CN102419173B - Method for locating posture sensing device and method for controlling mouse pointer - Google Patents
Method for locating posture sensing device and method for controlling mouse pointer Download PDFInfo
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- CN102419173B CN102419173B CN2011102352054A CN201110235205A CN102419173B CN 102419173 B CN102419173 B CN 102419173B CN 2011102352054 A CN2011102352054 A CN 2011102352054A CN 201110235205 A CN201110235205 A CN 201110235205A CN 102419173 B CN102419173 B CN 102419173B
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- gyrostatic
- voltage
- awareness apparatus
- rotation
- output voltage
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F3/00—Input arrangements for transferring data to be processed into a form capable of being handled by the computer; Output arrangements for transferring data from processing unit to output unit, e.g. interface arrangements
- G06F3/01—Input arrangements or combined input and output arrangements for interaction between user and computer
- G06F3/03—Arrangements for converting the position or the displacement of a member into a coded form
- G06F3/033—Pointing devices displaced or positioned by the user, e.g. mice, trackballs, pens or joysticks; Accessories therefor
- G06F3/0346—Pointing devices displaced or positioned by the user, e.g. mice, trackballs, pens or joysticks; Accessories therefor with detection of the device orientation or free movement in a 3D space, e.g. 3D mice, 6-DOF [six degrees of freedom] pointers using gyroscopes, accelerometers or tilt-sensors
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C19/00—Gyroscopes; Turn-sensitive devices using vibrating masses; Turn-sensitive devices without moving masses; Measuring angular rate using gyroscopic effects
- G01C19/56—Turn-sensitive devices using vibrating masses, e.g. vibratory angular rate sensors based on Coriolis forces
- G01C19/5776—Signal processing not specific to any of the devices covered by groups G01C19/5607 - G01C19/5719
Abstract
The embodiment of the invention provides a method for acquiring the output voltage of gyroscope, which comprises the steps of: acquiring an initial voltage signal on a detection arm of the gyroscope; amplifying the initial voltage signal by a factor of a first multiple, filtering out high frequency interference, and then performing A/D sampling to acquire a first voltage; amplifying the first voltage by a factor of a second multiple, wherein the second multiple is more than the first multiple, filtering out high frequency interference, and then performing A/D sampling to acquire a second voltage; and comparing the first voltage and the second voltage with a threshold voltage respectively, and selecting the first voltage or the second voltage as the output voltage of the gyroscope. In the embodiment of the invention, more accurate output voltage can be acquired. Based on the method for acquiring the output voltage of gyroscope, the embodiment of the invention further provides a method capable of rapidly and accurately locating posture sensing device, and a method for controlling mouse pointer at high sensitivity.
Description
Technical field
The present invention relates to the positioning field of attitude awareness apparatus, relate in particular to a kind of localization method of attitude awareness apparatus, the control method of mouse pointer.
Background technology
At present, the location great majority of computer pointer mouse pointer all rely on optical sensor or laser sensor to realize.These sensors all are based on the physical optics principle, make sensor need rely on platforms such as desktop to realize.But along with the day by day raising of people to working environment and simple operation requirement, the user wishes that mouse can break away from the dependence to desktop, upgrades to the space mouse, can realize unsettled 3D operation, the wrist of only need gently waving, pointer can arbitrarily move, and easily controls apparatus such as computer.Therefore, arise at the historic moment based on gyrostatic space mouse.
Realize the perception of aerial sports attitude, can adopt the variation of acceleration transducer induction speed, the perhaps variation of gyroscope sense angular rate.Gyroscope is with its variation that can in time induce the space, can detect that each goes up the advantage of the angular velocity of rotation in the motion process, and makes and comprise that gyrostatic air mouse takes advantage.
Gyrostatic ultimate principle is when using the objects at high speed rotation, and powerful angular momentum makes the turning axle stable character of pointing to a direction always, the directed instrument that manufacturing is come out.Point to when inconsistent when direction of motion and rotating shaft, can produce corresponding drift angle, again according to the relation of drift angle and motion, movement locus and the position of movement parts up till now, thereby realize the function of location.
Yet, the control method of the mouse pointer of the space mouse of prior art, because the gyroscope in the mouse of space is accurate inadequately to the perception of its athletic posture, thereby the sensitivity that the space mouse control mouse pointer of feasible employing prior art moves is lower, for user's practical operation is made troubles.
More details about the space mouse please refer to publication number and are the Chinese patent of " CN102043475A ".
Summary of the invention
The problem that the present invention solves provides a kind of localization method of the attitude awareness apparatus that can be accurately the attitude awareness apparatus be positioned, a kind of control method of highly sensitive mouse pointer.
For addressing the above problem, embodiments of the invention provide a kind of method of obtaining gyrostatic output voltage, comprising:
Obtain described gyrostatic initial voltage signal, described initial voltage signal is amplified first multiple, the filtering high frequency interference is carried out the A/D sampling again, obtains first voltage;
Described initial voltage signal is amplified second multiple, and described second multiple is greater than first multiple, and the filtering high frequency interference is carried out the A/D sampling again, obtains second voltage;
Respectively described first voltage, second voltage and threshold voltage are compared, when described first voltage and second voltage during all less than threshold voltage, select second voltage as gyrostatic output voltage; When described first voltage less than threshold voltage, second voltage selects first voltage as gyrostatic output voltage during greater than threshold voltage.
Alternatively, described threshold voltage is 1380～1420mv.
Alternatively, also comprise: after described initial voltage signal is amplified first multiple, before the filtering high frequency interference, carry out calculus of differences and amplify; After described initial voltage signal amplified second multiple, before the filtering high frequency interference, carry out calculus of differences and amplify.
Embodiments of the invention also provide a kind of localization method of attitude awareness apparatus, and described attitude awareness apparatus comprises first gyroscope and second gyroscope at least, and the described first gyrostatic detection arm comprises perpendicular to the described second gyrostatic detection arm:
Obtain the primary importance of described attitude awareness apparatus;
After described attitude awareness apparatus moves to the second place by described primary importance, obtain first gyroscope and the second gyrostatic output voltage respectively;
Determine described first gyroscope and the second gyrostatic angular velocity of rotation respectively, wherein, each gyrostatic output voltage and angular velocity of rotation are linear;
Based on described first gyroscope and the second gyrostatic angular velocity of rotation, determine the second place of described attitude awareness apparatus at the component of first direction and second direction, to locate described attitude awareness apparatus, described first direction is perpendicular to described second direction.
Alternatively, the linear relationship of the described first gyrostatic output voltage and angular velocity of rotation is V
1=a
1ω
1+ b
1, V wherein
1Be the described first gyrostatic output voltage, ω
1Be the described first gyrostatic angular velocity of rotation, a
1, b
1Be constant; The linear relationship of the described second gyrostatic output voltage and angular velocity of rotation is V
2=a
2ω
2+ b
2, V wherein
2Be the described second gyrostatic output voltage, ω
2Be the described second gyrostatic angular velocity of rotation, a
2, b
2Be constant.
Alternatively, described a
1, a
2Be 0.67, described b
1, b
2Be 1350.
Alternatively, based on described first gyroscope and the second gyrostatic angular velocity of rotation, determine that the second place of described attitude awareness apparatus comprises in the step of the component of first direction and second direction:
The described first gyrostatic angular velocity of rotation by the time integration, is obtained the described first gyrostatic anglec of rotation α 1;
Calculate the second place of described attitude awareness apparatus at the component A cos of first direction α 1, wherein, A is that the primary importance of described attitude awareness apparatus is at the component of first direction;
The described second gyrostatic angular velocity of rotation by the time integration, is obtained the described second gyrostatic anglec of rotation α 2;
Calculate the second place of described attitude awareness apparatus at the component Bcos of second direction α 2, wherein, B is that the primary importance of described attitude awareness apparatus is at the component of second direction.
Alternatively, also comprise:
Calculate the second place of described attitude awareness apparatus at change component the A '=A-Acos α 1 of first direction;
Calculate the second place of described attitude awareness apparatus at change component the B '=B-Bcos α 2 of second direction.
Alternatively, described first gyroscope and second gyroscope are single axis gyroscope, and described first gyroscope and the second gyrostatic material are quartzy.
Alternatively, also comprise:
The 3rd gyroscope is provided;
Obtain the described the 3rd gyrostatic output voltage, described the 3rd gyroscope comprises that detection arm, two symmetries are positioned at the actuating arm of detection arm both sides, and connect the connecting portion at described detection arm center and actuating arm center, and the described the 3rd gyrostatic output voltage is the voltage that records on the 3rd gyrostatic detection arm;
Determine the described the 3rd gyrostatic angular velocity of rotation;
Determine the second place of described attitude awareness apparatus at the component of third direction based on the described the 3rd gyrostatic angular velocity of rotation, described third direction is perpendicular to first direction and perpendicular to second direction.
Alternatively, the linear relationship of the described the 3rd gyrostatic output voltage and angular velocity of rotation is V
3=a
3ω
3+ b
3, V wherein
3Be the described the 3rd gyrostatic output voltage, ω
3Be the described the 3rd gyrostatic angular velocity of rotation, a
3, b
3Be constant.
Alternatively, determine that based on the described the 3rd gyrostatic angular velocity of rotation the second place of described attitude awareness apparatus comprises in the step of the component of third direction:
The described the 3rd gyrostatic angular velocity of rotation is obtained the described the 3rd gyrostatic anglec of rotation α 3 by the time integration;
Calculate the second place of described attitude awareness apparatus at the component Ccos of third direction α 3, wherein C is that the primary importance of described attitude awareness apparatus is at the component of third direction.
Alternatively, also comprise: calculate the second place of described attitude awareness apparatus at change component the C '=C-Ccos α 3 of third direction.
Alternatively, described the 3rd gyroscope is single axis gyroscope, and the described the 3rd gyrostatic material is quartzy.
A kind of control method of mouse pointer comprises:
Utilize above-mentioned localization method to determine that the second place of attitude awareness apparatus is in the change component of first direction and second direction;
Calculate the anglec of rotation rate of change vx of first direction, wherein vx=A '/SF
1, SF
1It is the first gyrostatic sensitivity coefficient;
Determine described mouse pointer at the displacement variable Δ X of X-direction, Δ X=vx/MF wherein, MF is the sensitivity coefficient of mouse pointer;
Calculate the anglec of rotation rate of change vy of second direction, wherein vy=B '/SF
2, SF
2It is the second gyrostatic sensitivity coefficient;
Determine described mouse pointer at the displacement variable Δ Y of Y direction, Δ Y=vy/MF wherein, described Y direction is perpendicular to X-direction;
Based on mouse pointer at the displacement variable Δ X of X-direction with control the movement of described mouse pointer at the displacement variable Δ Y of Y direction.
Alternatively, described mouse pointer is by the space mouse control.
Alternatively, described space mouse also comprises data data acquisition unit, data processing unit, the information transmitting unit that is positioned at described space mouse and the information receiving unit that links to each other with the display screen of computer or television.
Compared with prior art, embodiments of the invention have the following advantages:
In the embodiments of the invention, even the angle that the gyroscope rotation is very little, that part of voltage that gyroscope rotation itself produces is less, the voltage that produces with external interference mixes, be difficult to distinguish, after amplifying second multiple (greater than first multiple), the high-frequency signal that the voltage signal that can effectively gyroscope rotation itself be produced and external interference produce filters, the value of the output voltage that obtains is more accurate, is beneficial to gyrostatic athletic posture is carried out more accurate localization.
Further, the attitude awareness apparatus of the embodiment of the invention comprises first gyroscope and second gyroscope at least, and each gyrostatic output voltage that the method for the employing embodiment of the invention obtains makes that the location of attitude awareness apparatus is more accurate.And, because each gyrostatic output voltage and angular velocity of rotation are linear, can determine each gyrostatic angular velocity faster based on described linear relationship, and the second place of definite described attitude awareness apparatus is carried out two-dimensional localization to the attitude awareness apparatus faster at the component of first direction and second direction.
Further, the embodiment of the invention provides a kind of control method of mouse pointer, adopt embodiments of the invention to obtain described first gyroscope and the second gyrostatic output voltage, determine fast that by the linear relationship of each gyrostatic output voltage and angular velocity of rotation the second place of space mouse is in the change component of first direction and second direction, finally obtain mouse pointer at the displacement variable Δ X of X-direction with at the displacement variable Δ Y of Y direction, the movement of accurate mouse beacon pointer fast, the sensitivity that has improved the space mouse.
Further, also comprise the 3rd gyroscope in the embodiments of the invention, the described the 3rd gyrostatic output voltage and the anglec of rotation are linear, linear relationship based on the described the 3rd gyrostatic output voltage and the anglec of rotation, can determine fast that the second place of described attitude awareness apparatus at the component of third direction, carries out three-dimensional localization to the attitude awareness apparatus fast accurately.
Description of drawings
Fig. 1 is the schematic flow sheet that obtains gyrostatic output voltage of first embodiment of the invention;
Fig. 2 is the schematic flow sheet of localization method of the attitude awareness apparatus of first embodiment of the invention
Fig. 3 is first gyroscope and the second gyrostatic structural representation of the attitude awareness apparatus of first embodiment of the invention;
Fig. 4～Fig. 6 is the circuit diagram of each gyrostatic acquisition output voltage of the attitude awareness apparatus of first embodiment of the invention;
Fig. 7 is the synoptic diagram that concerns between the gyrostatic output voltage of the embodiment of the invention and the angular velocity of rotation;
Fig. 8 is the first gyrostatic output voltage of attitude awareness apparatus of first embodiment of the invention and the linear relationship synoptic diagram of angular velocity of rotation;
Fig. 9 is the second gyrostatic output voltage of attitude awareness apparatus of first embodiment of the invention and the linear relationship synoptic diagram of angular velocity of rotation;
Figure 10 is the schematic flow sheet that space mouse control mouse pointer moves that passes through of second embodiment of the invention;
Figure 11 is the 3rd gyrostatic structural representation of third embodiment of the invention;
Figure 12 is that first gyroscope, second gyroscope and the 3rd gyrostatic position of the attitude awareness apparatus of third embodiment of the invention concerns synoptic diagram.
Embodiment
Just as stated in the Background Art, the sensitivity of moving of the mouse beacon pointer of the space mouse of prior art is not high.The inventor finds through the research back, the space mouse is that axle rotates can the movement of mouse beacon pointer on display screen with the elbow joint, its cardinal principle is by detecting each the gyrostatic output voltage in the mouse of space, according to the relation between described output voltage and the angular velocity of rotation, determine each gyrostatic angular velocity of rotation, again based on described each gyrostatic angular velocity of rotation, determine that mouse pointer is in the movement of the displacement variable Δ Y mouse beacon pointer of the displacement variable Δ X of X-direction and Y direction.
The inventor finds that after further research the sensitivity that space mouse control mouse pointer moves in the prior art is not high, is mainly caused by following reason:
The one,, the value of each the gyrostatic output voltage that moves as follow-up definite mouse pointer is accurate inadequately, especially when the very little angle of described gyroscope rotation, because the voltage of the voltage that the rotation of gyroscope itself produces and external interference generation is difficult to distinguish.
The 2nd,, the gyroscope that the space mouse of prior art adopts, the displacement X (t) of described gyroscope on X-axis is: X (t)=Acos (ω
2T-Φ
c), wherein:
X
0Be the peak swing of vibration input, f
0Be the resonance frequency of detection arm, Q
0Be mechanical quality factor, ω
zBe the angular velocity of vibration input, A is the vibration amplitude of gyroscope on detection arm, Φ
cBe gyrostatic initial phase, f
cResonance frequency for driving shaft.According to above-mentioned formula as can be known, the displacement X (t) of gyroscope on X-axis and the angular velocity omega that vibrates input
zBe directly proportional, and be nonlinear relationship; Again because piezoelectric effect, gyroscope is directly proportional with gyrostatic displacement X (t) at the output voltage of the direction of detection arm, therefore can learn between the gyrostatic output voltage of prior art and the angular velocity of rotation and be nonlinear relationship, the process of calculating angular velocity of rotation by output voltage is comparatively complicated, length consuming time, make that the speed that moves by space mouse control mouse pointer is slower, the sensitivity of space mouse is low.
Further, please refer to Fig. 1, the inventor of the embodiment of the invention provides a kind of method of obtaining gyrostatic output voltage, comprising:
Step S10, obtain described gyrostatic initial voltage signal, described gyroscope comprises that detection arm, two symmetries are positioned at the actuating arm of detection arm both sides, and connect the connecting portion at described detection arm center and actuating arm center, measure on the detection arm of described gyrostatic initial voltage signal by correspondence;
Step S20 amplifies first multiple with described initial voltage signal, and the filtering high frequency interference is carried out the A/D sampling again, obtains first voltage;
Step S30 amplifies second multiple with described initial voltage signal, and described second multiple is greater than first multiple, and the filtering high frequency interference is carried out the A/D sampling again, obtains second voltage;
Step S40 compares described first voltage, second voltage and threshold voltage respectively, when described first voltage and second voltage during all less than threshold voltage, selects second voltage as gyrostatic output voltage; When described first voltage less than threshold voltage, second voltage selects first voltage as gyrostatic output voltage during greater than threshold voltage.
And, based on the above-mentioned method of obtaining gyrostatic output voltage, please refer to Fig. 2, the inventor of the embodiment of the invention provides a kind of localization method of attitude awareness apparatus, comprising:
Step S100 provides the attitude awareness apparatus, and described attitude awareness apparatus comprises first gyroscope and second gyroscope at least, and the described first gyrostatic detection arm is obtained the primary importance of described attitude awareness apparatus perpendicular to the described second gyrostatic detection arm;
Step S200 after described attitude awareness apparatus moves to the second place by described primary importance, obtains first gyroscope and the second gyrostatic output voltage respectively;
Step S300 determines described first gyroscope and the second gyrostatic angular velocity of rotation, and wherein, each gyrostatic output voltage and angular velocity of rotation are linear;
Step S400, based on described first gyroscope and the second gyrostatic angular velocity of rotation, determine the second place of described attitude awareness apparatus at the component of first direction and second direction, to locate described attitude awareness apparatus, described first direction is perpendicular to described second direction.
The localization method of above-mentioned attitude awareness apparatus, because each gyrostatic output voltage and angular velocity of rotation are linear, according to described output voltage, can determine described angular velocity of rotation fast, further determine the second place of attitude awareness apparatus fast at the component of first direction and second direction, thereby accurately the attitude awareness apparatus is carried out two dimension or three-dimensional location fast.
Further, the inventor of the embodiment of the invention provides a kind of control method that adopts the mouse pointer of said method, because the space mouse that the mouse beacon pointer moves comprises two gyroscopes, and it is linear between each gyrostatic output voltage and the angular velocity of rotation, when the space mouse control mouse pointer of the employing embodiment of the invention moves, owing to determine that by each gyrostatic output voltage the method for angular velocity of rotation is fast simple more, therefore the space mouse can obtain mouse pointer fast at the displacement variable Δ X of X-direction with at the displacement variable Δ Y of Y direction, thereby the fast movement of accurate mouse beacon pointer, space mouse highly sensitive.
For above-mentioned purpose, the feature and advantage that make embodiments of the invention can become apparent more, below in conjunction with accompanying drawing embodiments of the invention are described in detail.
A lot of details have been set forth in the following description so that fully understand embodiments of the invention, but embodiments of the invention can also adopt other to be different from alternate manner described here and implement, so embodiments of the invention are not subjected to the restriction of following public specific embodiment.
First embodiment
Please refer to Fig. 3, in the first embodiment of the present invention, at first, provide to comprise first gyroscope and the second gyrostatic attitude awareness apparatus at least, wherein:
Described first gyroscope comprises: detection arm 110; Symmetry is positioned at actuating arm 120 and the actuating arm 130 of described detection arm 110 both sides; The connecting portion 140 that connects described detection arm 110 centers, described actuating arm 120 centers and actuating arm 130 centers;
Described second gyroscope comprises: detection arm 210; Symmetry is positioned at actuating arm 220 and the actuating arm 230 of described detection arm 210 both sides; The connecting portion 240 that connects described detection arm 210 centers, described actuating arm 220 centers and described actuating arm 230;
The described first gyrostatic detection arm 110 is perpendicular to the described second gyrostatic detection arm 210.
Described first gyroscope and second gyroscope also comprise driving circuit respectively, described driving circuit is used for driving each gyrostatic two actuating arm and produces vibration, the vibration frequency of each gyrostatic two actuating arm is identical, and the vibration frequency of the vibration frequency of described first gyrostatic two actuating arms and second gyrostatic two actuating arms is 40KHz～60KHz.For fear of resonance, in an embodiment of the present invention, the vibration frequency of described first gyrostatic two actuating arms is 46.5KHz, and the vibration frequency of described second gyrostatic two actuating arms is 50.3KHz.
In an embodiment of the present invention, described first gyroscope and second gyroscope are single axis gyroscope, and consider that quartzy characteristic is not obvious with the variation of environment temperature, the inaccurate problem in location of the attitude awareness apparatus that causes for fear of temperature variation, described first gyroscope and the second gyrostatic material are quartzy.
Need to prove that described attitude awareness apparatus also comprises: data acquisition unit and data processing unit.Wherein, described data acquisition unit is used for obtaining the primary importance information of each gyrostatic output voltage and attitude awareness apparatus; Described data processing unit is used for determining according to each gyrostatic output voltage that data acquisition unit provides the second place of attitude awareness apparatus.
Described primary importance is the position of definite attitude awareness apparatus last time, can be obtained by data storage cell.In an embodiment of the present invention, described attitude awareness apparatus is static when primary importance, because two gyrostatic actuating arm symmetries are positioned at the both sides of detection arm, and the center that connects described detection arm and two actuating arms by connecting portion, described two actuating arms that are symmetricly set on the detection arm both sides are by vibration relatively, can eliminate noise, for example Wai Bu shock and vibration, described detection arm remains static.
Because described attitude awareness apparatus is static when primary importance, each the gyrostatic voltage when measuring described attitude awareness apparatus and being positioned at primary importance is as described reference voltage.Need to prove, in the actual mechanical process, can after each gyroscope assembling of described attitude awareness apparatus is finished, measure each gyrostatic reference voltage, and all remeasure each gyrostatic reference voltage when noting be used in each use.
Then, make described attitude awareness apparatus move to the second place by primary importance, described first gyroscope and second gyroscope rotate, and obtain each gyrostatic output voltage.
That obtains each gyrostatic output voltage can choose in following several mode any at least:
Please refer to Fig. 4, measure the initial voltage signal V of each gyrostatic certain point by the data acquisition unit (not shown) that links to each other with each gyrostatic detection axle
0, described initial voltage signal V
0Through low-pass filter (LPF) 300 filtering part high frequency interference, carry out A/D sampling 310 through port P again and obtain each gyrostatic output voltage, be i.e. the first gyrostatic output voltage V
1, and the second gyrostatic output voltage V
2
The part high frequency interference that adopted output voltage filtering that method shown in Figure 4 obtains, the value of the gyrostatic output voltage of each that obtains is comparatively accurate.
Please refer to Fig. 5, measure the initial voltage signal V of each gyrostatic certain point by the data acquisition unit that links to each other with each gyrostatic detection axle
0, by first amplifying unit 405 with described initial voltage signal V
0Amplify first multiple, obtain signal V
01, again through first low-pass filter (LPF1), 400 filtered signal V
01In high frequency interference obtain signal V
01', carry out A/D sampling 410 through port P1 again, obtain the first voltage V
01"; By second amplifying unit 420 with described initial voltage signal V
0Amplify second multiple, described second multiple obtains signal V greater than first multiple
02, again with described signal V
02Obtain V through second low-pass filter (LPF2), 430 filtering high frequency interference
02', carry out A/D sampling 410 through port P2 again and obtain the second voltage V
02"; At last by comparing the selected cell 440 more described first voltage V
01" and the second voltage V
02" whether less than threshold voltage, select the first voltage V
01" or the second voltage V
02" as each gyrostatic output voltage, i.e. the first gyrostatic output voltage V
1With the second gyrostatic output voltage V
2
Wherein, described first amplifying unit has first sensitivity coefficient, and described first multiple and first sensitivity coefficient are proportional; Described second amplifying unit has second sensitivity coefficient, and described second multiple and second sensitivity coefficient are proportional, and described first sensitivity coefficient is less than described second sensitivity coefficient.
In an embodiment of the present invention, described first sensitivity coefficient is 0.8mv/dps, the signal V behind described amplification first multiple
01Be V
00+ 0.8 α, wherein V
00Be the reference voltage of gyroscope when static, α is the gyrostatic anglec of rotation; Described second amplifying unit is reverser, and second sensitivity coefficient of described reverser is 3.624mv/dps, the signal V behind described amplification second multiple
02Be V
00+ 3.624 α, wherein V
00Be the reference voltage of gyroscope when static, α is the gyrostatic anglec of rotation.
Select first voltage or second voltage as the foundation of each gyrostatic output voltage to be: when described first voltage and second voltage during all less than threshold voltage, to select second voltage as each gyrostatic output voltage; When described first voltage less than threshold voltage, second voltage selects first voltage as each gyrostatic output voltage during greater than threshold voltage.
In an embodiment of the present invention, described threshold voltage is 1380～1420mv.
Adopt method shown in Figure 5 to obtain gyrostatic output voltage, even the angle (for example 3 ° and following) that the gyroscope rotation is very little, that part of voltage that gyroscope rotation itself produces is less, the voltage that produces with external interference mixes, be difficult to distinguish, after amplifying second multiple (greater than first multiple), the high-frequency signal that the voltage signal that can effectively gyroscope rotation itself be produced and external interference produce filters, the value of the output voltage that obtains is more accurate, follow-uply also can calculate the gyrostatic anglec of rotation accurately by gyrostatic output voltage, be beneficial to gyrostatic athletic posture is carried out more accurate localization.
Please refer to Fig. 6, measure the initial voltage signal V of each gyrostatic certain point by the data acquisition unit (not shown) that links to each other with each gyrostatic detection axle
0, by first amplifying unit 405 with described initial voltage signal V
0Amplify first multiple, obtain signal V
01, with described signal V
01Carry out difference through first operational amplifier 415 and amplify, the high frequency interference in the signal after amplifying through first low-pass filter (LPF1), 400 filtering difference again obtains signal V
010', carry out A/D sampling 410 through port P1 again, obtain the first voltage V
010"; By second amplifying unit 420 with described initial voltage signal V
0Amplify second multiple, described second multiple obtains signal V greater than first multiple
02, with described signal V
01Carry out difference through second operational amplifier 425 and amplify, the high frequency interference in the signal after amplifying through second low-pass filter (LPF2), 430 filtering difference again obtains signal V
020', carry out A/D sampling 410 through port P2 again and obtain the second voltage V
020"; The more described first voltage V at last
010" and the second voltage V
020" whether less than threshold voltage, select the first voltage V
010" or the second voltage V
020" as each gyrostatic output voltage, i.e. the first gyrostatic output voltage V
1With the second gyrostatic output voltage V
2
Wherein, described first operational amplifier 415 has two input ends and an output terminal, and the signal of one of them input end input is for amplifying initial voltage signal the signal V behind first multiple
01, the signal of another input end input is reference voltage signal V
Ref, the signal of described output terminal output is the signal V after difference is amplified
01-V
Ref, the signal of described output terminal output has been eliminated common mode interference, has especially eliminated the influence that temperature causes gyrostatic voltage signal.
Described second operational amplifier 425 has two input ends and an output terminal, and the input of one of them input end is amplified signal V behind second multiple with initial voltage signal
02, another input end signal is reference voltage signal V
Ref, the signal of described output terminal output is the signal V after difference is amplified
02-V
Ref, the signal of described output terminal output has been eliminated common mode interference, has especially eliminated the influence that temperature causes gyrostatic voltage signal.
Need to prove, consider the characteristic that calculus of differences amplifies, described reference voltage V
RefGreater than zero, less than V
01
The method that Fig. 6 adopts is on the basis of method shown in Figure 5, increased the step that difference is amplified, can effectively suppress common mode interference, especially can eliminate the influence that variation of temperature causes for gyrostatic output voltage, make that gyrostatic output voltage is more accurate.
In an embodiment of the present invention, preferably adopt method shown in Figure 5 to obtain the first gyrostatic output voltage V
1With the second gyrostatic output voltage V
2
Be subjected to the influence of earth deflection force (Coriolis force), two actuating arms that are symmetricly set on the second detection arm both sides can produce lengthwise movement, further drive described detection arm and produce the detection vibration, can obtain output voltage on the described gyrostatic detection arm by any method among above-mentioned Fig. 3～Fig. 5, be used for follow-up each gyrostatic angular velocity of rotation of determining.
Again then, determine the first gyrostatic angular velocity of rotation according to the first gyrostatic output voltage that records, determine the second gyrostatic angular velocity of rotation according to the second gyrostatic output voltage that records.
Wherein, because the equal symmetry of each gyrostatic actuating arm is positioned at the both sides of described detection arm, and connecting portion connects the center of described detection arm and two actuating arms, described gyrostatic structure makes resonance frequency and the gyrostatic mechanical quality factor of gyroscope actuating arm along with the variation of the different generations of other conditions is very little, referring among Fig. 7 shown in the solid line, be approximately linear relationship between gyrostatic output voltage and the angular velocity of rotation, pass through Least Square in Processing again, obtain straight line as shown in phantom in Figure 7, V=a ω+b, wherein V is gyrostatic output voltage, and ω is gyrostatic angular velocity of rotation, a, b is constant.
Linear between the described first gyrostatic output voltage and the angular velocity of rotation.Please refer to Fig. 8, the described first gyrostatic output voltage and angular velocity of rotation linear relationship are V
1=a
1ω
1+ b
1, V wherein
1Be the described first gyrostatic output voltage, ω
1Be the described first gyrostatic angular velocity of rotation, a
1, b
1Be constant, and b
1It is the first gyrostatic reference voltage value; Please refer to Fig. 9, linear between the described second gyrostatic output voltage and the angular velocity of rotation, the linear relationship of the described second gyrostatic output voltage and angular velocity of rotation is V
2=a
2ω
2+ b
2, V wherein
2Be the described second gyrostatic output voltage, ω
2Be the described second gyrostatic angular velocity of rotation, a
2, b
2Be constant and b
2It is the second gyrostatic reference voltage value.
In an embodiment of the present invention, described a
1, a
2Be 0.67, described b
1, b
2Be 1350.The linear relationship that is the described first gyrostatic output voltage and angular velocity of rotation is V
1=0.67 ω
1+ 1350, the described first gyrostatic reference voltage value is 1350mv; The linear relationship of the described second gyrostatic output voltage and angular velocity of rotation is V
2=0.67 ω
2+ 1350, the described second gyrostatic reference voltage value is 1350mv.
As mentioned above, the gyrostatic output voltage of each of described attitude awareness apparatus and angular velocity of rotation are linear, when determining each gyrostatic angular velocity of rotation by described each gyrostatic output voltage, need the time of cost shorter, can be faster the second place of attitude awareness apparatus be positioned, reduced the time required to the location of attitude awareness apparatus on the whole.
At last, based on the described first gyrostatic angular velocity of rotation, determine that the second place of described attitude awareness apparatus is at the component of first direction; Based on the described second gyrostatic angular velocity of rotation, determine the second place of described attitude awareness apparatus at the component of second direction, wherein said first direction is perpendicular to described second direction, particularly:
The described first gyrostatic angular velocity of rotation by the time integration, is obtained the described first gyrostatic anglec of rotation α 1;
Calculate the second place of described attitude awareness apparatus at the component A cos of first direction α 1, wherein, A is that the primary importance of described attitude awareness apparatus is at the component of first direction;
The described second gyrostatic angular velocity of rotation by the time integration, is obtained the described second gyrostatic anglec of rotation α 2;
Calculate the second place of described attitude awareness apparatus at the component Bcos of second direction α 2, wherein, B is that the primary importance of described attitude awareness apparatus is at the component of second direction.
Need to prove, in an embodiment of the present invention, can also be to the second place of calculating described attitude awareness apparatus change component the A '=A-Acos α 1 at first direction; Calculate the second place of described attitude awareness apparatus at change component the B '=B-Bcos α 2 of second direction, to realize the two-dimensional localization to the attitude awareness apparatus.
In the first embodiment of the present invention, described attitude awareness apparatus is by two mutually perpendicular gyroscopes of detection arm, and each gyrostatic output voltage and angular velocity of rotation are linear, determine corresponding angular velocity of rotation by each gyrostatic output voltage fast, finally realized accurately described attitude awareness apparatus being carried out fast the location of two dimension.
Need to prove, in other embodiments of the invention, described attitude awareness apparatus can also comprise a data storage unit, comprises a plurality of each the gyrostatic output voltage that obtain through repetition test, the position that reaches corresponding attitude awareness apparatus in the described data storage cell.When the attitude awareness apparatus is positioned, after getting access to each gyrostatic output voltage, can obtain position with the corresponding attitude awareness apparatus of described each gyrostatic output voltage by inquiry and data storage cell.Adopt this kind mode accurately the attitude awareness apparatus to be positioned faster.
Second embodiment
A kind of control method of mouse pointer is provided in an embodiment of the present invention.
In second embodiment of the invention, the space mouse that moves through of described mouse pointer is controlled.By mobile described space mouse, the position of described space mouse is mapped to the mouse pointer place on the display screen, and is mobile at display screen with the mouse beacon pointer.Described space mouse comprises first gyroscope and second gyroscope as shown in Figure 3.
Wherein, described first gyroscope comprises that actuating arm 120 that detection arm 110, symmetry are positioned at described detection arm 110 both sides is connected the connecting portion 140 at described detection arm 110 centers, described actuating arm 120 centers and actuating arm 130 centers with actuating arm 130; Described second gyroscope comprises detection arm 210; Symmetry is positioned at actuating arm 220 and the actuating arm 230 of described detection arm 210 both sides; The connecting portion 240 that connects described detection arm 210 centers, described actuating arm 220 centers and described actuating arm 230.
In an embodiment of the present invention, described first gyroscope and second gyroscope are single axis gyroscope, and described first gyroscope and the second gyrostatic material are quartzy, can avoid temperature to float phenomenon.
The method that obtains each gyrostatic output voltage also comprises any in three kinds shown in Fig. 4～6 at least, and details please refer to the first embodiment of the present invention.
Above-mentioned each gyrostatic output voltage and angular velocity of rotation are linear, and namely the described first gyrostatic output voltage and angular velocity of rotation are linear, and the linear relationship of the described first gyrostatic output voltage and angular velocity of rotation is V
1=a
1ω
1+ b
1, V wherein
1Be the described first gyrostatic output voltage, ω
1Be the described first gyrostatic angular velocity of rotation, a
1, b
1Be constant, and b
1It is the first gyrostatic reference voltage value (as shown in Figure 8); The described second gyrostatic output voltage and angular velocity of rotation are linear, and the linear relationship of the described second gyrostatic output voltage and angular velocity of rotation is V
2=a
2ω
2+ b
2, V wherein
2Be the described second gyrostatic output voltage, ω
2Be the described second gyrostatic angular velocity of rotation, a
2, b
2Be constant, and b
2It is the second gyrostatic reference voltage value (as shown in Figure 9).
Please refer to Figure 10, the space mouse 800 of second embodiment of the invention comprises data acquisition unit 810, data processing unit 820, information transmitting unit 830 and information receiving unit 840.Wherein, described collecting unit 810, data processing unit 820, information transmitting unit 830 are positioned at space mouse 800, and described information receiving unit 840 links to each other with the display screen of computer or TV.
Described data acquisition unit 810 is used for gathering the space mouse first gyrostatic output voltage and the second gyrostatic output voltage.
Described data processing unit 820 is used for obtaining the first gyrostatic output voltage and the second gyrostatic output voltage that data acquisition unit 810 collects, and determine mouse pointer at the displacement variable Δ X of X-direction based on the described first gyrostatic output voltage, determine that based on the described second gyrostatic output voltage mouse pointer is at the displacement variable Δ Y of Y direction.Wherein, the coordinate system of described X-axis and Y-axis formation is positioned on the display screen.
Described information transmitting unit 830 is used for and will be sent to information receiving unit 840 at the displacement variable Δ X of X-direction with at the displacement variable Δ Y of Y direction from the mouse pointer that data processing unit 820 obtains.
Described information receiving unit 840 is used for receiving mouse pointer that described information transmitting unit 830 sends at the displacement variable Δ X of X-direction with in the information of the displacement variable Δ Y of Y direction, and the display screen movement that linking to each other with information receiving unit 840 of mouse beacon pointer 850.
The course of work of the space mouse 800 of the embodiment of the invention is specially: be the axle rotation with the elbow joint, the motion of described space mouse 800 can be decomposed into along first direction and move with the second direction vertical with described first direction, the first gyrostatic output voltage V 1 and the second gyrostatic output voltage V 2 that the data acquisition unit 810 of described space mouse 800 will collect pass to data processing unit 820, described data processing unit 820 is through determining after the computing that the second place of space mouse 800 is at the component of described first direction and second direction, then according to the mapping relations between space mouse 800 and the mouse pointer 850, obtain mouse pointer 850 to need mobile data message be mouse pointer 850 at the displacement variable Δ X of X-direction with at the displacement variable Δ Y of Y direction, and need mobile data message send to information receiving unit 840 described mouse pointer 850 by the information transmitting unit 830 of space mouse 800, move at the display screen that links to each other with described information receiving unit 840 accurately fast with mouse beacon pointer 850.
In an embodiment of the present invention, easy to operate for the ease of the user, the first direction of described space mouse is identical with the X-direction of mouse pointer 850, and the second direction of described space mouse is identical with the Y direction of mouse pointer 850.
Need to prove that in other embodiments of the invention, the first direction of described space mouse also can be different with the X-direction of mouse pointer, the second direction of described space mouse also can be different with the Y direction of mouse pointer.As long as the first direction of space mouse is corresponding with the X-direction of mouse pointer after shining upon, the second direction of space mouse is corresponding with the Y direction of mouse pointer after shining upon.
The control method of the mouse pointer in the second embodiment of the present invention is mainly finished in the data processing unit 820 of space mouse, comprising:
Utilize the localization method of first embodiment to determine that the second place of attitude awareness apparatus is in the change component of first direction and second direction;
Calculate the anglec of rotation rate of change vx of first direction, wherein vx=A '/SF
1, SF
1It is the first gyrostatic sensitivity coefficient;
Determine described mouse pointer at the displacement variable Δ X of X-direction, Δ X=vx/MF wherein, MF is the sensitivity coefficient of mouse pointer;
Calculate the anglec of rotation rate of change vy of second direction, wherein vy=B '/SF
2, SF
2It is the second gyrostatic sensitivity coefficient;
Determine described mouse pointer at the displacement variable Δ Y of Y direction, Δ Y=vy/MF wherein, described Y direction is perpendicular to X-direction;
Based on mouse pointer at the displacement variable Δ X of X-direction with control the movement of described mouse pointer at the displacement variable Δ Y of Y direction.
Wherein, described gyrostatic sensitivity coefficient and first sensitivity coefficient, second sensitivity coefficient, relevant.Particularly, if select first voltage as output voltage, then described gyrostatic sensitivity coefficient is first sensitivity coefficient; If select second voltage as output voltage, then described gyrostatic sensitivity coefficient is second sensitivity coefficient.
Because each gyrostatic output voltage and angular velocity of rotation linear (shown in Fig. 8,9), the data processing unit of described space mouse is determined speeding up of angular velocity of rotation by each gyrostatic output voltage, can determine quickly that based on described first gyroscope and the second gyrostatic angular velocity of rotation mouse pointer is at the displacement variable Δ X of X-direction with at the displacement variable Δ Y of Y direction, the mouse beacon pointer is the accurate mobile second place that arrives fast, space mouse highly sensitive.
Need to prove that in other embodiments of the invention, the space mouse that is used for the mouse beacon pointer also can comprise data storage cell, described data storage cell comprises each gyrostatic output voltage of space mouse and the position of mouse pointer at least.Therefore, knowing under the situation of each gyrostatic output voltage, can directly obtain the position of mouse pointer fast by the data query storage unit, thus the quicker accurate movement of mouse beacon pointer.
The 3rd embodiment
Different with first embodiment, for realizing the three-dimensional localization of attitude awareness apparatus, please refer to Figure 11, the attitude awareness apparatus of third embodiment of the invention also comprises the 3rd gyroscope.Described the 3rd gyroscope comprises detection arm 910; Symmetry is positioned at actuating arm 920 and the actuating arm 930 of described detection arm 910 both sides; The connecting portion 940 that connects described detection arm 910 centers, described actuating arm 920 centers and described actuating arm 930 centers.
In an embodiment of the present invention, described the 3rd gyroscope is single axis gyroscope, and the described the 3rd gyrostatic material is quartzy.
Please refer to Figure 12, Figure 12 shows in the attitude awareness apparatus, described first gyroscope, second gyroscope and the 3rd gyrostatic position relation, the described first gyrostatic detection arm 110, the described second gyrostatic detection arm 210 and the described the 3rd gyrostatic detection arm 910 lay respectively at x, y, on the z axle, described each gyrostatic detection arm is vertical in twos.
Need to prove, described x, y, the z axle is represented first direction, second direction and third direction respectively, above-mentioned 3 directions are vertical in twos.
The 3-D positioning method of described attitude awareness apparatus also comprises:
After described attitude awareness apparatus moves to the second place by described primary importance, obtain the 3rd gyrostatic output voltage V
3, described output voltage V
3Be the voltage that records on the 3rd gyrostatic detection arm 910;
Determine the described the 3rd gyrostatic angular velocity of rotation ω
3, wherein the linear relationship of the 3rd gyrostatic output voltage and angular velocity of rotation is V
3=a
3ω
3+ b
3, a wherein
3, b
3Be constant;
Based on the described the 3rd gyrostatic angular velocity of rotation ω
3Determine the second place of described attitude awareness apparatus at the component of third direction, described third direction is perpendicular to first direction and perpendicular to second direction.
The described the 3rd gyrostatic output voltage V
3Preparation method also comprise in shown in Fig. 4～6 three kinds any at least, details please refer to the first embodiment of the present invention.
In the third embodiment of the present invention, the described the 3rd gyrostatic output voltage V
3Preferred adopt method shown in Figure 6 to obtain, owing to adopt passed through low pass filter filters out again behind reverser, operational method device high frequency interference, the 3rd gyrostatic output voltage V that obtains
3More accurate, be beneficial to follow-up accurate described attitude awareness apparatus location.
In the third embodiment of the present invention, the linear relationship of the described the 3rd gyrostatic output voltage and angular velocity of rotation and first gyroscope, second gyroscope are identical, i.e. a
3=0.67, b
3=1350.From the linear relationship of the described the 3rd gyrostatic output voltage and angular velocity of rotation as can be seen, the described the 3rd gyrostatic reference voltage is 1350mv.
Wherein, based on the described the 3rd gyrostatic angular velocity of rotation ω
3The second place of determining described attitude awareness apparatus comprises in the step of the component of third direction:
The described the 3rd gyrostatic angular velocity of rotation is obtained the described the 3rd gyrostatic anglec of rotation α 3 by the time integration;
Calculate the second place of described attitude awareness apparatus at the component Ccos of third direction α 3, wherein C is that the primary importance of described attitude awareness apparatus is at the component of third direction.
Need to prove, can also calculate the second place of described attitude awareness apparatus at change component the C '=C-Ccos α 3 of third direction.
Based on the second place of the described attitude awareness apparatus component at first direction, second direction and third direction, finished the three-dimensional localization of attitude awareness apparatus.
Need to prove, described attitude awareness apparatus also comprises data storage cell, described data storage cell comprises each the gyrostatic output voltage that obtains through repetition test, the position that reaches the attitude awareness apparatus corresponding with described output voltage, thereby realizes accurately the attitude awareness apparatus being carried out three-dimensional localization fast by each gyrostatic output voltage.
To sum up, in the embodiments of the invention, even the angle that the gyroscope rotation is very little, that part of voltage that gyroscope rotation itself produces is less, and the voltage that produces with external interference mixes, and is difficult to distinguish, after amplifying second multiple (greater than first multiple), the high-frequency signal that the voltage signal that can effectively gyroscope rotation itself be produced and external interference produce filters, and the value of the output voltage that obtains is more accurate, is beneficial to gyrostatic athletic posture is carried out more accurate localization.
Further, the attitude awareness apparatus of the embodiment of the invention comprises first gyroscope and second gyroscope at least, and each gyrostatic output voltage that the method for the employing embodiment of the invention obtains makes that the location of attitude awareness apparatus is more accurate.And, because each gyrostatic output voltage and angular velocity of rotation are linear, can determine each gyrostatic angular velocity faster based on described linear relationship, and the second place of definite described attitude awareness apparatus is carried out two-dimensional localization to the attitude awareness apparatus faster at the component of first direction and second direction.
Further, the embodiment of the invention provides a kind of control method of mouse pointer, adopt embodiments of the invention to obtain described first gyroscope and the second gyrostatic output voltage, determine fast that by the linear relationship of each gyrostatic output voltage and angular velocity of rotation the second place of space mouse is in the change component of first direction and second direction, finally obtain mouse pointer at the displacement variable Δ X of X-direction with at the displacement variable Δ Y of Y direction, the movement of accurate mouse beacon pointer fast, the sensitivity that has improved the space mouse.
Further, also comprise the 3rd gyroscope in the embodiments of the invention, the described the 3rd gyrostatic output voltage and the anglec of rotation are linear, linear relationship based on the described the 3rd gyrostatic output voltage and the anglec of rotation, can determine fast that the second place of described attitude awareness apparatus at the component of third direction, carries out three-dimensional localization to the attitude awareness apparatus fast accurately.
Though the present invention with preferred embodiment openly as above; but it is not to limit the present invention; any those skilled in the art without departing from the spirit and scope of the present invention; can utilize method and the technology contents of above-mentioned announcement that technical solution of the present invention is made possible change and modification; therefore; every content that does not break away from technical solution of the present invention; to any simple modification, equivalent variations and modification that above embodiment does, all belong to the protection domain of technical solution of the present invention according to technical spirit of the present invention.
Claims (16)
1. a method of obtaining gyrostatic output voltage is characterized in that, comprising:
Obtain described gyrostatic initial voltage signal, described gyroscope comprises that detection arm, two symmetries are positioned at the actuating arm of detection arm both sides, and connect the connecting portion at described detection arm center and actuating arm center, measure on the detection arm of described gyrostatic initial voltage signal by correspondence;
Described initial voltage signal is amplified first multiple, and the filtering high frequency interference is carried out the A/D sampling again, obtains first voltage;
Described initial voltage signal is amplified second multiple, and described second multiple is greater than first multiple, and the filtering high frequency interference is carried out the A/D sampling again, obtains second voltage;
Respectively described first voltage, second voltage and threshold voltage are compared, when described first voltage and second voltage during all less than threshold voltage, select second voltage as gyrostatic output voltage; When described first voltage less than threshold voltage, second voltage selects first voltage as gyrostatic output voltage during greater than threshold voltage, wherein, described threshold voltage is 1380～1420mv.
2. the method for obtaining gyrostatic output voltage as claimed in claim 1 is characterized in that, also comprises: after described initial voltage signal is amplified first multiple, before the filtering high frequency interference, carry out calculus of differences and amplify; After described initial voltage signal amplified second multiple, before the filtering high frequency interference, carry out calculus of differences and amplify.
3. the localization method of an attitude awareness apparatus, described attitude awareness apparatus comprises first gyroscope and second gyroscope at least, the described first gyrostatic detection arm is characterized in that perpendicular to the described second gyrostatic detection arm, comprising:
Obtain the primary importance of described attitude awareness apparatus;
After described attitude awareness apparatus moves to the second place by described primary importance, utilize any method in the claim 1～2 to obtain first gyroscope and the second gyrostatic output voltage respectively;
Determine described first gyroscope and the second gyrostatic angular velocity of rotation, wherein, each gyrostatic output voltage and angular velocity of rotation are linear;
Based on described first gyroscope and the second gyrostatic angular velocity of rotation, determine the second place of described attitude awareness apparatus at the component of first direction and second direction, to locate described attitude awareness apparatus, described first direction is perpendicular to described second direction.
4. the localization method of attitude awareness apparatus as claimed in claim 3 is characterized in that, the linear relationship of the described first gyrostatic output voltage and angular velocity of rotation is V
1=a
1ω
1+ b
1, V wherein
1Be the described first gyrostatic output voltage, ω
1Be the described first gyrostatic angular velocity of rotation, a
1, b
1Be constant; The linear relationship of the described second gyrostatic output voltage and angular velocity of rotation is V
2=a
2ω
2+ b
2, V wherein
2Be the described second gyrostatic output voltage, ω
2Be the described second gyrostatic angular velocity of rotation, a
2, b
2Be constant.
5. the localization method of attitude awareness apparatus as claimed in claim 4 is characterized in that, described a
1, a
2Be 0.67, described b
1, b
2Be 1350.
6. the localization method of attitude awareness apparatus as claimed in claim 3, it is characterized in that, based on described first gyroscope and the second gyrostatic angular velocity of rotation, determine that the second place of described attitude awareness apparatus comprises in the step of the component of first direction and second direction:
The described first gyrostatic angular velocity of rotation by the time integration, is obtained the described first gyrostatic anglec of rotation α 1;
Calculate the second place of described attitude awareness apparatus at the component A cos of first direction α 1, wherein, A is that the primary importance of described attitude awareness apparatus is at the component of first direction;
The described second gyrostatic angular velocity of rotation by the time integration, is obtained the described second gyrostatic anglec of rotation α 2;
Calculate the second place of described attitude awareness apparatus at the component Bcos of second direction α 2, wherein, B is that the primary importance of described attitude awareness apparatus is at the component of second direction.
7. the localization method of attitude awareness apparatus as claimed in claim 6 is characterized in that, also comprises:
Calculate the second place of described attitude awareness apparatus at change component the A '=A-Acos α 1 of first direction;
Calculate the second place of described attitude awareness apparatus at change component the B '=B-Bcos α 2 of second direction.
8. the localization method of attitude awareness apparatus as claimed in claim 3 is characterized in that, described first gyroscope and second gyroscope are single axis gyroscope, and described first gyroscope and the second gyrostatic material are quartzy.
9. the localization method of attitude awareness apparatus as claimed in claim 3 is characterized in that, also comprises:
The 3rd gyroscope is provided;
Obtain the described the 3rd gyrostatic output voltage, described the 3rd gyroscope comprises that detection arm, two symmetries are positioned at the actuating arm of detection arm both sides, and connect the connecting portion at described detection arm center and actuating arm center, and the described the 3rd gyrostatic output voltage is the voltage that records on the 3rd gyrostatic detection arm;
Determine the described the 3rd gyrostatic angular velocity of rotation;
Determine the second place of described attitude awareness apparatus at the component of third direction based on the described the 3rd gyrostatic angular velocity of rotation, described third direction is perpendicular to first direction and perpendicular to second direction.
10. the localization method of attitude awareness apparatus as claimed in claim 9 is characterized in that, the linear relationship of the described the 3rd gyrostatic output voltage and angular velocity of rotation is V
3=a
3ω
3+ b
3, V wherein
3Be the described the 3rd gyrostatic output voltage, ω
3Be the described the 3rd gyrostatic angular velocity of rotation, a
3, b
3Be constant.
11. the localization method of attitude awareness apparatus as claimed in claim 9 is characterized in that, determines that based on the described the 3rd gyrostatic angular velocity of rotation the second place of described attitude awareness apparatus comprises in the step of the component of third direction:
The described the 3rd gyrostatic angular velocity of rotation is obtained the described the 3rd gyrostatic anglec of rotation α 3 by the time integration;
Calculate the second place of described attitude awareness apparatus at the component Ccos of third direction α 3, wherein C is that the primary importance of described attitude awareness apparatus is at the component of third direction.
12. the localization method of attitude awareness apparatus as claimed in claim 11 is characterized in that, also comprises: calculate the second place of described attitude awareness apparatus at change component the C '=C-Ccos α 3 of third direction.
13. the localization method of attitude awareness apparatus as claimed in claim 11 is characterized in that, described the 3rd gyroscope is single axis gyroscope, and the described the 3rd gyrostatic material is quartzy.
14. the control method of a mouse pointer is characterized in that, comprising:
Utilize the described localization method of claim 7 to determine that the second place of attitude awareness apparatus is in the change component of first direction and second direction;
Calculate the anglec of rotation rate of change vx of first direction, wherein vx=A '/SF
1, SF
1It is the first gyrostatic sensitivity coefficient;
Determine described mouse pointer at the displacement variable Δ X of X-direction, Δ X=vx/MF wherein, MF is the sensitivity coefficient of mouse pointer;
Calculate the anglec of rotation rate of change vy of second direction, wherein vy=B '/SF
2, SF
2It is the second gyrostatic sensitivity coefficient;
Determine described mouse pointer at the displacement variable Δ Y of Y direction, Δ Y=vy/MF wherein, described Y direction is perpendicular to X-direction;
Based on mouse pointer at the displacement variable Δ X of X-direction with control the movement of described mouse pointer at the displacement variable Δ Y of Y direction.
15. the control method of mouse pointer as claimed in claim 14 is characterized in that, described mouse pointer is by the space mouse control.
16. the control method of mouse pointer as claimed in claim 15, it is characterized in that described space mouse also comprises data data acquisition unit, data processing unit, the information transmitting unit that is positioned at described space mouse and the information receiving unit that links to each other with the display screen of computer or television.
Priority Applications (2)
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|---|---|---|---|
| CN2011102352054A CN102419173B (en) | 2011-08-16 | 2011-08-16 | Method for locating posture sensing device and method for controlling mouse pointer |
| PCT/CN2011/081619 WO2013023411A1 (en) | 2011-08-16 | 2011-11-01 | Method for locating attitude-sensing device, and method for controlling mouse pointer |
Applications Claiming Priority (1)
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|---|---|---|---|
| CN2011102352054A CN102419173B (en) | 2011-08-16 | 2011-08-16 | Method for locating posture sensing device and method for controlling mouse pointer |
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| CN102419173B true CN102419173B (en) | 2013-09-04 |
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| CN105096539A (en) * | 2014-04-28 | 2015-11-25 | 鸿富锦精密电子(郑州)有限公司 | Standardized operation training system and method |
| CN109916428B (en) * | 2017-12-12 | 2020-10-09 | 珠海全志科技股份有限公司 | Performance test method and device for gyroscope sensing system in equipment |
| CN112325869A (en) * | 2019-08-02 | 2021-02-05 | 北京小米移动软件有限公司 | Gyroscope circuit, working method of gyroscope circuit and mobile terminal |
| CN113048960B (en) * | 2021-04-13 | 2024-04-12 | 广州得尔塔影像技术有限公司 | Spatial position detection device and position adjustment method |
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