CN1456871A - Six-dimensional parallel balance - Google Patents
Six-dimensional parallel balance Download PDFInfo
- Publication number
- CN1456871A CN1456871A CN 03131866 CN03131866A CN1456871A CN 1456871 A CN1456871 A CN 1456871A CN 03131866 CN03131866 CN 03131866 CN 03131866 A CN03131866 A CN 03131866A CN 1456871 A CN1456871 A CN 1456871A
- Authority
- CN
- China
- Prior art keywords
- balance
- connecting rod
- lower platform
- mounting plate
- upper mounting
- 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.)
- Pending
Links
- 230000007246 mechanism Effects 0.000 description 8
- 238000005259 measurement Methods 0.000 description 6
- 238000012360 testing method Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 4
- 230000035807 sensation Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 230000035945 sensitivity Effects 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Landscapes
- Force Measurement Appropriate To Specific Purposes (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The balance has the space-parallel closed loop structure formed by connecting up platform of main bearing rod and down platform set on wind-tunnel with ball-joint set on periphery of up and down platforms through connecting rod set on with force sensing element, of which the connecting rod is formed by connecting the up connecting rod and the down connecting rod with nuts.
Description
Technical field
Six-dimensional parallel balance of the present invention belongs to wind tunnel test force-moment sensor and makes the field, particularly a kind of six-dimensional space force-moment Parallel Wind Tunnel Balance mechanism.
Background technology
Wind-tunnel balance is the most important measurement mechanism of wind tunnel test, and the achievement highly visible that the Aero-Space cause of China obtains is inseparable with wind-tunnel balance.In the balance of wind tunnel force measurement test, mainly contain mechanical balance, strain balance, piezoelectric balance, magnetic suspention balance and various extraordinary day equality.But they can not adapt to the paces of Aero-Space career development, as complex structure, the power transfer route is long, precision is low, bandwidth range is narrow etc., model test to models such as high speed, heavy duty, flutters has produced unnecessary restriction, so wind-tunnel balance still needs constantly to weed out the old and bring forth the new, with adaptive technique development and application demand, with this understanding, parallel balance arises at the historic moment, it is knowledge-intensive and technology-intensive electromechanical integration high-tech product, is the intersection of multidisciplinary theories such as stamp identification machine, computing machine, kybernetics, precision measurement, multi-body system.
Parallel institution just occurred in 1949, was that a people who is high husband (Gough) designs and detects tire, and in the sixties, this mechanism is excavated again, and reason is because this mechanism is more practical on flight simulator.In nineteen sixty-five, this people of Stewart (Stewart) utilizes the parallel institution of 6DOF to make a flight simulator, and this mechanism is called Stewart (Stewart) mechanism.Therefore at the beginning, parallel institution refers to the Stewart (Stewart) or high husband one Stewart (Gough-Stewart) mechanism of 6DOF more.Begin to become the research focus eighties, along with deepening continuously and tangible advantage that parallel institution had of theoretical research, parallel institution has been applied to fields such as robot, lathe, locating device and measurement mechanism.1989, Kai Er (Kerr) proposed parallel institution is applied to sextuple force-moment sensor the earliest; CharlesC etc. have analyzed its basic theories; A.Romiti and M.Sorli have studied sextuple power measurement in robot assembling hand; M.Sorli and N.Zhmud have provided the application example that sextuple power is measured in robot assembling hand.
At home, traditional in recent years wind tunnel test balance does not have breakthrough, and some extraordinary balance has certain development; At application number is to disclose " parallel decoupling structure six-dimensional force and torque sensor " and " a kind of have sextuple power of elastic hinge and torque sensor " in 99119320 and 99102421 patent documents.The weak point of parallel institution has: position normal solution complexity, work space be little, have unusual morpheme etc., the present invention introduces the wind tunnel test balance with parallel institution, can avoid its shortcoming, make full use of the intrinsic advantage such as rigidity height, precision height of parallel institution, solve the problem of traditional wind-tunnel balance.
Summary of the invention
The object of the invention is to overcome the weak point of existing type balance, and a kind of Parallel Wind Tunnel Balance that can detect three-dimensional all one's effort information simultaneously is provided, and its sensor can be strain-type, piezoelectric type, condenser type etc.Have simple in structure, cost is low, the degree of modularity is high, assembly process process is good, calibration is simple, detection is easy to maintenance, according to application demand, can realize characteristics such as high precision, high rigidity, high sensitivity, high dynamic response, high linearity.
Technical solution of the present invention is as follows:
The formation of six-dimensional parallel balance of the present invention is, the upper mounting plate that main strut is housed on it links to each other with ball pivot on being loaded on the upper and lower platform circumference of upper mounting plate circumference by long connecting rod such as the six roots of sensation with lower platform on being fixed in wind-tunnel wall, constitutes the space parallel closed loop structure.The last connecting rod and the lower link of every connecting rod interconnect by nut, all are fixed with force sensing element on the connecting rod.
Tested model is loaded on the main strut of upper mounting plate, and the six-dimensional space that utilizes little distortion of force sensing element on the every connecting rod or charge variation amount to measure tested model is stressed.
The present invention compared with prior art has the following advantages:
1. parallel balance of the present invention is compared with traditional balance, has high precision, high rigidity, high sensitivity, high dynamic response, bandwidth height, high linearity etc.
2. six-dimensional parallel balance of the present invention has simple in structure, and identical parts quantity is few, and is easily manufactured, and cost is low.
3. six-dimensional parallel balance degree of modularity height of the present invention is convenient to realize seriation, universalization, standardization, is easy to realize wide range, and it is good to make assembly process process, is convenient to detect and maintenance.
4. six-dimensional parallel balance of the present invention has that the position is counter separates simply, and calibration is convenient, disturbs little.
5. six-dimensional parallel balance sensor of the present invention can be strain-type, piezoelectric type, condenser type etc., can add overload protection arrangement easily, strengthens the impact resistance of balance.
6. six-dimensional parallel balance of the present invention can detect three-dimensional all one's effort information simultaneously, has wide practical use and using value in the occasion that needs the sextuple power of measurement space.
Description of drawings:
Fig. 1 is a six-dimensional parallel balance structural representation of the present invention;
Fig. 2 is the connecting rod of six-dimensional parallel balance of the present invention and the synoptic diagram of several connected modes of last lower platform;
Punctuate title among Fig. 1: 1. tested model, 2. go up connecting rod, 3. with 9 nuts, the 4. quick part of power, 5. with 10 ball pivots, 6. wind-tunnel wall, 7. lower platform, 8. lower link, 11. upper mounting plates, 12. main struts
Figure a among Fig. 2 is several connected modes of upper mounting plate radius less than the lower platform radius to scheming b, wherein scheme a, 3～3 connected modes, figure b, 3-6 connected mode, figure c, 6-3 connected mode, figure d, 6-6 connected mode, figure e is several connected modes of upper mounting plate radius greater than the lower platform radius to scheming h, wherein scheme e, 3-3 connected mode, figure f, 3-6 connected mode, figure g, 6-3 connected mode, figure h .6-6 connected mode.
Embodiment
As shown in Figure 1, the concrete composition of six-dimensional parallel balance of the present invention is, the upper mounting plate 11 that main strut 12 is housed on it links to each other with ball pivot on being loaded on upper and lower platform circumference by the connecting rod of six roots of sensation equal length with lower platform 7 on placing wind-tunnel wall 6, constitutes the space parallel closed loop structure.Every connecting rod is formed by connecting by nut 3 by last connecting rod 2 and lower link 8, and force sensing element 4 is fixed on the every connecting rod.Force sensing element 4 can be piezoelectric ceramics force sensing element, capacitive force photosensitive elements, rectangle strain-type force sensing element and belt strain-type force sensing element etc.Tested model 1 (as model of an airplane etc.) is installed on the main strut 12 of upper mounting plate 11.Utilize the force sensing element on the every connecting rod to experience the stressed of connecting rod, cause piezoelectric type, capacitive force photosensitive elements change in charge or cause little distortion of strain-type force sensing element, realize the six-dimensional space power of tested model 1 (as aircraft) is measured.
Upper mounting plate of the present invention and lower platform have several connected modes as shown in Figure 2.Wherein scheming a is the four kind connected modes of upper mounting plate less than lower platform to scheming d, and figure e is to scheme h be upper mounting plate greater than lower platform and figure a to scheming the corresponding four kinds of connected modes of d.As scheme a with figure e be the 3-3 connected mode, three ball pivots are installed with all dividing equally respectively on the promptly upper and lower platform circumference, by six roots of sensation equal length connecting rod three ball pivots on the upper and lower platform circumference are coupled together accordingly, so abbreviate the 3-3 connected mode as.Figure b is that three ball pivots are installed on the upper mounting plate circumference with dividing equally with figure f, and 6 ball pivots of installation on the lower platform circumference, the ball pivot that to go up on the lower platform circumference by six roots of sensation equal length connecting rod couples together, so be called the 3-6 connected mode, analogize therewith, figure c and figure g are the 6-3 connected mode, and figure d and figure h are the 6-6 connected mode.
Claims (2)
1. a six-dimensional parallel balance comprises upper mounting plate, lower platform, it is characterized in that the upper mounting plate that main strut is housed on it is interconnected to the space parallel closed loop structure with placing the lower platform on the wind-tunnel wall by connecting rod that force sensing element is housed on it and the ball pivot that is loaded on the upper and lower platform circumference of upper mounting plate circumference.
2. according to the described six-dimensional parallel balance of claim 1, it is characterized in that connecting rod is linked to be by nut by last connecting rod and lower link and forms.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 03131866 CN1456871A (en) | 2003-06-12 | 2003-06-12 | Six-dimensional parallel balance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 03131866 CN1456871A (en) | 2003-06-12 | 2003-06-12 | Six-dimensional parallel balance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1456871A true CN1456871A (en) | 2003-11-19 |
Family
ID=29411774
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 03131866 Pending CN1456871A (en) | 2003-06-12 | 2003-06-12 | Six-dimensional parallel balance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1456871A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100494937C (en) * | 2007-06-12 | 2009-06-03 | 南京航空航天大学 | Large strain ratio six-dimensional parallel sensor |
| ES2369297A1 (en) * | 2011-05-24 | 2011-11-29 | Universidad Politécnica de Madrid | Balance for aerodynamic tunnel. (Machine-translation by Google Translate, not legally binding) |
| CN102865993A (en) * | 2012-09-24 | 2013-01-09 | 西北工业大学 | Recyclable airplane model experimental facility capable of changing appearance and parameter |
| CN104849016A (en) * | 2015-05-04 | 2015-08-19 | 中国科学院力学研究所 | Microscale wind-tunnel balance and test method thereof |
| CN105021370A (en) * | 2015-07-30 | 2015-11-04 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low speed high Reynolds number wind tunnel semi model force balance and force-measuring method |
| CN108593058A (en) * | 2018-05-02 | 2018-09-28 | 北京航空航天大学 | Air drag tests balance |
| CN108760130A (en) * | 2018-07-13 | 2018-11-06 | 浙江睿思自动化技术有限公司 | Six COMPONENT BALANCEs |
| CN111307399A (en) * | 2020-03-31 | 2020-06-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Train wind tunnel test attitude fine adjustment method |
| CN112146910A (en) * | 2020-09-27 | 2020-12-29 | 清华大学 | Simulation device |
-
2003
- 2003-06-12 CN CN 03131866 patent/CN1456871A/en active Pending
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100494937C (en) * | 2007-06-12 | 2009-06-03 | 南京航空航天大学 | Large strain ratio six-dimensional parallel sensor |
| ES2369297A1 (en) * | 2011-05-24 | 2011-11-29 | Universidad Politécnica de Madrid | Balance for aerodynamic tunnel. (Machine-translation by Google Translate, not legally binding) |
| CN102865993A (en) * | 2012-09-24 | 2013-01-09 | 西北工业大学 | Recyclable airplane model experimental facility capable of changing appearance and parameter |
| CN102865993B (en) * | 2012-09-24 | 2014-10-15 | 西北工业大学 | Recyclable airplane model experimental facility capable of changing appearance and parameter |
| CN104849016B (en) * | 2015-05-04 | 2017-05-24 | 中国科学院力学研究所 | Microscale wind-tunnel balance and test method thereof |
| CN104849016A (en) * | 2015-05-04 | 2015-08-19 | 中国科学院力学研究所 | Microscale wind-tunnel balance and test method thereof |
| CN105021370A (en) * | 2015-07-30 | 2015-11-04 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low speed high Reynolds number wind tunnel semi model force balance and force-measuring method |
| CN105021370B (en) * | 2015-07-30 | 2018-01-19 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low speed high Reynola number wind tunnel half model force balance and force measuring method |
| CN108593058A (en) * | 2018-05-02 | 2018-09-28 | 北京航空航天大学 | Air drag tests balance |
| CN108593058B (en) * | 2018-05-02 | 2019-10-08 | 北京航空航天大学 | Air drag tests balance |
| US11300478B2 (en) | 2018-05-02 | 2022-04-12 | Beihang University | Balance for air resistance testing |
| CN108760130A (en) * | 2018-07-13 | 2018-11-06 | 浙江睿思自动化技术有限公司 | Six COMPONENT BALANCEs |
| CN111307399A (en) * | 2020-03-31 | 2020-06-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Train wind tunnel test attitude fine adjustment method |
| CN112146910A (en) * | 2020-09-27 | 2020-12-29 | 清华大学 | Simulation device |
| CN112146910B (en) * | 2020-09-27 | 2021-08-10 | 清华大学 | Simulation device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102169040B (en) | Device for measuring quality center of mass by composite range sensor in cross-measuring range | |
| CN105196294B (en) | Reconfigurable mechanical arm decentralized control system and control method adopting position measuring | |
| CN101835974B (en) | Method for determining fatigue damage in a power train of a wind turbine | |
| CN107391858B (en) | Method for obtaining static aeroelastic deformation influence quantity of wind tunnel model | |
| CN202994470U (en) | Dynamic performance testing system for pilotless aircraft | |
| CN1456871A (en) | Six-dimensional parallel balance | |
| CN101210850A (en) | Multi-component force sensor | |
| CN201803831U (en) | Device for measuring inertia moment parameters of automobile engine assembly | |
| CN102087153A (en) | Wheel spoke type fault-tolerant six-dimension force sensor with parallel structure | |
| CN201331403Y (en) | Moment rigidity tester for hub bearing unit | |
| CN109141933A (en) | A kind of hub-type sensor dynamometric system | |
| CN201242478Y (en) | Three-dimensional small range force sensor | |
| CN101881679A (en) | Airplane steering wheel multi-axis force measurement component and measurement method thereof | |
| CN103278399A (en) | Experimental device for testing elasticity modulus G of material | |
| CN104897385B (en) | Efp dedicated test circuit system | |
| CN106940243A (en) | A kind of six component measurement balances and model for wind tunnel experiment | |
| Qiao et al. | Vehicle overload detection system based on magnetoresistance sensor | |
| CN101881651A (en) | Small-size portable high-accuracy disturbance measuring system | |
| CN113091981A (en) | Sensor with pretightening force and measuring method | |
| CN107063519B (en) | A kind of adjustable piezoelectric type hexa-dimensional force sensor of load sharing | |
| CN101329207A (en) | Six-dimensional force sensor of integral pre-tightening double-layer top and bottom asymmetry seven-rod parallel connection structure | |
| CN112948999B (en) | Joint reliability verification method for space robot | |
| CN111380690B (en) | Piston engine output thrust measurer and measuring method | |
| CN210426949U (en) | Continuous measurement system of direct-current temporary-impulse type transonic wind tunnel | |
| CN201697776U (en) | Unidirectional force measurement device with disturbance resistance |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |