CN101893445A - Rapid initial alignment method for low-accuracy strapdown inertial navigation system under swinging condition - Google Patents
Rapid initial alignment method for low-accuracy strapdown inertial navigation system under swinging condition Download PDFInfo
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Abstract
The invention aims to provide a rapid initial alignment method for a low-accuracy strapdown inertial navigation system under a swinging condition, which comprises the following steps: determining initial position parameters of a carrier; acquiring data output by an accelerometer and a gyroscope, completing coarse alignment of the strapdown inertial navigation system by second-order leveling and a direction estimation method, and determining the attitude of the carrier initially; estimating the length of a lever arm, calculating the disturbing acceleration induced by the lever arm effect, and compensating the output of the accelerometer; establishing a Kalman filtering state equation and a Kalman filtering measurement equation; and estimating the angular misalignment of the system, correcting the strapdown attitude matrix of the system by the angular misalignment at the finish time of fine alignment, and completing initial alignment. The invention eliminates the effect of lever arm effect error on the initial alignment of the strapdown inertial navigation system, shortens the alignment time of the system, and improves the alignment accuracy of the system, thereby comprehensively improving the performance of initial alignment of the low-accuracy strapdown inertial navigation system.
Description
Technical field
What the present invention relates to is the alignment methods that is used for marine navigation.
Background technology
Along with the continuous development of inertial technology, use the inertia device formation strapdown attitude system of low precision and research focus and the developing direction that integrated navigation system has become navigation field.The purpose of strapdown inertial navitation system (SINS) initial alignment is to determine the attitude of carrier at initial time, and initial alignment is a gordian technique of strapdown inertial navitation system (SINS), and it directly affects the precision and the reaction time of inertial navigation system.For the strapdown inertial navitation system (SINS) of low precision, the precision of inertial measurement cluster is not high, is difficult to finish effectively autoregistration, particularly alignment of orientation.
The naval vessel can be in swinging condition because of the interference of fitful wind wave in mooring, except including the rotational-angular velocity of the earth component, also comprising the information of waving on naval vessel in the gyrostatic output; Because the oscillating motion center that carrier is departed from the installation site of inertial measurement cluster not only includes in the output of accelerometer outside the gravitational acceleration component, is also comprising the disturbing acceleration that is caused by lever arm effect.Therefore, the initial alignment problem of researching and solving low-accuracy strapdown inertial navigation system under the swinging condition has great importance.
Summary of the invention
The object of the present invention is to provide low-accuracy strapdown inertial navigation system fast initial alignment method under the swinging condition that can effectively improve the alignment precision of low-accuracy strapdown inertial navigation system initial alignment under the swinging condition and shorten the aligning time.
The object of the present invention is achieved like this:
Low-accuracy strapdown inertial navigation system fast initial alignment method under the swinging condition of the present invention is characterized in that:
(1) determines the initial position parameters of carrier by GPS, comprise longitude and latitude;
(2) gather the data of accelerometer and gyroscope output and the data that collect are handled, adopt second order leveling and DOA estimation method to finish the coarse alignment of strapdown inertial navitation system (SINS), the preliminary attitude of determining carrier, be pitch angle θ, roll angle γ and course angle ψ, set up the initial strapdown matrix of strapdown inertial navitation system (SINS)
(3) at first, according to the angular speed of gyroscope output with and the attitude angle information estimation lever arm length of carrier: at two different moment t
1And t
2Accelerometer is respectively measured one group of specific force value
With
Utilize the different strapdown matrixes that obtain that constantly resolve
With
It is transformed into the calculating geographic coordinate system, obtains
Wherein
Be disturbing acceleration,
Be the distance between the oscillating motion center of the installation site of inertial measurement cluster and carrier,
Be the angular velocity of gyroscope output,
Be corresponding derivative,
Be respectively t
1, t
2Acceleration of gravity constantly, and
Order
Promptly
Obtain
Obtaining lever arm length is
Secondly, calculate the disturbing acceleration that lever arm effect causes:
Then, the output to accelerometer compensates:
Wherein
Be the specific force of compensation preacceleration meter output,
Specific force for the output of compensation post-acceleration meter;
(4) at first, setting up with velocity error and attitude error is the Kalman filtering state equation of state variable:
Wherein X is the state variable of system, and A and B are respectively the state-transition matrix and the noise matrix of system, and W is a system noise, and the state variable of system is
System noise is
δ V wherein
e, δ V
nRepresent east orientation, north orientation velocity error respectively, φ
e, φ
nAnd φ
uRepresent east orientation, north orientation and orientation misalignment respectively,
Represent X-axis, Y-axis accelerometer bias respectively, ε
x, ε
yAnd ε
zRepresent X-axis, Y-axis and Z axle gyroscope constant value drift respectively,
Be respectively X-axis, Y-axis accelerometer bias random white noise,
With
Represent X-axis, Y-axis and Z axle gyroscope constant value drift random white noise respectively, make the strapdown matrix
For
The state-transition matrix of system is
Wherein
ω in the formula
IeBe rotational-angular velocity of the earth, R
eBe earth radius,
Be the specific force of compensation post-acceleration meter output,
Be the angular velocity of gyroscope output, the system noise matrix is
Wherein
Secondly, setting up with velocity error and course error is the Kalman filtering measurement equation of measurement amount:
Z=HX+V,
Wherein Z is the measurement amount of system, and H is the measurement matrix of system, and V is the measurement noise battle array of system, and the amount of system is measured as
Z=[δV
e?δV
n?δψ]
T,
Wherein δ ψ=ψ '-ψ is the course error angle, the course angle that ψ ' resolves for strapdown inertial navitation system (SINS), and ψ is for to carry out revised course angle to the output of magnetic course transmitter, and the measurement matrix of system is
K wherein
1=-tan θ sin ψ, k
2=-tan θ cos ψ, θ, ψ are respectively the pitch angle and the course angle of carrier;
(5) utilize kalman filter method to estimate the misalignment of system, and come the strapdown attitude matrix of update the system with it the finish time at fine alignment:
The transition matrix that calculates between geographic coordinate system n ' and the local geographic coordinate system n is
Transition matrix between carrier coordinate system b and the local geographic coordinate system n is
According to
Determine attitude of carrier, promptly the main value of pitch angle θ, the roll angle γ of carrier and course angle ψ is respectively
The field of definition of roll angle is (0 a °, 360 °), and the field of definition of pitch angle is (90 °, 90 °), and the field of definition of course angle is (180 °, 180 °), and the true value that obtains attitude of carrier is
θ=θ
Main,
Initial alignment is finished.
Advantage of the present invention is: compensated the disturbing acceleration that lever arm effect causes, eliminated the influence of lever arm effect error to the strapdown inertial navitation system (SINS) initial alignment; The increase course error is observed quantity, having overcome traditional is the problem of long, estimation effect difference orientation misalignment estimated time of static-base alignment method of observed quantity with the velocity error, shortened the aligning time of system, improve the alignment precision of system, thereby improved the performance of low-accuracy strapdown inertial navigation system initial alignment comprehensively.
Description of drawings
Fig. 1 is a process flow diagram of the present invention;
Fig. 2 is a lever arm effect error schematic diagram of the present invention;
Fig. 3 is the evaluated error curve of east orientation misalignment in the specific embodiment of the invention;
Fig. 4 is the evaluated error curve of north orientation misalignment in the specific embodiment of the invention;
Fig. 5 is the evaluated error curve of orientation misalignment in the specific embodiment of the invention.
Embodiment
For example the present invention is done description in more detail below in conjunction with accompanying drawing:
In conjunction with Fig. 1~2, low-accuracy strapdown inertial navigation system fast initial alignment method is divided following steps under the swinging condition of the present invention:
(1) determines the initial position parameters of carrier by GPS, comprise longitude and latitude;
(2) gather the data of accelerometer and gyroscope output and the data that collect are handled, adopt second order leveling and DOA estimation method to finish the coarse alignment of strapdown inertial navitation system (SINS), the preliminary attitude of determining carrier, be pitch angle θ, roll angle γ and course angle ψ, set up the initial strapdown matrix of strapdown inertial navitation system (SINS)
(3) at first, according to the angular speed of gyroscope output with and the attitude angle information estimation lever arm length of carrier: at two different moment t
1And t
2Accelerometer is respectively measured one group of specific force value
With
Utilize the different strapdown matrixes that obtain that constantly resolve
With
It is transformed into the calculating geographic coordinate system, obtains
Wherein
Be disturbing acceleration,
Be the distance between the oscillating motion center of the installation site of inertial measurement cluster and carrier,
Be the angular velocity of gyroscope output,
Be corresponding derivative,
Be respectively t
1, t
2Acceleration of gravity constantly, and
Order
Promptly
Obtain
Obtaining lever arm length is
Secondly, calculate the disturbing acceleration that lever arm effect causes:
Then, the output to accelerometer compensates:
Wherein
Be the specific force of compensation preacceleration meter output,
Specific force for the output of compensation post-acceleration meter;
(4) at first, setting up with velocity error and attitude error is the Kalman filtering state equation of state variable:
Wherein X is the state variable of system, and A and B are respectively the state-transition matrix and the noise matrix of system, and W is a system noise, and the state variable of system is
System noise is
δ V wherein
e, δ V
nRepresent east orientation, north orientation velocity error respectively, φ
e, φ
nAnd φ
uRepresent east orientation, north orientation and orientation misalignment respectively,
Represent X-axis, Y-axis accelerometer bias respectively, ε
x, ε
yAnd ε
zRepresent X-axis, Y-axis and Z axle gyroscope constant value drift respectively,
Be respectively X-axis, Y-axis accelerometer bias random white noise,
With
Represent X-axis, Y-axis and Z axle gyroscope constant value drift random white noise respectively, make the strapdown matrix
For
The state-transition matrix of system is
Wherein
ω in the formula
IeBe rotational-angular velocity of the earth, R
eBe earth radius,
Be the specific force of compensation post-acceleration meter output,
Be the angular velocity of gyroscope output, the system noise matrix is
Wherein
Secondly, setting up with velocity error and course error is the Kalman filtering measurement equation of measurement amount:
Z=HX+V,
Wherein Z is the measurement amount of system, and H is the measurement matrix of system, and V is the measurement noise battle array of system, and the amount of system is measured as
Z=[δV
e?δV
n?δψ]
T,
Wherein δ ψ=ψ '-ψ is the course error angle, the course angle that ψ ' resolves for strapdown inertial navitation system (SINS), and ψ is for to carry out revised course angle to the output of magnetic course transmitter, and the measurement matrix of system is
K wherein
1=-tan θ sin ψ, k
2=-tan θ cos ψ, θ, ψ are respectively the pitch angle and the course angle of carrier;
(5) utilize kalman filter method to estimate the misalignment of system, and come the strapdown attitude matrix of update the system with it the finish time at fine alignment:
The transition matrix that calculates between geographic coordinate system n ' and the local geographic coordinate system n is
Transition matrix between carrier coordinate system b and the local geographic coordinate system n is
According to
Determine attitude of carrier, promptly the main value of pitch angle θ, the roll angle γ of carrier and course angle ψ is respectively
The field of definition of roll angle is (0 a °, 360 °), and the field of definition of pitch angle is (90 °, 90 °), and the field of definition of course angle is (180 °, 180 °), and the true value that obtains attitude of carrier is
θ=θ
Main,
Initial alignment is finished.
Utilize under the swinging condition of the present invention low-accuracy strapdown inertial navigation system fast initial alignment method to carry out emulation experiment:
The three-axis swinging motion of carrier is that its mathematical model is respectively around the motion with sinusoidal rule of pitch axis, axis of roll and course axle:
Wherein: θ
m, γ
m, ψ
mBe respectively the amplitude of waving of carrier pitching, rolling, yawing; T
θ, T
γ, T
ψBe respectively the rolling period of pitching, rolling, yawing; φ
θ, φ
γ, φ
ψBe initial phase; ψ
0Be the angle, initial heading.During emulation, θ
m=6 °, γ
m=6 °, ψ
m=5 °; T
θ=7s, T
γ=9s, T
ψ=8s; The initial heading is ψ
0Get 30 °; Initial phase φ
θ, φ
r, φ
yBe 0.
Simulation time: 300s;
The initial position of carrier: 45.7796 ° of north latitude, 126.6705 ° of east longitudes;
Equatorial radius: R
e=6378393.0m;
Rotational-angular velocity of the earth: ω
Ie=7.2921158e-5rad/s;
Earth surface acceleration of gravity: g
0=9.78049m/s
2
Lever arm length:
Gyroscope constant value drift: 0.1 °/h;
Gyroscope Random Drift: 0.01 °/h;
Accelerometer bias: 10
-4G;
Accelerometer random deviation: 10
-5G;
The precision of magnetic course transmitter: 0.1 °;
Attitude error angle after coarse alignment finishes: 0.5 °, 0.5 °, 1 °;
The graph of errors that utilizes east orientation misalignment, north orientation misalignment and orientation misalignment that the method for the invention obtains is respectively as Fig. 3, Fig. 4 and shown in Figure 5.The result shows, under swinging condition, adopts method of the present invention can shorten estimated time of orientation misalignment effectively, improves the alignment precision of low-cost strapdown inertial navitation system (SINS) initial alignment.
Claims (1)
1. low-accuracy strapdown inertial navigation system fast initial alignment method under the swinging condition is characterized in that:
(1) determines the initial position parameters of carrier by GPS, comprise longitude and latitude;
(2) gather the data of accelerometer and gyroscope output and the data that collect are handled, adopt second order leveling and DOA estimation method to finish the coarse alignment of strapdown inertial navitation system (SINS), the preliminary attitude of determining carrier, be pitch angle θ, roll angle γ and course angle ψ, set up the initial strapdown matrix of strapdown inertial navitation system (SINS)
(3) at first, according to the angular speed of gyroscope output with and the attitude angle information estimation lever arm length of carrier: at two different moment t
1And t
2Accelerometer is respectively measured one group of specific force value
With
Utilize the different strapdown matrixes that obtain that constantly resolve
With
It is transformed into the calculating geographic coordinate system, obtains
Wherein
Be disturbing acceleration,
Be the distance between the oscillating motion center of the installation site of inertial measurement cluster and carrier,
Be the angular velocity of gyroscope output,
Be corresponding derivative,
Be respectively t
1, t
2Acceleration of gravity constantly, and
Order
Promptly
Obtain
Obtaining lever arm length is
Secondly, calculate the disturbing acceleration that lever arm effect causes:
Then, the output to accelerometer compensates:
Wherein
Be the specific force of compensation preacceleration meter output,
Specific force for the output of compensation post-acceleration meter;
(4) at first, setting up with velocity error and attitude error is the Kalman filtering state equation of state variable:
Wherein X is the state variable of system, and A and B are respectively the state-transition matrix and the noise matrix of system, and W is a system noise, and the state variable of system is
System noise is
δ V wherein
e, δ V
nRepresent east orientation, north orientation velocity error respectively, φ
e, φ
nAnd φ
uRepresent east orientation, north orientation and orientation misalignment respectively,
Represent X-axis, Y-axis accelerometer bias respectively, ε
x, ε
yAnd ε
zRepresent X-axis, Y-axis and Z axle gyroscope constant value drift respectively,
Be respectively X-axis, Y-axis accelerometer bias random white noise,
With
Represent X-axis, Y-axis and Z axle gyroscope constant value drift random white noise respectively, make the strapdown matrix
For
The state-transition matrix of system is
Wherein
ω in the formula
IeBe rotational-angular velocity of the earth, R
eBe earth radius,
Be the specific force of compensation post-acceleration meter output,
Be the angular velocity of gyroscope output, the system noise matrix is
Wherein
Secondly, setting up with velocity error and course error is the Kalman filtering measurement equation of measurement amount:
Z=HX+V,
Wherein Z is the measurement amount of system, and H is the measurement matrix of system, and V is the measurement noise battle array of system, and the amount of system is measured as
Z=[δV
e?δV
n?δψ]
T,
Wherein δ ψ=ψ '-ψ is the course error angle, the course angle that ψ ' resolves for strapdown inertial navitation system (SINS), and ψ is for to carry out revised course angle to the output of magnetic course transmitter, and the measurement matrix of system is
K wherein
1=-tan θ sin ψ, k
2=-tan θ cos ψ, θ, ψ are respectively the pitch angle and the course angle of carrier;
(5) utilize kalman filter method to estimate the misalignment of system, and come the strapdown attitude matrix of update the system with it the finish time at fine alignment:
The transition matrix that calculates between geographic coordinate system n ' and the local geographic coordinate system n is
Transition matrix between carrier coordinate system b and the local geographic coordinate system n is
According to
Determine attitude of carrier, promptly the main value of pitch angle θ, the roll angle γ of carrier and course angle ψ is respectively
The field of definition of roll angle is (0 a °, 360 °), and the field of definition of pitch angle is (90 °, 90 °), and the field of definition of course angle is (180 °, 180 °), and the true value that obtains attitude of carrier is
θ=θ
Main,
Initial alignment is finished.
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Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5527003A (en) * | 1994-07-27 | 1996-06-18 | Litton Systems, Inc. | Method for in-field updating of the gyro thermal calibration of an intertial navigation system |
US5719772A (en) * | 1994-09-28 | 1998-02-17 | Aerospatiale Societe Nationale Industrielle | Process and device for minimizing in an inertial measurement system the error due to a perturbing motion in the retrieval of the velocity |
JP2000321070A (en) * | 1999-05-11 | 2000-11-24 | Japan Aviation Electronics Industry Ltd | Strap-down inertial navigation device |
CN101464150A (en) * | 2009-01-09 | 2009-06-24 | 哈尔滨工程大学 | Test method for dynamic property of optical fiber gyroscope |
CN101629826A (en) * | 2009-07-01 | 2010-01-20 | 哈尔滨工程大学 | Coarse alignment method for fiber optic gyro strapdown inertial navigation system based on single axis rotation |
CN101706287A (en) * | 2009-11-20 | 2010-05-12 | 哈尔滨工程大学 | Rotating strapdown system on-site proving method based on digital high-passing filtering |
-
2010
- 2010-07-09 CN CN2010102221161A patent/CN101893445B/en not_active Expired - Fee Related
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5527003A (en) * | 1994-07-27 | 1996-06-18 | Litton Systems, Inc. | Method for in-field updating of the gyro thermal calibration of an intertial navigation system |
US5719772A (en) * | 1994-09-28 | 1998-02-17 | Aerospatiale Societe Nationale Industrielle | Process and device for minimizing in an inertial measurement system the error due to a perturbing motion in the retrieval of the velocity |
JP2000321070A (en) * | 1999-05-11 | 2000-11-24 | Japan Aviation Electronics Industry Ltd | Strap-down inertial navigation device |
CN101464150A (en) * | 2009-01-09 | 2009-06-24 | 哈尔滨工程大学 | Test method for dynamic property of optical fiber gyroscope |
CN101629826A (en) * | 2009-07-01 | 2010-01-20 | 哈尔滨工程大学 | Coarse alignment method for fiber optic gyro strapdown inertial navigation system based on single axis rotation |
CN101706287A (en) * | 2009-11-20 | 2010-05-12 | 哈尔滨工程大学 | Rotating strapdown system on-site proving method based on digital high-passing filtering |
Non-Patent Citations (6)
Title |
---|
《中国惯性技术学报》 20030630 曹洁等 捷联惯导初始对准中杆臂效应误差的补偿 全文 1 第11卷, 第3期 2 * |
《中国惯性技术学报》 20040630 高伟等 摇摆状态下捷联惯导系统初始对准技术的研究 全文 1 第12卷, 第3期 2 * |
《中国惯性技术学报》 20050630 关劲等 捷联惯导角速度匹配传递对准方法研究 全文 1 第13卷, 第3期 2 * |
《中国航海》 20030930 高伟等 水下潜器捷联惯导系统初始对准技术研究 全文 1 , 第3期 2 * |
《仪器仪表学报》 20100430 孙枫等 摇摆基座下旋转捷联系统粗对准技术研究 全文 1 第31卷, 第4期 2 * |
《兵工学报》 20081231 徐博等 舰船捷联航姿系统自主粗对准仿真与实验研究 全文 1 第29卷, 第12期 2 * |
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Publication number | Priority date | Publication date | Assignee | Title |
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