CN103868512A - High-precision aircraft heading and attitude test circuit - Google Patents
High-precision aircraft heading and attitude test circuit Download PDFInfo
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- CN103868512A CN103868512A CN201410113614.0A CN201410113614A CN103868512A CN 103868512 A CN103868512 A CN 103868512A CN 201410113614 A CN201410113614 A CN 201410113614A CN 103868512 A CN103868512 A CN 103868512A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/10—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration
- G01C21/12—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning
- G01C21/16—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning by integrating acceleration or speed, i.e. inertial navigation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C25/00—Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
- G01C25/005—Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass initial alignment, calibration or starting-up of inertial devices
Abstract
The invention discloses a high-precision aircraft heading and attitude test circuit, mainly aiming at solving the problem that the existing test circuit is poor in accuracy. The test circuit comprises a digital system control circuit (1), an analog-digital conversion circuit (2), a temperature sensor circuit (3), a magnetoresistive sensor calibration circuit (4), a signal amplification circuit (5), a gyroscope sensor circuit (6) and an acceleration sensor circuit (7), wherein the four input ends of the analog-digital conversion circuit (2) are respectively connected with the temperature sensor circuit (3), the signal amplification circuit (5), the gyroscope sensor circuit (6) and the acceleration sensor circuit (7); the digital system control circuit (1) is used for controlling the analog-digital conversion circuit (2) to convert output signals of all the sensor circuits into digital values and controlling the magnetoresistive sensor calibration circuit (4) to complete the calibration work. After the high-precision aircraft heading attitude test circuit is adopted, the influence of factors such as high magnetic field, temperature, noise and the like to the circuit can be effectively reduced, so that the attitude and the heading of an aircraft can be accurately obtained.
Description
Technical field
The invention belongs to electronic circuit technology field, relate to aircraft course attitude test circuit, particularly a kind of aircraft course attitude high precision measurement circuit.
Background technology
Aircraft course attitude test circuit is for collecting the attitude information such as the angle of pitch, course angle of aircraft.General main sensor circuit and the analog to digital conversion circuit two parts of comprising of conventional aircraft course attitude test circuit.Analog to digital conversion circuit uses modulus conversion chip that the analog quantity of sensor output is converted to digital quantity.
Traditional sensor circuit generally uses the boat appearance status information of the sensor test aircraft such as vertical gyro, rate gyro, directional gyroscope, accelerometer, magnetoresistive transducer, for attitude and the course of flight-control computer real-time resolving aircraft.Existing aircraft course attitude test circuit does not gather ambient temperature data, because sensor can, because the variation of ambient temperature produces drift and causes attitude to be dispersed, cause output signal out of true.In addition, magnetoresistive transducer is very easily subject to the interference in extraneous large magnetic field, causes output decay.Meanwhile, the output signal of magnetoresistive transducer is very little, is very easily subject to the interference of external environmental noise.But available circuit does not propose solution for the problems referred to above.Simultaneously, when the analog quantity of sensor output is converted to digital quantity by existing aircraft course attitude test circuit, adopt the modulus conversion chip of 16, data processed result can only be accurate to after radix point 6, and adopt single-ended input, in the time that external environment noise is larger, input signal can be affected, and causes data processing inaccurate.Therefore, current test circuit is poor to the antijamming capability of the external environmental factors such as high-intensity magnetic field, temperature, high frequency noise, causes surveying appearance error larger, cannot resolve accurately attitude and the course of aircraft.
Summary of the invention
The object of the invention is to, for existing aircraft course attitude test circuit deficiency, propose a kind of aircraft course attitude high precision measurement circuit, to reduce to survey appearance error, draw accurately attitude and the course of aircraft.
For achieving the above object, aircraft course attitude high precision measurement circuit of the present invention, comprise digital display circuit control circuit 1, analog to digital conversion circuit 2, gyro sensor circuit 6 and acceleration sensor circuit 7, this analog to digital conversion circuit 2 is provided with nine input ends, two output terminals, the first input end a of analog to digital conversion circuit 2 is connected with gyro sensor circuit 6, for angular velocity data is converted to digital quantity; The second input end b of analog to digital conversion circuit 2 is connected with acceleration sensor circuit 7, is converted to digital quantity for will speed up degrees of data, it is characterized in that:
The 3rd input end c of analog to digital conversion circuit 2 is connected with temperature sensor circuit 3, for temperature data is converted to digital quantity, and digital quantity is offered to digital display circuit control circuit 1;
The output terminal of digital display circuit control circuit 1 is connected with magnetoresistive transducer calibration circuit 4, in the time of circuit working, magnetoresistive transducer is calibrated;
The four-input terminal d of analog to digital conversion circuit 2 is connected with signal amplification circuit 5, for the magnetoresistive transducer output signal after amplifying is converted to digital quantity, and digital quantity is offered to digital display circuit control circuit 1.
As preferably, digital display circuit control circuit 1 of the present invention, adopts but is not limited to the digital display circuit control chip U1 that model is MC56F8014, and it is provided with an input end MISO and five output terminal CLK, MOSI, SS, SET and RESET.
As preferably, analog to digital conversion circuit 2 of the present invention, comprises 24 high precision analogue conversion chip U2, two-way operational amplifier U3, resistance R 1, R2, and capacitor C 1;
Described modulus conversion chip U2, its 3rd output terminal DOUT is connected with the first input end MISO of digital display circuit control chip U1; The 7th input end CS of modulus conversion chip U2 is connected with the first output terminal SS of digital display circuit control chip U1, the 8th input end SCLK is connected with the second output terminal CLK of digital display circuit control chip U1, and the 9th input end DIN is connected with the 3rd output terminal MOSI of digital display circuit control chip U1;
Described two-way operational amplifier U3, is provided with four input ends and 2 output terminals, and the first output terminal MUXOUTP of its second input end e and modulus conversion chip U2 joins, and the first output terminal MUXOUTP of four-input terminal h and modulus conversion chip U2 joins; First input end f and the first output terminal g join, and the 3rd input end i and the second output terminal j join, and form 2 road voltage follower circuits, improve output impedance; Its first output terminal g is connected with the 5th input end ADCINN of modulus conversion chip U2 by resistance R 1, and the second output terminal j is connected with the 6th input end ADCINP of modulus conversion chip U1 by resistance R 2;
Described capacitor C 1, is connected across between the 5th input end ADCINN and the 6th input end ADCINP of modulus conversion chip U2, for isolation mode number conversion sample rate current.
As preferably, temperature data acquisition circuit 3 of the present invention, is made up of temperature sensor U4 and capacitor C 2, this temperature sensor U4, and its anode is connected with power supply VCC, negativing ending grounding, output terminal TEMP is connected with the 3rd input end c of modulus conversion chip U2; This capacitor C 2 is connected across between the anode and negative terminal of temperature sensor U4.
As preferably, magnetoresistive transducer calibration circuit 4 of the present invention, comprises power supply chip U5, triode Q1, two N, P passage metal-oxide-semiconductor chip U6, magnetoresistive transducer U7, capacitor C 3～C5 that resistance R 3～R5 and withstand voltage are 50V;
Described power supply chip U5, provides 20V calibration voltage, and capacitor C 3 is connected across between the output terminal and ground of power supply chip U6, for filtering voltage noise;
Described triode Q1, be provided with two input ends and an output terminal, its base stage Base is connected with the 4th output terminal SET of digital display circuit control circuit 1 by resistance R 4 as first input end, collector Collector receives the output terminal of power supply, chip U4 by resistance R 3 as the second input end, penetrate grade Emitter as output head grounding;
Described binary channels metal-oxide-semiconductor chip U6, be provided with four input ends and two output terminals, its second grid G2 is as first input end, the second source class S2 is as the second input end, first grid G1 is as the 3rd input end, the first source class S1 is as four-input terminal, and the first drain D 1 is as the first output terminal, and the second drain D 2 is as the second output terminal; Its second grid G2 is connected with the collector Collector of triode Q1 by capacitor C 4, be connected with the output terminal of power supply, chip U5 by resistance R 3, the second source class S2 is connected with the output terminal of power supply, chip U5, first grid G1 is connected with the 5th output terminal RESET end of digital display circuit control circuit 1, the first source class S1 ground connection, the first drain D 1 is connected with the second drain D 2;
Described magnetoresistive transducer U7, is provided with an input end, three output terminals, and its input end SR1 is connected to the first drain D 1 and the second drain D 2, the first output terminal SR2 ground connection of binary channels metal-oxide-semiconductor chip U6 by capacitor C 5.
As preferably, signal amplification circuit 5 of the present invention, by accurate differential amplifier U8, power supply fiducial chip U9, resistance R 6, R7, capacitor C 6 forms;
Described accurate differential amplifier U8, is provided with five input ends and an output terminal, and its first input end IP is connected with the second output terminal OP of magnetoresistive transducer, and the second input end IN is connected with the 3rd output terminal ON of magnetoresistive transducer; Resistance R 6 is connected across between the 3rd input end RG1 and four-input terminal RG2, determines the gain of amplifying circuit, and the 5th input end REF is connected with power supply fiducial chip U9, and the reference voltage of amplifying circuit is provided; Its output terminal is connected to the four-input terminal d of modulus conversion chip U2 by resistance R 7, capacitor C 6 is connected across between resistance R 7 and ground; Resistance R 7 and capacitor C 6 are for determining differential amplifier output bandwidth, filter away high frequency noise.
The present invention compared with prior art has the following advantages:
(1) the present invention is owing to having adopted 24 analog to digital converters of high precision, and its voltage resolution can reach 0.6uV, and maximum 0.001% full scale integral nonlinear error, can obtain high-resolution digital signal; This analog to digital converter is taked the mode of difference input, and by two-way voltage follower circuit, improves input impedance, play signal buffer compartment from effect, strengthen signal antijamming capability, improve system accuracy;
(2) the present invention is by increasing magnetoresistive transducer calibration circuit, use the duty of digital display circuit controller control calibration circuit, by high voltage, magnetoresistive transducer is calibrated, eliminated the interference of extraneous high-intensity magnetic field, improved output accuracy and the sensitivity of magnetoresistive transducer;
(3) the present invention, by signal amplification circuit, amplifies the tiny signal of magnetoresistive transducer output, has strengthened the ability of anti-external interference.
(4) the present invention, can the temperature variant drift of compensating signal in the time of data processing by gathering ambient temperature data, thereby has improved system accuracy.
Measured data shows, the present invention can reduce the impacts of external environment factor on circuit such as high-intensity magnetic field, temperature, noise effectively, make data processed result can be accurate to after radix point 7, and current aircraft course attitude test circuit, data processed result can only be accurate to after radix point 6.
Accompanying drawing explanation
Fig. 1 is the structured flowchart of aircraft course attitude high precision measurement circuit of the present invention;
Fig. 2 is the analog to digital conversion circuit schematic diagram in the present invention;
Fig. 3 is the temperature sensor circuit schematic diagram in the present invention;
Fig. 4 is the magnetoresistive transducer calibration circuit schematic diagram in the present invention;
Fig. 5 is the input terminal voltage change curve of magnetoresistive transducer in the present invention;
Fig. 6 is the signal amplification circuit schematic diagram in the present invention.
Embodiment
Below in conjunction with accompanying drawing and embodiment, the invention will be further described.
With reference to Fig. 1, aircraft course attitude high precision measurement circuit of the present invention, comprises digital display circuit control circuit 1, analog to digital conversion circuit 2, temperature sensor circuit 3, magnetoresistive transducer calibration circuit 4, signal amplification circuit 5, gyro sensor circuit 6 and acceierometer sensor circuit 7.Temperature sensor circuit 3, signal amplification circuit 5, gyro sensor circuit 6 is all connected with analog to digital conversion circuit 2 with acceleration sensor circuit 7.Temperature sensor circuit 3 gathers ambient temperature data, offers analog to digital conversion circuit 2; The angular velocity data of generation when gyro sensor circuit 6 overturns for gathering aircraft, and offer analog to digital conversion circuit 2; The acceleration information that acceierometer sensor circuit 7 produces at acceleration or deceleration motion process for gathering aircraft, offers analog to digital conversion circuit 2; Digital display circuit control circuit 1 is connected with magnetoresistive transducer calibration circuit 4, controlling magnetoresistive transducer calibration circuit 4 by transmitting control signal calibrates magnetoresistive transducer, after calibration operation completes, the output signal of magnetoresistive transducer offers signal amplification circuit 5, and the field signal after amplifying is offered analog to digital conversion circuit 2 by signal amplification circuit 5; Digital display circuit control circuit 1 carries out two-way communication with analog to digital conversion circuit 2, control analog to digital conversion circuit 2 and gather the data that the sensor provides, and data are converted to digital quantity, and receive the digital quantity that analog to digital conversion circuit 2 sends, data are processed, according to temperature data, eliminated angular velocity data, the temperature of acceleration information and magnetic field data is floated, and reduces data error.According to angular velocity data after treatment, acceleration information and magnetic field data, the attitude and the course that accurately draw aircraft.
Described digital display circuit control circuit 1, adopt but be not limited to the digital display circuit control chip U1 that model is MC56F8014, it is provided with an input end MISO and five output terminals, i.e. the first output terminal SS, the second output terminal CLK, the 3rd output terminal MOSI, the 4th output terminal SET and the 5th output terminal RESET.Input end MISO, the first output terminal SS, the second output terminal CLK is connected with analog to digital conversion circuit 2 with the 3rd output terminal MOSI, controls analog to digital conversion circuit 2 data are converted to digital quantity, and accept the digital quantity that analog to digital conversion circuit 2 sends; The 4th output terminal SET and the 5th output terminal RESET provide control signal control magnetoresistive transducer calibration circuit 4 to complete calibration operation.
Described gyro sensor circuit 6, comprises gyrosensor U10, capacitor C 7, C8, resistance R 8; Gyro sensor U10 adopts but is not limited to ADXRS300 model, and its anode is connected with voltage VCC, negativing ending grounding; Capacitor C 7 is connected across between voltage VCC and ground, for filter out power noise; Capacitor C 8 and resistance R 8 are connected across between output terminal OUT1 and output terminal SMJ end, for determining output bandwidth, filter away high frequency noise.
Described acceierometer sensor circuit 7, comprises acceierometer sensor U11, capacitor C 9, C10; Acceierometer sensor U11 adopts but is not limited to ADXL103 model, and its anode is connected with power supply VCC, negativing ending grounding; Capacitor C 9 is connected across between power supply VCC and ground and is connected, for filter out power noise; Capacitor C 10 is connected across between output terminal OUT2 and ground, for determining output bandwidth, filter away high frequency noise.
With reference to Fig. 2, the analog to digital conversion circuit 2 in the present invention, comprises 24 high-precision modulus conversion chip U2, two-way operational amplifier U3, resistance R 1, R2, and capacitor C 1; 24 high-precision modulus conversion chip U2 adopt but are not limited to ADS1258 model, and two-way operational amplifier U3 adopts but is not limited to OPA2365 model;
Described modulus conversion chip U2, is provided with nine input end a, b, c, d, ADCINN, ADCINP, CS, SCLK and DIN, three output terminal MUXOUTP, MUXOUTN and DOUT; Its first input end a connects the output terminal OUT1 of gyro sensor U10, and the second input end b connects the output terminal OUT2 of acceierometer sensor U11, and the 3rd input end c connects temperature sensor output terminal TEMP; Its four-input terminal d connects differential amplifier output signal OUT; The 7th input end CS is connected with the first output terminal SS of digital display circuit control chip U1, the 8th input end SCLK is connected with the second output terminal CLK of digital display circuit control chip U1, and the 9th input end DIN is connected with the 3rd output terminal MOSI of digital display circuit control chip U1; The first output terminal MUXOUTP is connected with the four-input terminal h of two-way operational amplifier U3, the second output terminal MUXOUTN is connected with the second input end e of two-way operational amplifier U3, and the 3rd output terminal DOUT is connected with the first input end MISO of digital display circuit control chip U1;
The 6th input end ADCINP of described modulus conversion chip U1 is by the output terminal h of resistance R 2 concatenation operation amplifier U3; The 5th input end ADCINN is by the output terminal e of resistance R 1 concatenation operation amplifier U3.Resistance R 1 is kept apart the output of operational amplifier and filter capacitor with resistance R 2, improves circuit precision.Capacitor C 1 is connected across electric capacity between the 5th input end ADCINN and the 6th input end ADCINP, is used for bypass analog to digital conversion sample rate current;
The first input end f of described two-way operational amplifier U3 and the first output terminal g join, and the 3rd input end i and the second output terminal j join, and form two-way voltage follower circuit, improve output impedance.
With reference to Fig. 3, the temperature sensor circuit 3 in the present invention, comprises temperature sensor U4 and capacitor C 2; Temperature sensor U4 adopts but is not limited to AD590 model, and its anode is connected with power supply VCC, negativing ending grounding, and output terminal TEMP is connected to the 3rd input end c of analog to digital converter; This capacitor C 2 is connected across between the power positive end and negative terminal of temperature sensor U4, with filter away high frequency noise.
With reference to Fig. 4, the magnetoresistive transducer calibration circuit 4 in the present invention, comprises triode Q1, power supply chip U5, two N, P passage metal-oxide-semiconductor chip U6, magnetoresistive transducer U7, capacitor C 3～C5 that withstand voltage is 50V, resistance R 3～R5; Triode Q1, power supply chip U5 adopts but is not limited to LM27317 model, two N, P passage metal-oxide-semiconductor chip U6, magnetoresistive transducer U7 adopts but is not limited to HMC1001 model.
Described power supply chip U5, provides 20V calibration voltage, and an end of capacitor C 3 is connected on the output terminal of power supply chip U5, other end ground connection, filter out power high frequency noise;
Described triode Q1, is provided with two input ends and an output terminal, and Base is as first input end for its base stage, and collector Collector, as the second input end, penetrates grade Emitter as output terminal; Its base stage Base is connected with the 4th output terminal SET of digital display circuit control chip U1 by resistance R 4, penetrates a grade Emitter ground connection, and collector Collector receives the output terminal of power supply chip U5 by resistance R 3, and resistance R 3 and resistance R 4 play the effect of current limliting;
Described binary channels metal-oxide-semiconductor chip U6, its inside comprises a N-channel MOS pipe and a P channel MOS tube, be provided with four input ends and two output terminals, its second grid G2 is as first input end, the second source class S2 is as the second input end, and first grid G1 is as the 3rd input end, and the first source class S1 is as four-input terminal, the first drain D 1 is as the first output terminal, and the second drain D 2 is as the second output terminal; Its second grid G2 is connected with the collector Collector of triode Q1 by capacitor C 4, is connected with the output terminal of power supply chip U5 by resistance R 3, and the second source class S2 is connected with the output terminal of power supply chip U5; First grid G1 is connected with the 5th output terminal RESET of digital display circuit control chip U1, the first source class S1 ground connection, and the first drain D 1 is connected with the second drain D 2;
Described magnetoresistive transducer U7, is provided with an input end, three output terminals, its input end SR1 is connected to the first drain D 1 and the second drain D 2 by capacitor C 5, the first output terminal SR2 ground connection, the output signal of the second output terminal OP is V1, the output signal of the 3rd output terminal is V2.
With reference to Fig. 5, described magnetoresistive transducer calibration circuit 4 is provided with five kinds of different time sequence status:
The first time sequence status is: the 4th output terminal SET end of digital display circuit control chip U1 provides 0V signal, the 5th output terminal RESET end of digital display circuit control chip U1 provides 3.3V signal, triode Q1 cut-off in this state, collector Collector voltage is 20V, the second grid G2 voltage of binary channels metal-oxide-semiconductor chip U6 is constant, be still 20V, therefore, the cut-off of P channel MOS tube; Because the 5th output terminal RESET end of digital display circuit control chip U1 provides 3.3V signal, the conducting of N-channel MOS pipe, therefore, the first drain D 1 voltage of binary channels metal-oxide-semiconductor chip U6 is 0V.Capacitor C 5 both end voltage pressure reduction keep 0V constant, so the voltage of magnetoresistive transducer U7 input end SR1 is 0V, its voltage as the line segment in Fig. 5 curve 1. as shown in.
The second time sequence status is: the 4th output terminal SET end of digital display circuit control chip U1 provides 0V signal, the 5th output terminal RESET end of digital display circuit control chip U1 provides 0V signal, triode Q1 cut-off in this state, collector Collector voltage is 20V, the second grid G2 terminal voltage of binary channels metal-oxide-semiconductor chip U6 is constant, be still 20V, therefore, the cut-off of P channel MOS tube; Because the 5th output terminal RESET end of digital display circuit control chip U1 provides 0V signal, the cut-off of N-channel MOS pipe, the first drain D 1 voltage of binary channels metal-oxide-semiconductor chip U6 keeps 0V constant, capacitor C 5 both end voltage pressure reduction are 0V, so the voltage of magnetoresistive transducer U7 input end SR1 is 0V, its voltage as the line segment in Fig. 5 curve 2. as shown in.
The third time sequence status is: the 4th output terminal SET end of digital display circuit control chip U1 provides 3.3V signal, the 5th output terminal RESET end of digital display circuit control chip U1 provides 0V signal, triode Q1 conducting in this state, collector Collector voltage is 0V, can not suddenly change because capacitor C 4 both end voltage are poor, so the second grid G2 voltage of binary channels metal-oxide-semiconductor chip U6 is 0V, the conducting of P channel MOS tube, the second drain D 2 voltages are 20V; Because the 5th output terminal RESET end of digital display circuit control chip U1 provides 0V signal, the cut-off of N-channel MOS pipe, the first drain D 1 voltage of binary channels metal-oxide-semiconductor chip U6 is also 20V.Because the voltage pressure reduction at capacitor C 5 two ends can not suddenly change, so the voltage of magnetoresistive transducer U7 input end SR1 is 20V, afterwards, capacitor C 5 is discharged, and after 3 μ s, magnetoresistive transducer U7 input end SR1 voltage returns to 0V.The voltage of magnetoresistive transducer U7 input end SR1 as the line segment in Fig. 5 curve 3. as shown in.
The 4th kind of time sequence status is: the 4th output terminal SET end of digital display circuit control chip U1 provides 0V signal, the 5th output terminal RESET end of digital display circuit control chip U1 provides 0V signal, triode Q1 cut-off in this state, collector Collector voltage is 20V; The second grid G2 terminal voltage of binary channels metal-oxide-semiconductor chip U6 is constant, is still 20V, the cut-off of P channel MOS tube; Because the 5th output terminal RESET end of digital display circuit control chip U1 provides 0V signal, the cut-off of N-channel MOS pipe, the first drain D 1 end and the second drain D 2 voltages of binary channels metal-oxide-semiconductor chip U6 remain 20V, the voltage of magnetoresistive transducer U7 input end SR1 remains unchanged, be still 0V, capacitor C 5 both end voltage pressure reduction are 20V.The voltage of magnetoresistive transducer U7 input end SR1 as the line segment in Fig. 5 curve 4. as shown in.
The 5th kind of time sequence status is: the 4th output terminal SET end of digital display circuit control chip U1 provides 0V signal, when the 5th output terminal RESET end of digital display circuit control chip U1 provides 3.3V signal, triode Q1 cut-off in this state, collector Collector voltage is 20V, the second grid G2 terminal voltage of binary channels metal-oxide-semiconductor chip U6 keeps 20V constant, the cut-off of P channel MOS tube; Because the 5th output terminal RESET end of digital display circuit control chip U1 provides 3.3V signal, the conducting of N-channel MOS pipe, now, the first drain D 1 of binary channels metal-oxide-semiconductor chip U6 and the second drain D 2 are 0V, because the voltage pressure reduction at capacitor C 5 two ends can not suddenly change, magnetoresistive transducer U7 input end SR1 voltage is-20V.After 3 μ s, SR1 terminal voltage reverts to 0V.The voltage of magnetoresistive transducer U7 input end SR1 as the line segment in Fig. 5 curve 5. as shown in.
With reference to Fig. 6, signal amplification circuit 5 of the present invention, for the tiny signal of magnetoresistive transducer U7 is amplified, strengthens anti-external interference ability, its output voltage OUT=G*(V1-V2)+V
ref.This circuit comprises accurate differential amplifier U8, power supply fiducial chip U9, resistance R 6, R7, capacitor C 6; Accurate differential amplifier U8 adopts but is not limited to AD8226 model, and power supply fiducial chip U9 adopts but is not limited to TPS77725 model.
Described accurate differential amplifier U8, is provided with five input ends and an output terminal, and its first input end IP is connected with the second output terminal OP of magnetoresistive transducer, and the second input end IN is connected with the 3rd output terminal ON of magnetoresistive transducer; Output terminal is connected to the four-input terminal d of modulus conversion chip U2 by resistance R 7, capacitor C 6 is connected across between resistance R 7 and ground, and resistance R 7 and capacitor C 6 are for determining its output bandwidth, and filter away high frequency noise, improves signal stabilization.
Described resistance R 6 is connected across between the 3rd input end RG1 and four-input terminal RG2 of accurate differential amplifier U8, is used for determining amplifier gain G=50;
Described power supply fiducial chip U9, its output terminal is connected to the 5th input end REF of accurate differential amplifier U8, for amplifier provides reference voltage V
ref;
Checking after tested, the present invention can reduce the impacts of external environment factor on circuit such as high-intensity magnetic field, temperature, noise effectively, make data processed result can be accurate to after radix point 7, and current aircraft course attitude test circuit, data processed result can only be accurate to after radix point 6.
Below be only a preferred example of the present invention; do not form any limitation of the invention; obviously for those skilled in the art; understanding after content of the present invention and principle; all may be in the situation that not deviating from the principle of the invention, structure; carry out various corrections and change in form and details, but these corrections based on inventive concept and changing still within claim protection domain of the present invention.
Claims (6)
1. an aircraft course attitude high precision measurement circuit, comprise digital display circuit control circuit (1), analog to digital conversion circuit (2), gyro sensor circuit (6) and acceleration sensor circuit (7), this analog to digital conversion circuit (2) is provided with nine input ends, two output terminals, the first input end a of analog to digital conversion circuit (2) is connected with gyro sensor circuit (6), for angular velocity data is converted to digital quantity; The second input end b of analog to digital conversion circuit (2) is connected with acceleration sensor circuit (7), is converted to digital quantity for will speed up degrees of data, it is characterized in that:
The 3rd input end c of analog to digital conversion circuit (2) is connected with temperature sensor circuit (3), for temperature data is converted to digital quantity, and digital quantity is offered to digital display circuit control circuit (1);
The output terminal of digital display circuit control circuit (1) is connected with magnetoresistive transducer calibration circuit (4), for when the circuit working, magnetoresistive transducer is calibrated;
The four-input terminal d of analog to digital conversion circuit (2) is connected with signal amplification circuit (5), for the magnetoresistive transducer output signal after amplifying is converted to digital quantity, and digital quantity is offered to digital display circuit control circuit (1).
2. aircraft course attitude high precision measurement circuit according to claim 1, wherein digital display circuit control circuit (1), adopt but be not limited to the digital display circuit control chip U1 that model is MC56F8014, it is provided with an input end MISO and five output terminal CLK, MOSI, SS, SET and RESET.
3. aircraft course attitude high precision measurement circuit according to claim 1, wherein analog to digital conversion circuit (2), comprises 24 high precision analogue conversion chip U2, two-way operational amplifier U3, resistance R 1, R2, and capacitor C 1;
Described modulus conversion chip U2, its 3rd output terminal DOUT is connected with the first input end MISO of digital display circuit control chip U1; The 7th input end CS of modulus conversion chip U2 is connected with the first output terminal SS of digital display circuit control chip U1, the 8th input end SCLK is connected with the second output terminal CLK of digital display circuit control chip U1, and the 9th input end DIN is connected with the 3rd output terminal MOSI of digital display circuit control chip U1;
Described two-way operational amplifier U3, is provided with four input ends and 2 output terminals, and the first output terminal MUXOUTP of its second input end e and modulus conversion chip U2 joins, and the first output terminal MUXOUTP of four-input terminal h and modulus conversion chip U2 joins; First input end f and the first output terminal g join, and the 3rd input end i and the second output terminal j join, and form 2 road voltage follower circuits, improve output impedance; Its first output terminal g is connected with the 5th input end ADCINN of modulus conversion chip U2 by resistance R 1, and the second output terminal j is connected with the 6th input end ADCINP of modulus conversion chip U1 by resistance R 2;
Described capacitor C 1, its two ends are connected with the 6th input end ADCINP with the 5th input end ADCINN of modulus conversion chip U2 respectively, for isolation mode number conversion sample rate current.
4. aircraft course attitude high precision measurement circuit according to claim 1, wherein temperature sensor circuit (3), formed by temperature sensor U4 and capacitor C 2, this temperature sensor U4, its anode is connected with power supply VCC, negativing ending grounding, its output terminal TEMP is connected with the 3rd input end c of modulus conversion chip U2; This capacitor C 2 is connected across between the anode and negative terminal of temperature sensor U4.
5. aircraft course attitude high precision measurement circuit according to claim 1, wherein magnetoresistive transducer calibration circuit (4), comprises power supply chip U5, triode Q1, two N, P passage metal-oxide-semiconductor chip U6, magnetoresistive transducer U7, capacitor C 3～C5 that resistance R 3～R5 and withstand voltage are 50V;
Described power supply chip U5, provides 20V calibration voltage, and capacitor C 3 is connected across between the output terminal and ground of power supply chip U6, for filtering voltage noise;
Described triode Q1, be provided with two input ends and an output terminal, its base stage Base is connected with the 4th output terminal SET of digital display circuit control circuit (1) by resistance R 4 as first input end, collector Collector receives the output terminal of power supply chip U4 by resistance R 3 as the second input end, penetrate grade Emitter as output head grounding;
Described binary channels metal-oxide-semiconductor chip U6, be provided with four input ends and two output terminals, its second grid G2 is as first input end, the second source class S2 is as the second input end, first grid G1 is as the 3rd input end, the first source class S1 is as four-input terminal, and the first drain D 1 is as the first output terminal, and the second drain D 2 is as the second output terminal; Its second grid G2 is connected with the collector Collector of triode Q1 by capacitor C 4, be connected with the output terminal of power supply chip U5 by resistance R 3, the second source class S2 is connected with the output terminal of power supply chip U5, first grid G1 is connected with the 5th output terminal RESET end of digital display circuit control circuit (1), the first source class S1 ground connection, the first drain D 1 is connected with the second drain D 2;
Described magnetoresistive transducer U7, is provided with an input end, three output terminals, and its input end SR1 is connected to the first drain D 1 and the second drain D 2 of binary channels metal-oxide-semiconductor chip U6 by capacitor C 5, by the first output terminal SR2 ground connection.
6. aircraft course attitude high precision measurement circuit according to claim 1, wherein signal amplification circuit (5), by accurate differential amplifier U8, power supply fiducial chip U9, resistance R 6 and R7, capacitor C 6 forms;
Described accurate differential amplifier U8, is provided with five input ends and an output terminal, and its first input end IP is connected with the second output terminal OP of magnetoresistive transducer, and the second input end IN is connected with the 3rd output terminal ON signal of magnetoresistive transducer; Resistance R 6 is connected across between the 3rd input end RG1 and four-input terminal RG2, determines the gain of amplifying circuit, and the 5th input end REF is connected with power supply fiducial chip U9, and the reference voltage of amplifying circuit is provided; Its output terminal is connected to the four-input terminal d of modulus conversion chip U2 by resistance R 7, capacitor C 6 is connected across between resistance R 7 and ground; Resistance R 7 and capacitor C 6 are for determining differential amplifier output bandwidth, filter away high frequency noise.
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| CN201410113614.0A CN103868512A (en) | 2014-03-25 | 2014-03-25 | High-precision aircraft heading and attitude test circuit |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104949669A (en) * | 2015-06-24 | 2015-09-30 | 北京理工大学 | Method for expanding range of fiber optic gyroscope based on magnetoresistive sensor |
| CN105540056A (en) * | 2016-03-01 | 2016-05-04 | 杭州糖球科技有限公司 | Intelligent vacuum refreshing food containing box and control method thereof |
| CN106406274A (en) * | 2016-08-31 | 2017-02-15 | 河北汉光重工有限责任公司 | Simulation test device based on all-digital control circuit and simulation test method thereof |
| CN108426559A (en) * | 2018-02-27 | 2018-08-21 | 北京环境特性研究所 | A kind of antenna attitude detection device and method |
| CN112833921A (en) * | 2020-12-31 | 2021-05-25 | 广州导远电子科技有限公司 | Single-axis gyroscope circuit |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1851407A (en) * | 2006-05-30 | 2006-10-25 | 梁保山 | High-precision micro electromechanical combined inertial nevigation apparatus |
| CN102360218A (en) * | 2011-10-14 | 2012-02-22 | 天津大学 | ARM (advanced RISC (reduced instruction set computer) machines) and FPGA (field-programmable gate array) based navigation and flight control system for unmanned helicopter |
| CN102980577A (en) * | 2012-12-05 | 2013-03-20 | 南京理工大学 | Micro-strapdown altitude heading reference system and working method thereof |
| CN103308039A (en) * | 2013-05-14 | 2013-09-18 | 深圳市通创通信有限公司 | Digital magnetic compass and calibration compensation method and calibration compensation system thereof |
-
2014
- 2014-03-25 CN CN201410113614.0A patent/CN103868512A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1851407A (en) * | 2006-05-30 | 2006-10-25 | 梁保山 | High-precision micro electromechanical combined inertial nevigation apparatus |
| CN102360218A (en) * | 2011-10-14 | 2012-02-22 | 天津大学 | ARM (advanced RISC (reduced instruction set computer) machines) and FPGA (field-programmable gate array) based navigation and flight control system for unmanned helicopter |
| CN102980577A (en) * | 2012-12-05 | 2013-03-20 | 南京理工大学 | Micro-strapdown altitude heading reference system and working method thereof |
| CN103308039A (en) * | 2013-05-14 | 2013-09-18 | 深圳市通创通信有限公司 | Digital magnetic compass and calibration compensation method and calibration compensation system thereof |
Non-Patent Citations (1)
| Title |
|---|
| 任剡等: "微型无人机磁航向测量系统的设计与实现", 《西安航空技术高等专科学校学报》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104949669A (en) * | 2015-06-24 | 2015-09-30 | 北京理工大学 | Method for expanding range of fiber optic gyroscope based on magnetoresistive sensor |
| CN105540056A (en) * | 2016-03-01 | 2016-05-04 | 杭州糖球科技有限公司 | Intelligent vacuum refreshing food containing box and control method thereof |
| CN105540056B (en) * | 2016-03-01 | 2017-08-29 | 杭州糖球科技有限公司 | Intelligent vacuum Fresh-keeping mess tin and its control method |
| CN106406274A (en) * | 2016-08-31 | 2017-02-15 | 河北汉光重工有限责任公司 | Simulation test device based on all-digital control circuit and simulation test method thereof |
| CN108426559A (en) * | 2018-02-27 | 2018-08-21 | 北京环境特性研究所 | A kind of antenna attitude detection device and method |
| CN108426559B (en) * | 2018-02-27 | 2020-07-24 | 北京环境特性研究所 | Antenna attitude detection device and method |
| CN112833921A (en) * | 2020-12-31 | 2021-05-25 | 广州导远电子科技有限公司 | Single-axis gyroscope circuit |
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