25 June 2014 Self-calibration method based on navigation in high-precision inertial navigation system with fiber optic gyro
Author Affiliations +
Optical Engineering, 53(6), 064103 (2014). doi:10.1117/1.OE.53.6.064103
Abstract
A rotary inertial navigation system requires higher calibration accuracy of some error parameters owing to rotation. Conventional multiposition and rotation calibration methods are limited, for they do not consider sensors’ actual operating condition. In order to achieve these parameters’ values as closely as possible to their true values in application, their influence on navigation is analyzed, and a relevant new calibration method based on a system’s velocity output during navigation is designed for the vital error parameters, including inertial sensors’ installation errors and the scale factor error of fiber optic gyro. Most importantly, this approach requires no additional devices compared to the conventional method and costs merely several minutes. Experimental results from a real dual-axis rotary fiber optic gyro inertial navigation system demonstrate the practicability and higher precision of the suggested approach.
Wang, Wang, Zhang, and Gao: Self-calibration method based on navigation in high-precision inertial navigation system with fiber optic gyro

1.

Introduction

It has becomes a trend that fiber optic gyro (FOG) is employed in inertial navigation systems (INS) due to its low cost, small size, low power consumption, and high reliability.1,2 Rotating inertial measurement units (IMU) periodically can bound the free propagation of the INS error introduced by gyro drift.3,4 Thus, this method is applied to improve the precision of FOG INS. As a single-axis rotary INS has an effect on only two gyros,5,6 one more rotation axis should be added at least to reduce the impact of all three gyros and achieve higher precision of navigation results.7,8 A typical rotation strategy of dual-axis rotary INS is presented in Ref. 9. But this strategy plays an equal role in the three gyros named x, y, and z. Compared to gyro z, the drifts of gyros x and y contribute more to the system’s inaccuracy during navigation. This paper examines a dual-axis rotary FOG INS with a new rotation strategy that rotates several circles along with the z axis to bound the drifts of gyros x and y and then quickly rotates 180 deg along the x axis to reduce the impact of gyro z’s drift, by which the drifts of gyros x and y can be mitigated more efficiently. For the change of rotation strategy, the influence of error parameters on navigation is diverse and the calibration associated with this should be redesigned.

Calibration is required by any type of INS.10 For the novel system proposed in this paper, because of its particular rotation, a more precise calibration is demanded for the gyro’s scale factor and some special installation error parameters. Conventional calibration, named multiposition and rotation method, generally, is carried out with the support of external turn tables.11,12 However, many error parameters are related to environmental conditions. The positions and rotational movements that the turn table affords differ from the actual operating condition of INS; hence, the values of error parameters calibrated by the method above are not accurate enough for system requiremenst. Especially for FOG INS, a gyro’s performance is more susceptible to environmental conditions, such as temperature,13,14 magnetic field,15 and vibration.16 Therefore, for the sake of high-precision, conventional multiposition and rotation method is treated as a basic calibration in the proposed INS, and a precise calibration considering the sensors’ actual operating condition is required.

Thus, a calibration based on the velocity error of navigation in a stationary base is designed to decrease the impact due to environmental conditions. What is more, this calibration method does not need the utilization of external high-accuracy turn tables. All in all, compared with a conventional multiposition and rotation method, this calibration meets system requirements of better accuracy in performance and brings a sharp decrease in cost.

The rest of the paper is organized as follows. Section 2 examines the error parameters in this system. The mathematical models between error parameters and velocity errors are established for the calibration in Sec. 3. Section 4 presents and discusses the experimental calibration results, followed by conclusions in Sec. 5.

2.

Analysis of Error Parameters

There is no doubt that sensor error exists in inertial systems. In this paper, gyro and accelerometer’s scale factor errors are symbolized as ΔKgx, ΔKgy, ΔKgz, ΔKax, ΔKay, and ΔKaz. Gyro drifts are symbolized as εx, εy, and εz. Accelerometer biases are symbolized as x, y, and z.

Misalignment angles due to installation account for the system’s navigation inaccuracy as well. Especially for rotary INS, they are different from those in common INS. To define these installation errors, except for two common coordinate frames called a body frame (denoted as b) and a navigation frame (denoted as n), another two essential coordinate frames and their relationship must also be illustrated. One is the inertial sensor axes frame (denoted as a) that is defined by the sensors’ input axes. Because it is unrealistic that gyros and accelerometers of the IMU are mounted orthogonally without any error, a-frame is a nonorthogonal coordinate frame. In contrast, the other one, called the IMU frame (denoted as s), is an orthogonal coordinate frame. First of all, sensors’ output should be transformed from a-frame to s-frame. As an s-frame varies with the real-time attitudes of IMU in rotary INS, data should be transformed to n-frame, which is a local-level frame with orientation east-north-up in this paper, for navigation calculation subsequently, and b-frame is used for attitude calculation.

The Zs axis of the s-frame is defined to coincide with the inner rotation axis of this dual-axis rotary INS. Then, the Xs axis is defined by the projection of Xa in the normal plane of Zs, and the Ys axis is defined according to the right-hand rule. Therefore, the misalignment of gyros can be presented by five small angles βgx, βgy, αgy, δgzX, and δgzY, as shown in Fig. 1. Then the direction cosine matrix required to transform the gyro data from a-frame to s-frame can be simplified as

(1)

Cags=[10βgxαgy1βgyδgzYδgzX1].

Fig. 1

Installation error of gyros.

OE_53_6_064103_f001.png

Similarly, the direction cosine matrix required to transform the accelerometer data from a-frame to s-frame can be simplified as

(2)

Caas=[1αaxβaxαay1βayδazYδazX1],
where symbols βax, βay, αax, αay, δazX, and δazY also represent six small angles.

3.

Principle of the Navigation-Based Self-Calibration Method

3.1.

Models of Navigation Error in Calibration

For systems studied in this paper, except the misalignment angles αax and αay, the rough values of other error parameters mentioned in Sec. 2 can be calibrated and compensated easily by conventional methods before navigation calculations, which makes this calibration based on navigation both necessary and feasible. On one hand, as the spatial relationship between gyros and accelerometers is hard to ascertain without system-level methods, αax and αay that are defined by taking x gyro as the reference in this paper, are not calibrated separately in the preceding conventional method. The conventional calibration obtained here is merely the difference of αax and αay so that to get their respective value by navigation is obligatory. On the other hand, if there is no conventional calibration and compensation reducing error in parameters’ value beforehand, it is difficult to separate them from each other.

Since the status of IMU in alignment is rotating along with the Zs axis, when IMU taking the same action in navigation, most error parameters are balanced with alignment error and can hardly be calibrated. Additionally, velocity output in stationary base navigation should be zero in theory. Thus, this paper focuses on a system’s velocity output when IMU rotates 180 deg along with the Xs axis. As shown in Fig. 2, the direction cosine matrix required to transform inertial sensor data from s-frame to b-frame in this course is

(3)

Csb=[1000cosωtsinωt0sinωtcosωt].

Fig. 2

Relations among coordinate frames.

OE_53_6_064103_f002.png

During the calibration, INS is placed with its b-frame coincident with the n-frame, approximately. So the direction cosine matrix required to transform inertial sensor data from b-frame to n-frame can be written as

(4)

Cbn=I3×3.

When the IMU starts to rotate along with Xs axis, taking no account of any error parameter, the output of inertial sensors can be expressed by Eqs. (5) and (6).

(5)

ωa=[ωωNcosωt+ωUsinωtωUcosωtωNsinωt],

(6)

fa=[0gsinωtgcosωt],
where ωa and fa are the output of gyros and accelerometers, respectively. ω is the angular velocity that IMU rotates along with the Xs axis. ωN and ωU denote the north and up components of Earth rotation angular velocity, respectively. g denotes the gravity acceleration.

The calibration takes only a few minutes so that the impact of gyro drift and accelerometer bias on the system’s velocity output is a drop in the bucket. Furthermore, there is a continuous large input only for x gyro in this process. So no sensor error other than the scale factor of x gyro can make a difference and be calibrated. Then Eq. (5) is updated as

(7)

ωa=[(1+ΔKgx)ωωNcosωt+ωUsinωtωUcosωtωNsinωt].

With the analysis above, the measured angular velocity ωn in n-frame is shown.

(8)

ωn=CbnCsbCagsωa=[100010001][1000cosωtsinωt0sinωtcosωt][10βgxαgy1βgyδgzYδgzX1][(1+ΔKgx)ωωNcosωt+ωUsinωtωUcosωtωNsinωt]=[(1+ΔKgx)ω+βgx(ωUcosωtωNsinωt)αgy(1+ΔKgx)ωcosωt+ωNβgy(ωUcos2ωtωNsinωtcosωt)+δgzY(1+ΔKgx)ωsinωtδgzX(ωNsinωtcosωt+ωUsin2ωt)αgy(1+ΔKgx)ωsinωt+ωUβgy(ωUsinωtcosωtωNsin2ωt)δgzY(1+ΔKgx)ωcosωt+δgzX(ωNcos2ωt+ωUsinωtcosωt)].

Similarly, the measured acceleration fn in n-frame is

(9)

fn=CbnCsbCaasfa=[100010001][1000cosωtsinωt0sinωtcosωt][1αaxβaxαay1βayδazYδazX1][0gsinωtgcosωt]=[αaxgsinωt+βaxgcosωtβaygcos2ωtδazXgsin2ωtgβaygsinωtcosωt+δazXgsinωtcosωt].

But the true angular velocity ω0n and acceleration f0n during this time in n-frame are

(10)

ω0n=[ωωNωU],

(11)

f0n=[00g].

So, based on Eqs. (8) and (10), the angular velocity measurement error Δωn can be described as

(12)

Δωn=ωnω0n=[ΔωEΔωNΔωU],
where

(13)

{ΔωE=ΔKgxω+βgx(ωUcosωtωNsinωt)ΔωN=αgy(1+ΔKgx)ωcosωtβgy(ωUcos2ωtωNsinωtcosωt)+δgzY(1+ΔKgx)ωsinωtδgzX(ωNsinωtcosωt+ωUsin2ωt)ΔωU=αgy(1+ΔKgx)ωsinωtβgy(ωUsinωtcosωtωNsin2ωt)δgzY(1+ΔKgx)ωcosωt+δgzX(ωNcos2ωt+ωUsinωtcosωt).

As every error parameter is infinitesimal, the product of them, such as αgyΔKgx, is a higher-order infinitesimal that can be ignored. Then Eq. (13) is simplified as

(14)

{ΔωE=ΔKgxω+βgx(ωUcosωtωNsinωt)ΔωN=αgyωcosωtβgy(ωUcos2ωtωNsinωtcosωt)+δgzYωsinωtδgzX(ωNsinωtcosωt+ωUsin2ωt)ΔωU=αgyωsinωtβgy(ωUsinωtcosωtωNsin2ωt)δgzYωcosωt+δgzX(ωNcos2ωt+ωUsinωtcosωt).

In a similar way, based on Eqs. (9) and (11), the acceleration measurement error Δfn can be described as

(15)

Δfn=fnf0n=[ΔfEΔfNΔfU],
where

(16)

{ΔfE=αaxgsinωt+βaxgcosωtΔfN=βaygcos2ωtδazXgsin2ωtΔfU=βaygsinωtcosωt+δazXgsinωtcosωt.

The angle errors engendered in this course can be obtained by integrating Eq. (14), as described by Eq. (17). The up component of angle errors is neither listed below nor employed in this calibration, because its impact on velocity cannot come to light in the next short calibration time IMU rotating along with Zs axis, especially when there is no translocation for the system.

(17)

{ΔϕE=0π/ωΔωEdt=ΔKgx0π/ωωdt+βgxωU0π/ωcosωtdtβgxωN0π/ωsinωtdt=ΔKgxπ2βgxωNωΔϕN=0π/ωΔωNdt=αgyω0π/ωcosωtdtβgyωU20π/ω(1+cos2ωt)dt+βgyωN20π/ωsin2ωtdt+δgzYω0π/ωsinωtdtδgzXωN20π/ωsin2ωtdtδgzXωU20π/ω(1cos2ωt)dt=βgyωUπ2ω+2δgzYδgzXωUπ2ω,
where ΔϕE and ΔϕN express the east and north components of angle errors.

According to inertial navigation theory, ΔϕE and ΔϕN will cause the increase of horizontal velocity errors directly and observably. As the following period IMU rotating along with the Zs axis is so short in this paper, the impact caused by ΔϕE and ΔϕN can be described by Eq. (18) for simplicity.

(18)

{ΔVE=0tΔϕNgdt=ΔϕNgtΔVN=0tΔϕEgdt=ΔϕEgt,
where ΔVE and ΔVN express the east and north components of velocity errors.

The velocity errors caused in this course can be obtained by integrating Eq. (16), as described by Eq. (19). The up component of velocity is usually damped by other height sensors and its error mechanism is changed. Correspondingly, only horizontal velocity errors are taken into account as well.

(19)

{ΔVE=0π/ωΔfEdt=αaxg0π/ωsinωtdt+βaxg0π/ωcosωtdt=2αaxgωΔVN=0π/ωΔfNdt=βayg20π/ω(1+cos2ωt)dtδazXg20π/ω(1cos2ωt)dt=βaygπ2ωδazXgπ2ω.

3.2.

Navigation-Based Calibration Solution

The error parameters listed above, except for αax and αay, have been corrected by a conventional method ahead of time; hence, the values of them become small in this calibration. For instance, the FOG scale factor errors can be reduced from several thousand parts per million (ppm) to dozens of ppm, and misalignment angles can be reduced from hundreds or thousands of arc seconds to several arc seconds. Based on this, Table 1 exhibits the pragmatic numerical relationship between error parameters and navigation errors in accordance with Eqs. (17) and (19), supposing ω=6deg/s, ωN=11.49deg/h, ωU=9.64deg/h, and g=9.8m/s.

Table 1

Numerical relationship between error parameters and navigation errors.

Error parameterSet value of error parameterNavigation errors
ΔϕE (“)ΔϕN (“)ΔVE (m/s)ΔVN (m/s)
ΔKgx50 ppm32.4000
βgx5”−0.0053000
βgy5”0−0.003500
δgzX5”0−0.003500
δgzY5”01000
βay5”000−0.0036
αax200”00−0.180
δazX5”000−0.0036

Note: The largest values are indicated in bold.

What deserve special attention are the impacts of ΔKgx on ΔϕE, δgzY on ΔϕN, and αax on ΔVE, since their values are a few orders of magnitude larger than others’. In line with Eq. (18), supposing the next time IMU rotating along with the Zs axis is 2 min and the east angle error is 32.4, the north velocity error that follows reaches up to 0.19m/s, which is definitely apparent and unacceptable in high-precision INS. It is similar to the north angle error and the east velocity error. Furthermore, the noteworthy impacts are so decoupled that ΔKgx, δgzY, and αax can be worked out effortlessly, which is helpful for the realization of calibration based on navigation.

Calculating the east velocity error ΔVE in the course of IMU rotating along with Xs axis can directly help obtain the value of x accelerometer’s installation error αax by Eq. (20), which is an expression of another form for Eq. (19).

(20)

αax=ΔVEω2g.

While the value of αax is acquired in this way, αay, the other parameters that cannot be calibrated by conventional method can be calculated by Eq. (21).

(21)

αay=(αayαax)+αax,
where (αayαax) is obtained by a conventional method in advance.

Calculating the east velocity error ΔVE in the followed course of IMU rotating along with Zs axis can help obtain the north angle error ΔϕN by Eq. (18) first, and then z gyro’s installation error δgzY would be obtained by Eq. (22), which is a simplification and variant of Eq. (17). Calculating the north velocity error ΔVN in the same course can give an east angle error ΔϕE by Eq. (18), and x gyro’s scale factor error ΔKgx would be obtained by Eq. (22) subsequently.

(22)

{ΔKgx=1πΔϕEδgzY=12ΔϕN.

As velocity is also affected by the precision of alignment, this calibration is implemented by averaging the testing values of repeated measurements to reduce the impact of alignment error. Although not all of the error parameters can be calibrated using this approach, the key parameters that strongly damage a system’s precision can be calibrated to a more advanced level.

4.

Experimental Results and Discussion

4.1.

Experimental Method

The dual-axis rotary FOG INS, which has been calibrated and compensated by conventional method, is placed on a stationary marble platform with the system’s b-frame coincident with n-frame approximately (Fig. 3). The INS’s inner axis is named Zs axis, while the outer axis is named Xs axis. The system used in this experiment consists of three FOGs with an accuracy of 0.05deg/h and three quartz accelerometers with an accuracy of 60 μg. It is fed by a dc-regulated power supply, and data are sampled by a laptop at a frequency of 20 Hz. According to the principle analyzed in Sec. 3, the INS works as follows.

Fig. 3

The experimental setup.

OE_53_6_064103_f003.png

After alignment, the navigation calculation starts, and the IMU rotates along with the Zs axis first. Two minutes later, rotation along with the Zs axis suspends and rotation along with the Xs axis executes for 30 s at a speed of 6deg/s, which means the IMU rotates 180 deg along with the Xs axis. Then rotation along the Zs axis continues, followed by rotation along the Xs axis in the inverse direction.

In the whole process, INS velocity is recorded for calibration. As it is carried out on a stationary base, velocity should be zero theoretically. So INS velocity just represents the velocity error and is treated as the measurement in calibration. This calibration must be completed in the first several minutes of navigation, because the accuracy of velocity decreases over operating time in INS. At the beginning, the measurement accuracy of velocity is usually better than 0.001m/s. Take x gyro’s scale factor error for example; according to Eqs. (18) and (22), the corresponding calibration error is 0.3ppm, which can be ignored.

4.2.

Calibration of x Accelerometer’s Installation Error

From the velocity output in the stationary base, we can get its velocity error directly. Figure 4 shows one calibration result for αax based on the east velocity error during IMU rotating along with Xs axis. During this process, which starts at the end of the second minute and ends a half minute later in Fig. 4(a), an east velocity error with the value of 0.113m/s arises, meaning there is a misalignment angle of x accelerometer with a value of 124.2 based on Eq. (20). Table 2 is a summary of calibration experimental results for αax. The mean of six results implies that the value of αax is 121.1, while the root mean square suggests the achievable calibration accuracy for αax is 2. After compensating αax using the mean value in Table 2, the obvious fluctuation of east velocity disappears as shown in Fig. 4(b).

Fig. 4

Compare results of the east velocity error due to αax: (a) before calibration and (b) after calibration and compensation.

OE_53_6_064103_f004.png

Table 2

Calibration results of αax.

Test numberΔVE (m/s) Rotation along with the Xs axisαax (“)
1−0.113124.2
2−0.110121.5
3−0.111122.6
4−0.107117.9
5−0.109120.5
6−0.109119.7
Mean−0.110121.1
Root mean square0.0022

4.3.

Calibration of z Gyro’s Installation Error

With the calibration and compensation of x accelerometer’s installation error αax, the variation of east velocity is not as drastic as before, leaving z gyro’s installation error δgzY as the dominant error source. In Fig. 5(a), during the rotation along with Zs axis from 2.5 to 4.5 min, the east velocity error augments nearly 0.065m/s, and a misalignment angle of z gyro with the value of 5.7 can be figured out based on Eqs. (18) and (22). Six experimental calibration results are listed in Table 3, indicating that the residual value of δgzY after calibration and compensation by a conventional approach is some 5, and its achievable accuracy is as good as 0.7. As shown in Fig. 5(b), correcting δgzY with 5, the east velocity error stays near zero throughout the succedent rotation along with the Zs axis.

Fig. 5

Compare results of the east velocity error due to δgzY: (a) before calibration and (b) after calibration and compensation.

OE_53_6_064103_f005.png

Table 3

Calibration results of δgzY.

Test numberΔVE (m/s) Rotation along with the Zs axisΔϕN (“) Rotation along with the Xs axisδgzY (“)
10.065−11.4−5.7
20.044−7.6−3.8
30.055−9.7−4.8
40.064−11.2−5.6
50.059−10.3−5.2
60.055−9.6−4.8
Mean0.057−10.0−5.0
Root mean square0.00810.7

4.4.

Calibration of x Gyro’s Scale Factor Error

Different from the two calibrations above, the calibration of the x gyro’s scale factor error is based on the north velocity error. On account of the angle error engendered during rotation along with Xs axis due to ΔKgx, a balloon of 0.242m/s happens to ΔVN when IMU rotates along with the Zs axis subsequently, as shown in Fig. 6(a). Utilizing Eqs. (18) and (22), the corresponding scale factor error with the value of 65.5 ppm can be worked out. Taking the same way, another five experimental results are received and recorded in Table 4. Using the mean value of 67.8 ppm for six results with an accuracy of 6 ppm to modify the x gyro’s scale factor, the north velocity error is improved substantially.

Fig. 6

Compare results of the north velocity error due to ΔKgx: (a) before calibration and (b) after calibration and compensation.

OE_53_6_064103_f006.png

Table 4

Calibration results of ΔKgx.

Test numberΔVN (m/s) Rotation along with the Zs axisΔϕE (“) Rotation along with the Xs axisΔKgx (ppm)
10.24242.565.5
20.24843.567.1
30.22940.161.9
40.29251.178.9
50.23941.964.7
60.25444.468.6
Mean0.25143.967.8
Root mean square0.0246

4.5.

Discussion

The experiments above are finished by the system’s own operation, instead of mounting it on a high-accuracy turn table. In addition, the abscissas of Figs. 4(a), 5(a), and 6(a) indicate that this calibration method costs no more than 6 min, and, in contrast, conventional methods usually take as long as several quarters to calibrate these parameters. Both of the two points are in favor of this calibration’s convenience. Although the impact of operating conditions on sensors is finite, the value of δgzY in Table 3 is only 5, and the value of ΔKgx in Table 4 is only 67.8ppm, they are not small enough and cause large navigation errors. Rapid accumulation of velocity errors disappear after calibration and compensation by the proposed technique, which suggests that this method is more accurate than conventional calibration in this system. The comparison of this calibration method with a conventional method is refined in Table 5.

Table 5

Comparison of calibration techniques.

Multiposition and rotation calibrationSelf-calibration method based on navigation
Dependence on external deviceYesNo
Execution timeBefore navigationIn navigation
Parameters that can be calibratedAlmost all parametersKey parameters
Time that calibration consumedSeveral quartersSeveral minutes
Accuracy that meets system requirementLimitedHigh

5.

Conclusion

A calibration approach based on the velocity error of stationary base navigation is presented for dual-axis rotary FOG INS in this paper. There are two uppermost advantages for this method. First, it is simple and practicable because it takes only several minutes and is implemented by its own rotating mechanism requiring no external device. Second, it is executed during the navigation process, namely, the status of IMU and the surroundings during calibration are the same as those during navigation, and the calibration results are more accurate compared with those obtained by a conventional method. One possible disadvantage is that not all error parameters can be calibrated. However, error parameters calibrated by this method, including x accelerometer’s installation error, z gyro’s installation error, and x gyro’s scale factor error, are the fatal error sources in this type of inertial system. The accuracy of other parameters calibrated by conventional methods is also acceptable for this system. The experimental results show that high accuracies of 2 and 0.7 can be achieved for x accelerometer and z gyro’s installation errors, respectively, while high accuracy of 6 ppm can be achieved for x gyro’s scale factor error.

Acknowledgments

This study was supported by the Aeronautical Science Foundation of China (20110851007) and the Fund of BUAA for Graduate Innovation and Practice (YCSJ-01-2013-03).

References

1. 

S. Sabatet al., “Characterization of fiber optics gyro and noise compensation using discrete wavelet transform,” in Proc. 2nd Int. Conf. on Emerging Trends in Engineering and Technology, pp. 909–913, IEEE, Nagpur (2009).Google Scholar

2. 

J. Nayak, “Fiber-optic gyroscopes: from design to production,” Appl. Opt. 50(25), E152–E161 (2011).APOPAI0003-6935http://dx.doi.org/10.1364/AO.50.00E152Google Scholar

3. 

W. Sunet al., “MEMS-based rotary strapdown inertial navigation system,” Measurement 46(8), 2585–2596 (2013).MSRMDA0263-2241http://dx.doi.org/10.1016/j.measurement.2013.04.035Google Scholar

4. 

S. Ishibashiet al., “Accuracy improvement of an inertial navigation system brought about by the rotational motion,” in OCEANS 2007-Europe, pp. 1–5, IEEE, Aberdeen, England (2007).Google Scholar

5. 

Y. F. Xuet al., “Error modeling and compensation for rotation-modulation strapdown inertial navigation system,” Adv. Sci. Lett. 5(2), 981–985 (2012).1936-6612 http://dx.doi.org/10.1166/asl.2012.1850Google Scholar

6. 

W. SunY. Gao, “Fiber-based rotary strapdown inertial navigation system,” Opt. Eng. 52(7), 076106 (2013).OPEGAR0091-3286http://dx.doi.org/10.1117/1.OE.52.7.076106Google Scholar

7. 

K. M. Hayset al., “A submarine navigator for the 21th century,” in Position Location Navigation Symp., pp. 179–188, IEEE, California (2002).Google Scholar

8. 

B. L. YuanD. LiaoS. L. Han, “Error compensation of an optical gyro INS by multi-axis rotation,” Meas. Sci. Technol. 23(2), 025102 (2012).MSTCEP0957-0233http://dx.doi.org/10.1088/0957-0233/23/2/025102Google Scholar

9. 

J. H. Chenget al., “Research of strapdown inertial navigation system monitor technique based on dual-axis consequential rotation,” in IEEE Int. Conf. on Information and Automation, pp. 203–208, IEEE, Shenzhen (2011).Google Scholar

10. 

R. Peesapatiet al., “Efficient hybrid Kalman filter for denoising fiber optic gyroscope signal,” Optik 124(20), 4549–4556 (2013).OTIKAJ0030-4026http://dx.doi.org/10.1016/j.ijleo.2013.02.013Google Scholar

11. 

J. K. Bekkeng, “Calibration of a novel MEMS inertial reference unit,” IEEE Trans. Instrum. Meas. 58(6), 1967–1974 (2009).IEIMAO0018-9456http://dx.doi.org/10.1109/TIM.2008.2006126Google Scholar

12. 

T. Nieminenet al., “An enhanced multi-position calibration method for consumer-grade inertial measurement units applied and tested,” Meas. Sci. Technol. 21(10), 105204 (2010).MSTCEP0957-0233http://dx.doi.org/10.1088/0957-0233/21/10/105204Google Scholar

13. 

A. M. KurbatovR. A. Kurbatov, “Temperature characteristics of fiber-optic gyroscope sensing coils,” J. Commun. Technol. Electron. 58(7), 745–752 (2013).JTELEJ1064-2269http://dx.doi.org/10.1134/S1064226913060107Google Scholar

14. 

Z. H. Liet al., “A novel method for determining and improving the quality of a quadrupolar fiber gyro coil under temperature variations,” Opt. Express 21(2), 2521–2530 (2013).OPEXFF1094-4087http://dx.doi.org/10.1364/OE.21.002521Google Scholar

15. 

D. W. Zhanget al., “Magnetic drift in single depolarizer interferometric fiber-optic gyroscopes induced by orthogonal magnetic field,” Opt. Eng. 52(5), 054403 (2013).OPEGAR0091-3286http://dx.doi.org/10.1117/1.OE.52.5.054403Google Scholar

16. 

Y. G. ZhangZ. X. Gao, “Fiber optic gyroscope vibration error due to fiber tail length asymmetry based on elastic-optic effect,” Opt. Eng. 51(12), 124403 (2012).OPEGAR0091-3286http://dx.doi.org/10.1117/1.OE.51.12.124403Google Scholar

Biography

Lei Wang is a PhD candidate in precision instrument and machinery at Beihang University. He received his BEng from the School of Instrumentation Science and Opto-electronics Engineering, Beihang University in 2009. His research interests are in inertial navigation, motor control, and so forth.

Wei Wang received her PhD from Northwestern Polytechnical University in 2005. From 2005 to 2007, she was a postdoctoral fellow at the School of Instrumentation Science and Opto-electronics Engineering, Beihang University, where she is currently an associate professor. Her research fields include inertial navigation, satellite navigation, and integrated navigation.

Qian Zhang is a PhD candidate in precision instrument and machinery at Beihang University. He received his BEng from the School of Instrumentation Science and Opto-electronics Engineering, Beihang University in 2012. His research interests include inertial navigation.

Pengyu Gao is a PhD candidate in precision instrument and machinery at Beihang University. He received his BEng from the School of Advanced Engineering, Beihang University in 2012. His research interests are in inertial navigation, big data, and so forth.

Lei Wang, Wei Wang, Qian Zhang, Pengyu Gao, "Self-calibration method based on navigation in high-precision inertial navigation system with fiber optic gyro," Optical Engineering 53(6), 064103 (25 June 2014). http://dx.doi.org/10.1117/1.OE.53.6.064103
Submission: Received ; Accepted
JOURNAL ARTICLE
8 PAGES


SHARE
KEYWORDS
Calibration

Gyroscopes

Navigation systems

Fiber optic gyroscopes

Sensors

Inertial navigation systems

Optical engineering

Back to Top