CN102636139B  Sixdisplacementsensor dynamic measuring method of space sixdegreeoffreedom movement  Google Patents
Sixdisplacementsensor dynamic measuring method of space sixdegreeoffreedom movement Download PDFInfo
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 CN102636139B CN102636139B CN201210106028.4A CN201210106028A CN102636139B CN 102636139 B CN102636139 B CN 102636139B CN 201210106028 A CN201210106028 A CN 201210106028A CN 102636139 B CN102636139 B CN 102636139B
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Abstract
Description
Technical field
The present invention relates to six displacement transducer dynamic measuring methods of a kind of space sixfreedom motion, utilize six displacement transducer parallel connections moving object to be carried out to the kinetic measurement of space sixfreedom motion.Space sixfreedom motion comprises: threedegreeoffreedom motion displacement x (t), y (t), z (t) and threedegreeoffreedom motion angle θ x (t), θ y (t), θ z (t), be convertible into movement velocity, acceleration of motion, motion angular velocity, motion angular acceleration after moving displacement and angle differential.
Background technology
Existing industry, the military measurement to object space motion require more and more higher, and environment becomes increasingly complex, and utilize original metering system, can not meet the requirements such as measuring accuracy, environment, frequency, coupling.When carrying out rocket projectile flight test, a series of reasons such as the high thrust, thump, High Temperature High Pressure, blast that transmitting produces make emitter in rugged environment, emitter affects its flight path, accuracy at target and closeness to the initial disturbance of rocket projectile (guided missile) transmitting, even causes the fighting capacity of whole army to decline.This just need to have a kind of measuring mechanism that can adapt under particular surroundings, can accurately measure the sixfreedom degree amount of movement of measurement point, need to each principal element carry out dynamic test and research to the initial disturbance in emission process, especially need to adapt to measuring method and the device of omnidistance Measurement accuracy emitter space sixfreedom motion under particular surroundings (move axially, translation, heave, pitching, driftage, rolling).
Precision is one of main standard of weighing measurement mechanism or method, but at present as vibration acceleration sensor or vibrating speed sensors are directly installed on emitter, through being integrated into speed or displacement, because range, frequency response and integral error etc. cause error larger; Measurement based on machine vision is subject to air refraction fluctuation and the smog dust of high temperature blast to make the method measuring error large, and the flue dust can not adapt to launch time, hot environment, can not be used even completely; Adopt threeaxis gyroscope measurement space three axis angular rates, be integrated into angular displacement, the method can not be measured threeshaft displacement, and because range, frequency response and integral error etc. cause, error is larger etc. causes error larger.
In other engineering application of industry, military affairs and space flight and aviation, the method of measuring object of which movement both at home and abroad at present can not be measured the sixfreedom motion rule of moving object simultaneously, integral error is large, measures complicated precision low, can not accurately obtain the sixfreedom motion of moving object simultaneously.
Summary of the invention
Technical matters to be solved by this invention is to provide six displacement transducer dynamic measuring methods of a kind of space sixfreedom motion, can carry out space sixfreedom motion highacruracy survey to moving object simultaneously.Space sixfreedom motion comprises: threedegreeoffreedom motion displacement x (t), y (t), z (t) and threedegreeoffreedom motion angle θ x (t), θ y (t), θ z (t), be convertible into movement velocity, acceleration of motion, motion angular velocity, motion angular acceleration after moving displacement and angle differential.
Technical scheme of the present invention is as follows: six displacement transducer dynamic measuring methods of a kind of space sixfreedom motion, is characterized in that comprising the following steps:
Six displacement transducer dynamic measuring methods of space sixfreedom motion, is characterized in that comprising the following steps:
1) build six displacement transducers measuring mechanism in parallel:
The six displacement transducers measuring mechanism in parallel of building comprises upper mounting plate, lower platform and six staysupported type displacement sensors, on upper mounting plate and lower platform, respectively there are six mounting points for staysupported type displacement sensor is installed, six mounting points in identical platform are on a circle or the place of hexagonal six angles, six mounting points of upper mounting plate are corresponding one by one with six mounting points of lower platform, between the mounting points of the mounting points of upper mounting plate and corresponding lower platform according to shortest distance principle connecting stay wire formula displacement transducer, six staysupported type displacement sensor touchless, described lower platform is fixed on pedestal, on upper mounting plate, fix testee, and move with testee,
2) set up coordinate system:
On upper mounting plate, set up moving coordinate system o'x'y'z', on lower platform, set up quiet coordinate system oxyz, A _{i}, B _{i}be respectively the contact point of six staysupported type displacement sensors in upper mounting plate and lower platform, A _{i}, B _{i}vector representation in rectangular coordinate system oxyz is respectively A (A _{ix}, A _{iy}, A _{iz}), B (B _{ix}, B _{iy}, B _{iz}), l _{i}represent A _{i}b _{i}between displacement, in solution procedure, the six degree of freedom x (t) of moving object, y (t), z (t), θ x (t), θ y (t), θ z (t) are expressed as x, y, z, θ _{x}, θ _{y}, θ _{z}, be convenient to calculate;
3) inverse position solution:
In the time that upper mounting plate changes, obtain the coordinate figure A of this stylish point according to the relation of plane and Planepoint,
A＝T*A′ _{i}+P
T is the direction cosine matrix of upper mounting plate attitude, A ' _{i}for A _{i}point is in the position vector of moving coordinate system, and P is that moving coordinate system on upper mounting plate is with respect to the displacement vector in the quiet coordinate system of lower platform;
If the initial length between the corresponding mounting points of upper and lower two platforms is l _{i0}, i=1,2 ... 6; Line between the each corresponding mounting points of upper and lower two platform is as six branches, and the realtime measurement length of each branch can be expressed as the function of tested moving object location parameter:
In formula, A _{ix}, A _{iy}, A _{iz}for the position of termination contact on staysupported type displacement sensor in position fixing system, B _{ix}, B _{iy}, B _{iz}for the position of termination contact under staysupported type displacement sensor in position fixing system, because tested moving object is the length variations amount that staysupported type displacement sensor records at the pose of upper mounting plate against solution:
Δl _{i}＝l _{i}l _{i0}＝g _{i}(x,y,z,θ _{x},θ _{y},θ _{z})l _{i0}???(1.3)
By six pose parameter substitution formulas (1.3) of tested moving object, can obtain the length variations amount that while measuring testee, staysupported type displacement sensor records, then according to formula l _{i0}=l _{i}Δ l _{i}adjust again the distance between upper lower platform;
4) position normal solution
Just solving an equation by the contrary variation of solving an equation
l ^{2}＝(AB _{i})(AB _{i}) ^{T}
B _{i}for the coordinate of staysupported type displacement sensor lower extreme point in the quiet coordinate system of lower platform, l _{i}the length recording for staysupported type displacement sensor
Order
First make initial point x, y, z, θ _{x}, θ _{y}, θ _{z}=(0,0,0,0,0,0); By f _{i}(A _{i}) (i=1,2 ... 6) at A _{i}near carry out Taylor expansion, and get its linear segment:
Formula (1.4) can be regarded as with A _{i}for the system of linear equations of unknown number, its Jacobin coefficient matrix is:
Ask the inverse matrix of Jacobi matrix by Applying Elementary Row Operations, be converted into plusminus and the multiplying of asking matrix so completely; Wherein (x _{1}, x _{2}, x _{3}, x _{4}, x _{5}, x _{6})=(x, y, z, θ _{x}, θ _{y}, θ _{z}); Separate the athletic posture x that Nonlinear System of Equations (1.4) just can obtain testee, y, z, θ _{x}, θ _{y}, θ _{z}.
For simplified structure and algorithm, described upper mounting plate and lower platform are regular hexagon or circle, upper mounting plate be positioned at lower platform directly over.
The invention has the beneficial effects as follows:
1) can directly measure the characteristics of motion of tested moving object sixfreedom degree, measuring accuracy is high simultaneously.
2) algorithm is easy to realize, and reliability is strong.
3) applied range, may be used in the national defence major fields such as parallel machine, flight simulator, model in wind tunnel device, space articulation equipment.
Brief description of the drawings
Fig. 1 is the structural representation of six displacement parallel institutions in the present invention.
The schematic diagram of the coordinate system that Fig. 2 sets up for the present invention.
Embodiment
Below in conjunction with drawings and Examples, the invention will be further described:
Six displacement transducer dynamic measuring methods of space sixfreedom motion, comprise the following steps:
1) build six displacement transducers measuring mechanism in parallel:
As shown in Figure 1, the six displacement transducers measuring mechanism in parallel of building is made up of upper mounting plate 1, lower platform 3 and six staysupported type displacement sensors 2.The shape of upper and lower platform 1,3 can be set arbitrarily as required, is preferably circle or regular hexagon.On upper mounting plate 1 and lower platform 3, respectively have six mounting points for staysupported type displacement sensor 2 is installed, six mounting points in identical platform are on a circle or the place of hexagonal six angles.Six mounting points of upper mounting plate 1 are corresponding one by one with six mounting points of lower platform 3, between the mounting points of the mounting points of upper mounting plate 1 and corresponding lower platform 3 according to shortest distance principle connecting stay wire formula displacement transducer 2, six staysupported type displacement sensor 2 touchless, when measurement, lower platform 3 is fixed on pedestal, on upper mounting plate 1, fix testee, and move with testee.If on testee or fixed pedestal, can determine respectively that six points are for the installation of staysupported type displacement sensor, can cancel upper mounting plate or lower platform directly by installation of sensors on pedestal and testee (or two platforms are integrated on pedestal and testee).
2) set up coordinate system:
On upper mounting plate, set up moving coordinate system o'x'y'z', on lower platform, set up quiet coordinate system oxyz, A _{i}, B _{i}be respectively the contact point of six staysupported type displacement sensors in upper mounting plate and lower platform, i=1,2 ... 6.A _{i}, B _{i}vector representation in rectangular coordinate system oxyz is respectively A (A _{ix}, A _{iy}, A _{iz}), B (B _{ix}, B _{iy}, B _{iz}), l _{i}represent A _{i}b _{i}between displacement.In solution procedure, the six degree of freedom x (t) of moving object, y (t), z (t), θ x (t), θ y (t), θ z (t) are expressed as x, y, z, θ _{x}, θ _{y}, θ _{z}, be convenient to calculate.
3) inverse position solution:
In the time that testee moves, the position of upper mounting plate and state can change.If given locus and the attitude of upper mounting plate, is respectively x, y, z, θ _{x}, θ _{y}, θ _{z}, the length variations of asking each staysupported type displacement sensor to record, is inverse position solution.In the time that upper mounting plate changes, can obtain according to the relation of plane and Planepoint the coordinate figure A of this stylish point.
A＝T*A′ _{i}+P
T is the direction cosine matrix of upper mounting plate attitude, A ' _{i}for A _{i}point is in the position vector of moving coordinate system, and P is that moving coordinate system on upper mounting plate is with respect to the displacement vector in the quiet coordinate system of lower platform.
If the initial length between the corresponding mounting points of upper and lower two platforms is l _{i0}, i=1,2 ... 6; Line between each corresponding mounting points is as six branches, and the realtime measurement length of each branch can be expressed as the function of tested moving object location parameter:
In formula, A _{ix}, A _{iy}, A _{iz}for the position of termination contact on staysupported type displacement sensor in position fixing system, B _{ix}, B _{iy}, B _{iz}for the position of termination contact under staysupported type displacement sensor in position fixing system.Because tested moving object is the length variations amount that staysupported type displacement sensor records at the pose of upper mounting plate against solution:
Δl _{i}＝l _{i}l _{i0}＝g _{i}(x,y,z,θ _{x},θ _{y},θ _{z})l _{i0}???(1.3)
By six pose parameter substitution formulas (1.3) of tested moving object, can obtain the length variations amount that while measuring testee, staysupported type displacement sensor records, then according to formula l _{i0}=l _{i}Δ l _{i}adjust again the distance between upper lower platform.
4) position normal solution
Position normal solution adopts Newton iteration method, and its basic thought is nonlinear equation F (x)=0 to be converted into certain linear equation solve.Of the present invention just solving an equation can be by the contrary variation of solving an equation.
l ^{2}＝(AB _{i})(AB _{i}) ^{T}
B _{i}for the coordinate of staysupported type displacement sensor lower extreme point in the quiet coordinate system of lower platform.L _{i}for six mounting points of upper mounting plate are from the distance (being the length that staysupported type displacement sensor records) of six mounting points of lower platform
Order
First make initial point x, y, z, θ _{x}, θ _{y}, θ _{z}=(0,0,0,0,0,0).By f _{i}(A _{i}) (i=1,2 ... 6) at A _{i}near carry out Taylor expansion.And get its linear segment, obtain:
Formula (1.4) can be regarded as with A _{i}for the system of linear equations of unknown number, its Jacobin coefficient matrix is:
Ask the inverse matrix of Jacobi matrix by Applying Elementary Row Operations, be converted into plusminus and the multiplying of asking matrix so completely.Wherein (x _{1}, x _{2}, x _{3}, x _{4}, x _{5}, x _{6})=(x, y, z, θ _{x}, θ _{y}, θ _{z}).Separate the athletic posture x that Nonlinear System of Equations (1.4) just can obtain testee, y, z, θ _{x}, θ _{y}, θ _{z}.
The present invention is according to the preliminary motion of moving object, utilize Inverse Kinematics Solution to obtain the length of displacement transducer, adjust upper mounting plate and the distance value of lower platform or the length of displacement transducer, build parallel institution formula six displacement transducers, utilize dynamic measuring method, according to the normal solution computing method of displacement transducer, obtain the sixfreedom motion rule of moving object.
5) measuring mechanism precision analysis:
If the precision of measuring mechanism of the present invention is L=L _{1}× L _{2}, wherein, L _{1}for the sensitivity (unit is mv/um) of staysupported type displacement sensor, L _{2}for the space geometry sensitivity (unit is um/um) of measuring mechanism, under normal circumstances, the sensitivity of six staysupported type displacement sensors is identical, L now _{1}also be the sensitivity of single displacement transducer.
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CN103486989B (en) *  20130916  20160504  南京航空航天大学  Staysupported spatial position measuring mechanism and measuring method 
CN103934823B (en) *  20140428  20150930  哈尔滨工程大学  A kind of 6PTRT type parallel robot with self calibrating function 
CN104390612B (en) *  20140708  20170308  西安电子科技大学  Sixdegreeoffreedom parallel robot benchmark pose scaling method for Stewart platform configuration 
CN104236629B (en) *  20140917  20170118  上海大学  Pull wire type measuring system and method applied to spatial location accuracy and track measurement of industrial robot 
CN104493808B (en) *  20141126  20170104  上海大学  Moving component spatial pose precision and track staysupported measure system and method 
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CN106643382B (en) *  20161128  20191231  山东科技大学  Relative full pose detection device and application thereof 
CN106767781A (en) *  20161129  20170531  中国地质大学（武汉）  The sixfreedom motion track data processing method of drop test preburied sensor 
CN108253996B (en) *  20161228  20200207  比亚迪股份有限公司  Guy wire code measuring device, guy wire code space position measuring method and system 
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CN110500990B (en)  20190709  20200818  同济大学  Sixdegreeoffreedom measurement system and method 
Citations (5)
Publication number  Priority date  Publication date  Assignee  Title 

CN1570556A (en) *  20040512  20050126  清华大学  Measuring device and method for spatial pose of rigid body 
CN101173876A (en) *  20071130  20080507  哈尔滨工业大学  Control method for threeaxis sixfreedom hydraulic vibration table based on kinematics 
CN102063122A (en) *  20101110  20110518  哈尔滨工业大学  Spatial sixdegreeoffreedom motion platform modal control method 
CN102221123A (en) *  20110422  20111019  陕西豪曼机电科技工程有限公司  Submicronlevel positioning accuracy parallel regulating platform and regulating method thereof 
CN102278963A (en) *  20110630  20111214  燕山大学  Selfcalibration method of parallel robot 

2012
 20120412 CN CN201210106028.4A patent/CN102636139B/en not_active IP Right Cessation
Patent Citations (5)
Publication number  Priority date  Publication date  Assignee  Title 

CN1570556A (en) *  20040512  20050126  清华大学  Measuring device and method for spatial pose of rigid body 
CN101173876A (en) *  20071130  20080507  哈尔滨工业大学  Control method for threeaxis sixfreedom hydraulic vibration table based on kinematics 
CN102063122A (en) *  20101110  20110518  哈尔滨工业大学  Spatial sixdegreeoffreedom motion platform modal control method 
CN102221123A (en) *  20110422  20111019  陕西豪曼机电科技工程有限公司  Submicronlevel positioning accuracy parallel regulating platform and regulating method thereof 
CN102278963A (en) *  20110630  20111214  燕山大学  Selfcalibration method of parallel robot 
NonPatent Citations (3)
Title 

《非对称式6/6SPS型Stewart并联机构运动学正解的研究》;周辉等;《现代制造工程》;20100630;第15页 * 
周辉等.《非对称式6/6SPS型Stewart并联机构运动学正解的研究》.《现代制造工程》.2010,15. * 
曹毅等.《6/ 6SPS型Stewart并联机构运动学正解的研究》.《安徽理工大学学报（自然科学版）》.2008,第28卷(第1期), * 
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