742U (en) | Piezoresistance sensor based electronic scale | |
| CN206330658U (en) | A kind of simple high-precision electronic scale | |
| CN208872438U (en) | A kind of strain wheel load and real-time heavy condition measuring system | |
| CN208282973U (en) | The vertical load power system of high-precision pivoted arm force-measuring framework tests structure | |
| CN102393540A (en) | Magnetic suspension rainfall intensity recorder | |
| CN202938849U (en) | Testing instrument for synchronously testing polished rod load and reducer casing torque of pumping unit | |
| CN210128761U (en) | Large electronic truck scale weighing device | |
| CN102998046B (en) | Method and device for transverse tension measuring of capacitive steel wire rope | |
| CN213515963U (en) | Intelligent precision electronic balance | |
| CN204027674U (en) | Intelligent track weighing system based on fiber-optic grating sensor | |
| CN208520454U (en) | Bar shaped stress-type dynamic vehicle weighing device | |
| CN108931324A (en) | A kind of strain wheel load and real-time heavy condition measuring system | |
| CN206920051U (en) | Pressure sensor device | |
| CN208109243U (en) | A kind of road vehicle dynamic weigher |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151028 Termination date: 20200520 |